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  • AIRCRAFT PROPULSION AND POWER  (270)
  • 2000-2004
  • 1995-1999
  • 1980-1984
  • 1975-1979  (270)
  • 1977  (270)
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Schlagwörter
Erscheinungszeitraum
  • 2000-2004
  • 1995-1999
  • 1980-1984
  • 1975-1979  (270)
Jahr
  • 1
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    Aircraft engines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-16
    Beschreibung: Thrust and weight requirements of aircraft engines in general are discussed. The characteristics and operating principles of various types of air breathing and rocket engines are described.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Soviet Aircraft and Rockets (NASA-TT-F-770); p 81-139
    Format: text
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  • 2
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    Streamtube analysis of a hydrogen-burning scramjet exhaust and simulation technique (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-17
    Beschreibung: A scramjet/airframe integration program and a technique for simulating thermally perfect scramjet exhaust flows (freon/argon gas blends) is studied to extend the technique to more complicated flows approaching the actual exhaust flow in complexity. The state of the flow and the accuracy of the substitute gas simulation are analyzed in the case of a shock discontinuity present. Findings are: scramjet exhaust flow is essentially frozen throughout the expansion at Mach 6 and Mach 8; flow behind moderate shocks remains frozen; the technique can accurately track static distributions in scramjet exhaust flows (shocked or unshocked).
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Journal of Aircraft; 14; Sept
    Format: text
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  • 3
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    How good is jet lift VTOL technology (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-17
    Beschreibung: The status of technologies for jet-lift V/STOL aircraft is examined, and a critical review of the performance of jet-lift VTOL aircraft built to date is made. Most jet-lift aircraft have suffered from adverse propulsion-induced effects during takeoff and landing. Flight dynamics of jet-lift aircraft have suffered from shortcomings in static and dynamic stability, control characteristics, and flight path control. Some of the main problems to be considered during the selection of a propulsion system arrangement for a V/STOL fighter are discussed. At present, experimental and analytical data on supersonic V/STOL configurations are insufficient to permit evaluating propulsion system arrangements.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Astronautics and Aeronautics; 15; Dec. 197
    Format: text
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  • 4
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    Effect of endwall cooling on secondary flows in turbine stator vanes (1977)
    In:  CASI
    Details
    Publikationsdatum: 2012-05-19
    Beschreibung: An experimental investigation was performed to determine the effect of endwall cooling on the secondary flow behavior and the aerodynamic performance of a coreturbine stator vane. The investigation was conducted in a cold-air, full-annular cascade, where three-dimensional effects could be obtained. Two endwall cooling configurations were tested. In the first configuration, the cooling holes were oriented so that the coolant was injected in line with the inviscid streamline direction. In the second configuration, the coolant was injected at an angle of 15 deg to the inviscid streamline direction and oriented toward the vane pressure surface. In both cases the stator vanes were solid and uncooled so that the effect of endwall cooling could be obtained directly. Total-pressure surveys were taken downstream of the stator vanes over a range of cooling flows at the design, mean-radius, critical velocity ratio of 0.778. Changes in the total-pressure contours downstream of the vanes were used to obtain the effect of endwall cooling on the secondary flows in the stator. Comparisons were made between the two cooled-endwall configurations and with the results obtained previously for solid endwalls.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: AGARD Secondary Flows in Turbomachines; 29 p
    Format: text
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  • 5
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    Advanced low-NO(x) combustors for supersonic high-altitude gas turbines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The impact of gas-turbine-engine-powered aircraft on worldwide pollution was defined within two major areas of contribution. First, the contribution of aircraft to the local air pollution of metropolitan areas and, second, the long-term effects on the chemical balance of the stratosphere of pollutants emitted from future generations of high-altitude, supersonic commercial and military aircraft. Preliminary findings indicate that stratospheric oxides of nitrogen (NOx) emissions may have to be limited to very low levels if, for example, ozone depletion with concomitant increases in sea-level radiation, are to be avoided. Theoretical considerations suggest that (NOx) levels as low as 1.0 gram per kilogram of fuel and less should be attainable from a idealized premixed type of combustor. Experimental rig studies were intended to explore new combustor concepts designed to minimize the formation of (NOx) in aircraft gas turbines and to define their major operational problems and limitations.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 393-415
    Format: application/pdf
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  • 6
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    Soot formation in a turbulent swirling flow (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The qualitative understanding of soot formation in simple models of gas turbine primary-zone combustors is summarized. Soot formation in flame radiation and air pollution was investigated. Results are presented, namely: (1) if the fuel is premixed with air in approximately stoichiometric proportions, the sequence of states that a fluid element undergoes as it burns is quite different from the sequence when liquid or vapor fuel is injected into an air-flow; (2) swirling flows, as are typical or swirl-can combustors, when burning, can amplify small aerodynamic disturbances upstream of the swirl vanes; and (3) different fuels form significantly different amounts of soot. Each of these effects makes major changes in the amount of soot formed in a given combustor.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 309-321
    Format: application/pdf
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  • 7
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    Pollution reduction technology program for turboprop engines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The reduction of CO, HC, and smoke emissions while maintaining acceptable NO(x) emissions without affecting fuel consumption, durability, maintainability, and safety was accomplished. Component combustor concept screening directed toward the demonstration of advanced combustor technology required to meet the EPA exhaust emissions standards for class P2 turboprop engines was covered. The combustion system for the Allison 501-D22A engine was used, and three combustor design concepts - reverse flow, prechamber, and staged fuel were evaluated.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 125-147
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  • 8
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    Ceramic composite protection for turbine disc bursts (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Ceramic composite turbine disc protection panels for the A300B were developed using armor technology. Analytical predictions for modifying the ballistic projectile armor system were verified by a test program conducted to qualify the rotor containment system. With only a slight change in the areal density of the armor system a more than two-fold increase in kinetic energy protection level was achieved. Thickness of the fiberglass reinforced plastic backing material was increased to achieve an optimum ratio of ceramic thickness to backing thickness for the different ballistic defeat condition.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 277-293
    Format: application/pdf
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  • 9
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    Materials and manufacturing processes for increased life/reliability (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Improvements in both quality and durability of disk raw material for both military and commercial engines necessitated an entirely new concept in raw material process control which imposes careful selection, screening and sampling of the basic alloy ingredients, followed by careful monitoring of the melting parameters in all phases of the vacuum melting sequence. Special care is taken to preclude solidification conditions that produce adverse levels of segregation. Melt furnaces are routinely cleaned and inspected for contamination. Ingots are also cleaned and inspected before entering the final melt step.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 347-368
    Format: application/pdf
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  • 10
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    Numerical analysis of projectile impact in woven texile structures (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Computer codes were developed for simulating the dynamic fracture and viscoelastic constitutive response due to stress wave interaction and reflections caused by ballistic impact on woven textiles. The method, which was developed for use in the design and analysis of protection devices for personnel armor, has potential for use in studies of rotor blade burst containment at high velocity. Alterations in coding required for burst containment problems are discussed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Assessment of Technol. for Turbojet Engine Rotor Failures; p 247-260
    Format: application/pdf
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  • 11
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    Lightweight engine containment (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Kevlar fabric styles and weaves were studied, as well as methods of application for advanced gas turbine engines. The Kevlar material was subjected to high speed impacts by simple projectiles fired from a rifle, as well as more complex shapes such as fan blades released from gas turbine rotors in a spin pit. Just contained data was developed for a variety of weave and/or application techniques, and a comparative containment weight efficiency was established for Kevlar containment applications. The data generated during these tests is being incorporated into an analytical design system so that blade containment trade-off studies between Kevlar and metal case engine structures can be made. Laboratory tests and engine environment tests were performed to determine the survivability of Kevlar in a gas turbine environment.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 235-245
    Format: application/pdf
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  • 12
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    Approaches to rotor fragment protection (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Key airworthiness design criteria considerations for fragment protection as found in various FAA requirements in FAR Parts 25 and 33, and in interpretive 8110 orders are reviewed. The impact of providing aircraft armor in lieu of engine armor for typical three- and four-engine wide bodied transports for protection within the length of the engine case as well as from fragments exiting ahead of the enlet engine inlet flange is assessed. For protection within the length of the engine case, armor weight penalties, plus fuel burned and dollar cost of carrying the armor protection are defined. Immediately ahead of the inlet flange, direct tangential impacts are predominant, but further forward, rebound impacts predominate. Armor thickness requirements and fuel cost impact of protection are given.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 101-103
    Format: application/pdf
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  • 13
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    Engine Non-Containment: The UK CAA View (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Airworthiness accidents account for roughly one quarter of the total number of accidents to public transport turbojet aircraft. The most reliable, practicable, and cost-effective means of minimizing damage outside the confines of the nacelle is to make the aircraft design invulnerable to any debris which may affect the aircraft. A failure model was developed for use by aircraft builders in measuring the freedom from catastrophe factor of their design.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 11-32
    Format: application/pdf
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  • 14
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    Effect of ambient temperature and humidity on emissions of an idling gas turbine (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The effects of inlet pressure, temperature, and humidity on the oxides of nitrogen produced by an engine operating at takeoff power setting were investigated and numerous correction factors were formulated. The effect of ambient relative humidity on gas turbine idle emissions was ascertained. Experimentally, a nonvitiating combustor rig was employed to simulate changing combustor inlet conditions as generated by changing ambient conditions. Emissions measurements were made at the combustor exit. For carbon monoxide, a reaction kinetic scheme was applied within each zone of the combustor where initial species concentrations reflected not only local combustor characteristics but also changing ambient conditions.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 437-456
    Format: application/pdf
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  • 15
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    Global atmospheric sampling program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Automated instruments were installed on a commercial B-747 aircraft, during the program, to obtain baseline data and to monitor key atmospheric constituents associated with emissions of aircraft engines in order to determine if aircraft are contributing to pollution of the upper atmosphere. Data thus acquired on a global basis over the commercial air routes for 5 to 10 years will be analyzed. Ozone measurements in the 29,000 to 45,000 foot altitude were expanded over what has been available from ozonesondes. Limited aerosol composition measurements from filter samples show low levels of sulfates and nitrates in the upper troposphere. Recently installed instruments for measurement of carbon monoxide and condensation nuclei are beginning to return data.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 323-355
    Format: application/pdf
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  • 16
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    Emissions control for ground power gas turbines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The similarities and differences of emissions reduction technology for aircraft and ground power gas turbines is described. The capability of this technology to reduce ground power emissions to meet existing and proposed emissions standards is presented and discussed. Those areas where the developing aircraft gas turbine technology may have direct application to ground power and those areas where the needed technology may be unique to the ground power mission are pointed out. Emissions reduction technology varying from simple combustor modifications to the use of advanced combustor concepts, such as catalysis, is described and discussed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 203-242
    Format: application/pdf
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  • 17
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    Pollution reduction technology program for small jet aircraft engines: Class T1 (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Small jet aircraft engines (EPA class T1, turbojet and turbofan engines of less than 35.6 kN thrust) were evaluated with the objective of attaining emissions reduction consistent with performance constraints. Configurations employing the technological advances were screened and developed through full scale rig testing. The most promising approaches in full-scale engine testing were evaluated.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 149-180
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  • 18
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    Emissions Reduction Technology Program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Combustor concepts having the potential for significantly lower emissions levels were investigated. The combustor emissions reduction was measured in an engine test. Emission characteristics common to all engine classes are shown. Multiple-burning zone combustors, specifically the double-annular and swirl-can combustors were studied. Airblast and air-assist fuel injection techniques were evaluated for emissions control potential. The combustor sceening and refining phases are summarized.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 19-58
    Format: application/pdf
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  • 19
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    Turbine disks for improved reliability (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Advanced disk structural concepts were employed to improve the cyclic lives and reliability of turbine disks. Analytical studies were conducted to evaluate bore-entry disks as potential replacements for the existing first-stage turbine disks in the CF6-50 and JT8D-17 engines. Results of low cycle fatigue, burst, fracture mechanics, and fragment energy analyses are summarized for the advanced disk designs and the existing disk designs, with both conventional and advanced disk materials. Other disk concepts such as composite, laminated, link, multibore, multidisk, and spline disks were also evaluated for the CF6-50 engine.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 389-411
    Format: application/pdf
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  • 20
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    Analysis methods for Kevlar shield response to rotor fragments (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Several empirical and analytical approaches to rotor burst shield sizing are compared and principal differences in metal and fabric dynamic behavior are discussed. The application of transient structural response computer programs to predict Kevlar containment limits is described. For preliminary shield sizing, present analytical methods are useful if insufficient test data for empirical modeling are available. To provide other information useful for engineering design, analytical methods require further developments in material characterization, failure criteria, loads definition, and post-impact fragment trajectory prediction.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 261-275
    Format: application/pdf
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  • 21
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    Rotor burst protection criteria and implications (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Current aircraft design practices to minimize the hazard from rotor bursts are described. The consequences of non-contained engine failures and the impact of rotor burst protection systems on aircraft design are discussed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 37-43
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  • 22
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    Laboratory studies of lean combustion (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The fundamental processes controlling lean combustion were observed for better understanding, with particular emphasis on the formation and measurement of gas-phase pollutants, the stability of the combustion process (blowout limits), methods of improving stability, and the application of probe and optical diagnostics for flow field characterization, temperature mapping, and composition measurements. The following areas of investigation are described in detail: (1) axisymmetric, opposed-reacting-jet-stabilized combustor studies; (2) stabilization through heat recirculation; (3) two dimensional combustor studies; and (4) spectroscopic methods. A departure from conventional combustor design to a premixed/prevaporized, lean combustion configuration is attractive for the control of oxides of nitrogen and smoke emissions, the promotion of uniform turbine inlet temperatures, and, possibly, the reduction of carbon monoxide and hydrocarbons at idle.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 417-436
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  • 23
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    Alternative fuels (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Potential problems related to the use of alternative aviation turbine fuels are discussed and both ongoing and required research into these fuels is described. This discussion is limited to aviation turbine fuels composed of liquid hydrocarbons. The advantages and disadvantages of the various solutions to the problems are summarized. The first solution is to continue to develop the necessary technology at the refinery to produce specification jet fuels regardless of the crude source. The second solution is to minimize energy consumption at the refinery and keep fuel costs down by relaxing specifications.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 277-308
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  • 24
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    Summary of emissions reduction technology programs (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The NASA emissions reduction contract programs for EPA aircraft engine classes P2 (turboshaft engines), T1 (jet engines with thrust under 8000 lb), T4 (JT8D) engines), and T2 (jet engines with thrust over 8000 lb) are discussed. The most important aspects of these programs, the commonality of approaches used, the test results, and assessments regarding applications of the derived technology are summarized.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 181-202
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  • 25
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    NASA/Pratt and Whitney experimental clean combustor program: Engine test results (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: A two-stage vorbix (vortex burning and mixing) combustor and associated fuel system components were successfully tested in an experimental JT9D engine at steady-state and transient operating conditions, using ASTM Jet-A fuel. Full-scale JT9D experimental engine tests were conducted in a phase three aircraft experimental clean combustor program. The low-pollution combustor, fuel system, and fuel control concepts were derived from phase one and phase two programs in which several combustor concepts were evaluated, refined, and optimized in a component test rig. Significant pollution reductions were achieved with the combustor which meets the performance, operating, and installation requirements of the engine.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 91-123
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  • 26
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    Stratospheric cruise emission reduction program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: A recently implemented NASA effort specifically aimed at reducing cruise oxides of nitrogen from high-altitude aircraft is discussed. The desired emission levels and the combustor technology required to achieve them are discussed. A brief overview of the SCERP operating plan is given. Lean premixed-prevaporized combustion and some of the potential difficulties that are associated with applying this technique to gas turbine combustors are examined. Base technology was developed in several key areas. These fundamental studies are viewed as a requirement for successful implementation of the lean premixed combustion technique.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 357-391
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  • 27
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    General aviation piston-engine exhaust emission reduction (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: To support the promulgation of aircraft regulations, two airports were examined, Van Nuys and Tamiami. It was determined that the carbon monoxide (CO) emissions from piston-engine aircraft have a significant influence on the CO levels in the ambient air in and around airports, where workers and travelers would be exposed. Emissions standards were set up for control of emissions from aircraft piston engines manufactured after December 31, 1979. The standards selected were based on a technologically feasible and economically reasonable control of carbon monoxide. It was concluded that substantial CO reductions could be realized if the range of typical fuel-air ratios could be narrowed. Thus, improvements in fuel management were determined as reasonable controls.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 243-275
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  • 28
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    Pollution reduction technology program for class T4(JT8D) engines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The technology required to develop commercial gas turbine engines with reduced exhaust emissions was demonstrated. Can-annular combustor systems for the JT8D engine family (EPA class T4) were investigated. The JT8D turbofan engine is an axial-flow, dual-spool, moderate-bypass-ratio design. It has a two-stage fan, a four-stage low-pressure compressor driven by a three-stage low-pressure turbine, and a seven-stage high-pressure compressor driven by a single-stage high-pressure turbine. A cross section of the JT8D-17 showing the mechanical configuration is given. Key specifications for this engine are listed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Aircraft Eng. Emissions; p 29-89
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  • 29
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    Blade fragment energy analysis (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Two classes of fan blade fragments were considered in an analysis of blade fragment energy. The first, of relatively small size (.15 pound) and energy, tends to rebound from the fan and case when liberated in an FOD encounter. These small fragments have relatively low secondary damage potential and are less demanding in terms of protection. The larger fan blade fragments are ejected in a more direct release trajectory with higher energy and hence can represent a higher potential hazard. Simplified analytical methods were used to describe blade fragment energy transfer kinematics, establish fragment energy levels, evaluate damage potential and configure protection. The approach, methodology, and application are discussed as a possible building block for other applications. Development of effective local protection using Kevlar is also discussed. Analysis methods developed and applied to the rebound fragment problem and to the large direct release fragment problem are described.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 93-95
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  • 30
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    Development of fiber shields for engine containment (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Tests were conducted in translational launchers and spin pits to generate empirical data used in the design of a Kevlar shield for containing engine burst debris. Methods are given for modeling the relationship of fragment characteristics to shielding requirements. The change in relative importance of shield mounting provisions as fragment energy is increased is discussed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 217-234
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  • 31
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    Types of rotor failure and characteristics of fragments (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Noncontained rotor failures in U.K. engines resulting from low cycle fatigue, low cycle fatigue with superimposed high cycle fatigue, and overheating and-or overspeeding were analyzed. The size, shape, weight, velocity, energy, and direction of the fragments released from turbines and compressors were studied and are presented in graph.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 65-92
    Format: application/pdf
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  • 32
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    Designing the L-1011 to minimize rotor failures effects (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Design philosophies used in the L-1011 aircraft to provide protection against rotor fragments include: (1) incorporating into the rotor design features that tend to promote small fragments if failure occurs; (2) containing the fragments within the engine shell or greatly reducing the energy content of those fragments that are eventually uncontained; (3) shielding vulnerable elements or systems with heavy structural members that tend to stop or deflect high velocity fragments; and (4) incorporating redundant and/or backup systems into the basic design and separating these systems so as to minimize the probability that more than one system will be damaged by an uncontained rotor fragment. Some of the design features that were incorporated into the Rolls-Royce RB211 engine are discussed, and two in-service experiences are considered in order to illustrate the practical operation of these features.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 97-100
    Format: application/pdf
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  • 33
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    Status of the NASA/General Electric experimental clean combustor program, phase 3 (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The technology required to design and develop advanced commercial, conventional-takeoff-and-landing aircraft engines with significantly lower pollutant exhaust emissions levels than those of current-technology engines was generated and demonstrated. The target pollutant emissions reductions in tests of an advanced commercial aircraft turbofan engine were attained by developing advanced combustor designs. This technology is intended to be applicable to advanced military aircraft engines. The primary focus was on reducing the levels of the gaseous pollutant emissions.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 37-58
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  • 34
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    Environmental protection agency aircraft emissions standards (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Emissions of air pollutants from aircraft were investigated in order to determine: (1) the extent to which such emissions affect air quality in air quality control regions throughout the United States; and (2) the technological feasibility of controlling such emissions. The basic information supporting the need for aircraft emissions standards is summarized. The EPA ambient air quality standards are presented. Only the primary (health related) standards are shown. Of the six pollutants, only the first three, carbon monoxide (CO), hydrocarbons (HC), and nitrogen oxides, are influenced significantly by aircraft.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA. Lewis Res. Center Aircraft Eng. Emissions; p 1-17
    Format: application/pdf
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  • 35
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    Some airline experience in preventing engine rotor failures (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Methods used by airlines, with the assistance of the engine manufacturers to achieve control over the type of problems which lead to uncontained failure and avoid many potential problems are discussed.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 413-418
    Format: application/pdf
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  • 36
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    Application of a flight-line disk crack detector to a small engine (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: A disk crack detector was developed and applied to a small military engine for use as a flight-line turbine crack monitor. The system consists of an eddy current type sensor and its cables within the engine, external connecting cables, and a remotely located electrical capacitance-conductance bridge and signal analyzer. As the turbine spins, the rotor is monitored by the sensor for radial surface cracks emanating from the interblade region of the rotor.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures 383-388 (SEE N78-10068 01-07)
    Format: application/pdf
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  • 37
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    NDE: A key to engine rotor life prediction (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: A key ingredient in the establishment of safe life times for critical components is the means of reliably detecting flaws which may potentially exist. Currently used nondestructive evaluation procedures are successful in detecting life limiting defects; however, the development of automated and computer aided NDE technology permits even greater assurance of flight safety.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 369-382
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  • 38
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    Design of rotors for improved structural life (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Major rotor design criteria are discussed with particular emphasis on those aspects of rotor design that ensure long life component integrity. Dynamic considerations, that necessitate tuning of bladed disk and seal assemblies to avoid excessive vibratory stress at both design and off-design conditions are reviewed as well as low cycle fatigue considerations, which have resulted in detailed analysis procedures to establish part temperature and stress variation throughout an operating cycle and extensive specimen and component fatigue testing to establish safe cyclic operating limits. The frequency, size, and behavior of intrinsic material defects were investigated. Manufacturing process improvements, including the application of increasingly sophisticated inspection techniques and quality control procedures are reviewed in light of their impact on component durability.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 331-346
    Format: application/pdf
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  • 39
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    Concepts for the development of light-weight composite structures for rotor burst containment (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Published results on rotor burst containment with single materials, and on body armor using composite materials were used to establish a set of hypotheses about what variables might control the design of a weight-efficient protective device. Based on modern concepts for the design and analysis of small optimum seeking experiments, a particular experiment for evaluating the hypotheses and materials was designed. The design and methods for the analysis of results are described. The consequence of such hypotheses is that the device should consist of as many as four concentric rings, each to consist of a material uniquely chosen for its position in the penetration sequence.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 295-330
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  • 40
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    Engine non-containment: UK risk assessment methods (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: More realistic guideline data must be developed for use in aircraft design in order to comply with recent changes in British civil airworthiness requirements. Unrealistically pessimistic results were obtained when the methodology developed during the Concorde SST certification program was extended to assess catastrophic risks resulting from uncontained engine rotors.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 45-63
    Format: application/pdf
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  • 41
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    Federal Aviation Administration's approach to engine rotor integrity (1977)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Sections of the U.S. Airworthiness Standards which contribute to rotor integrity are explored. Reports published under NASA's Rotor Burst Protection program are included in current FAA studies to determine the weight penalty for two different levels of increased containment, and the penalty associated with protecting critical structure and systems, the passenger cabin, and the flight deck by strategic location of armor shields or deflector plates. Findings of the two studies will be used to propose revisions to regulations to reduce uncontained rotor failures.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: MIT An Assessment of Technol. for Turbojet Engine Rotor Failures; p 1-9
    Format: application/pdf
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  • 42
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    Quiet Clean Short-haul Experimental Engine (QCSEE) under-the-wing engine composite fan blade design report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A total of 38 quiet clean short haul experimental engine under the wing composite fan blades were manufactured for various component tests, process and tooling, checkout, and use in the QCSEE UTW engine. The component tests included frequency characterization, strain distribution, bench fatigue, platform static load, whirligig high cycle fatigue, whirligig low cycle fatigue, whirligig strain distribution, and whirligig over-speed. All tests were successfully completed. All blades planned for use in the engine were subjected to and passed a whirligig proof spin test.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135046 , R77AEG177
    Format: application/pdf
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  • 43
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    Quiet Clean Short-haul Experimental Engine (QCSEE) main reduction gears detailed design report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Lightweight turbine engines with geared slower speed fans are considered. The design of two similar but different gear ratio, minimum weight, epicyclic star configuration main reduction gears for the under the wing (UTW) and over the wing (OTW) engines is discussed. The UTW engine reduction gear has a ratio of 2.465:1 and a 100% power design rating of 9885 kW (13,256 hp) at 3143 rpm fan speed. The OTW engine reduction gear has a ratio of 2.062:1 and a 100% power design rating of 12813 kW (17183 hp) at 3861 rpm fan speed. Details of configuration, stresses, deflections, and lubrication are presented.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134872 , CW-WR-77-024
    Format: application/pdf
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  • 44
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    Quiet Clean Short-haul Experimental Engine (QCSEE) main reduction gears test program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Sets of under the wing (UTW) engine reduction gears and sets of over the wing (OTW) engine reduction gears were fabricated for rig testing and subsequent installation in engines. The UTW engine reduction gears which have a ratio of 2.465:1 and a design rating of 9712 kW at 3157 rpm fan speed were operated at up to 105% speed at 60% torque and 100% speed at 125% torque. The OTW engine reduction gears which have a ratio of 2.062:1 and a design rating of 12,615 kW at 3861 rpm fan speed were operated at up to 95% speed at 50% torque and 80% speed at 109% torque. Satisfactory operation was demonstrated at powers up to 12,172 kW, mechanical efficiency up to 99.1% UTW, and a maximum gear pitch line velocity of 112 m/s (22,300 fpm) with a corresponding star gear spherical roller bearing DN of 850,00 OTW. Oil and star gear bearing temperatures, oil churning, heat rejection, and vibratory characteristics were acceptable for engine installation.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134669 , CW-WR-77-008
    Format: application/pdf
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  • 45
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    Acoustic analysis of aft noise reduction techniques measured on a subsonic tip speed 50.8 cm (twenty inch) diameter fan (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Sound data which were obtained during tests of a 50.8 cm diameter, subsonic tip speed, low pressure ratio fan were analyzed. The test matrix was divided into two major investigations: (1) source noise reduction techniques; and (2) aft duct noise reduction with acoustic treatment. Source noise reduction techniques were investigated which include minimizing second harmonic noise by varying vane/blade ratio, variation in spacing, and lowering the Mach number through the vane row to lower fan broadband noise. Treatment in the aft duct which includes flow noise effects, faceplate porosity, rotor OGV treatment, slant cell treatment, and splitter simulation with variable depth on the outer wall and constant thickness treatment on the inner wall was investigated. Variable boundary conditions such as variation in treatment panel thickness and orientation, and mixed porosity combined with variable thickness were examined. Significant results are reported.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134891 , R75AEG368
    Format: application/pdf
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  • 46
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    Quiet Clean Short-haul Experimental Engine (QCSEE) Over The Wing (OTW) design report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The design, fabrication, and testing of two experimental high bypass geared turbofan engines and propulsion systems for short haul passenger aircraft are described. The propulsion technology required for future externally blown flap aircraft with engines located both under the wing and over the wing is demonstrated. Composite structures and digital engine controls are among the topics included.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134848 , R75AEG443
    Format: application/pdf
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  • 47
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    Quiet Clean Short-haul Experimental Engine (QCSEE): The aerodynamic and mechanical design of the QCSEE under-the-wing fan (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The design, fabrication, and testing of two experimental high bypass geared turbofan engines and propulsion systems for short haul passenger aircraft are described. The aerodynamic and mechanical design of a variable pitch 1.34 pressure ratio fan for the under the wing (UTW) engine are included. The UTW fan was designed to permit rotation of the 18 composite fan blades into the reverse thrust mode of operation through both flat pitch and stall pitch directions.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135009 , R75AEG484
    Format: application/pdf
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  • 48
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    Quiet Clean Short-haul Experimental Engine (QCSEE) Under-The-Wing (UTW) composite nacelle subsystem test report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The element and subcomponent testing conducted to verify the under the wing composite nacelle design is reported. This composite nacelle consists of an inlet, outer cowl doors, inner cowl doors, and a variable fan nozzle. The element tests provided the mechanical properties used in the nacelle design. The subcomponent tests verified that the critical panel and joint areas of the nacelle had adequate structural integrity.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135075 , R76AEG420
    Format: application/pdf
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  • 49
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    Quiet Clean Short-haul Experimental Engine (QCSEE) Over-The-Wing (OTW) boilerplate nacelle design report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A summary of the mechanical design of the boiler plate nacelle for the QCSEE over the wing (OTW) engine is presented. The nacelle, which features a D-shaped nozzle/thrust reverser and interchangeable hard wall and acoustic panels, is utilized in the engine testing to establish the aerodynamic and acoustic requirements for nozzles and reversers of this type.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135168 , R77AEG300
    Format: application/pdf
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  • 50
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Under-The-Wing (UTW) engine boilerplate nacelle test report, volume 1 (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The design and testing of high bypass geared turbofan engines with nacelles forming the propulsion systems for short haul passenger aircraft are considered. The test results demonstrate the technology required for externally blown flap aircraft for introduction into passenger service in the 1980's. The equipment tested is described along with the test facility and instrumentation. A chronological history of the test and a summary of results are given.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135249 , R77AEG2121-VOL-1
    Format: application/pdf
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  • 51
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Aerodynamic and aeromechanical performance of a 50.8 cm (20 inch) diameter 1.34 PR variable pitch fan with core flow (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The fan aerodynamic and aeromechanical performance tests of the quiet clean short haul experimental engine under the wing fan and inlet with a simulated core flow are described. Overall forward mode fan performance is presented at each rotor pitch angle setting with conventional flow pressure ratio efficiency fan maps, distinguishing the performance characteristics of the fan bypass and fan core regions. Effects of off design bypass ratio, hybrid inlet geometry, and tip radial inlet distortion on fan performance are determined. The nonaxisymmetric bypass OGV and pylon configuration is assessed relative to both total pressure loss and induced circumferential flow distortion. Reverse mode performance, obtained by resetting the rotor blades through both the stall pitch and flat pitch directions, is discussed in terms of the conventional flow pressure ratio relationship and its implications upon achievable reverse thrust. Core performance in reverse mode operation is presented in terms of overall recovery levels and radial profiles existing at the simulated core inlet plane. Observations of the starting phenomena associated with the initiation of stable rotor flow during acceleration in the reverse mode are briefly discussed. Aeromechanical response characteristics of the fan blades are presented as a separate appendix, along with a description of the vehicle instrumentation and method of data reduction.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135017 , R75AEG445
    Format: application/pdf
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  • 52
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Composite fan frame subsystem test report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The element and subcomponent testing conducted to verify the composite fan frame design of two experimental high bypass geared turbofan engines and propulsion systems for short haul passenger aircraft is described. Emphasis is placed on the propulsion technology required for future externally blown flap aircraft with engines located both under the wing and over the wing, including technology in composite structures and digital engine controls. The element tests confirmed that the processes used in the frame design would produce the predicted mechanical properties. The subcomponent tests verified that the detail structural components of the frame had adequate structural integrity.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135010 , R76AEG233
    Format: application/pdf
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  • 53
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    Quiet Clean Short-haul Experimental Engine (QCSEE) over-the-wing control system design report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A control system incorporating a digital electronic control was designed for the over-the-wing engine. The digital electronic control serves as the primary controlling element for engine fuel flow and core compressor stator position. It also includes data monitoring capability, a unique failure indication and corrective action feature, and optional provisions for operating with a new type of servovalve designed to operate in response to a digital-type signal and to fail with its output device hydraulically locked into position.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135337 , R77AEG664
    Format: application/pdf
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  • 54
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Core engine noise measurements (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Noise measurements were taken on a turbofan engine which uses the same core, with minor modifications, employed on the quiet clean short-haul experimental engine (QCSEE) propulsion systems. Both nearfield and farfield noise measurements were taken in order to determine the core internally generated noise levels. The resulting noise measurements were compared to predicted combustor and turbine noise levels, to verify or improve the predicted QCSEE combustor and turbine noise levels.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135160 , R75AEG511
    Format: application/pdf
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  • 55
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    Quiet Clean Short-haul Experimental Engine (QCSEE). Under-The-Wing (UTW) engine boilerplate nacelle test report. Volume 3: Mechanical performance (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Results of initial tests of the under the wing experimental engine and boilerplate nacelle are presented. The mechanical performance of the engine is reported with emphasis on the advanced technology components. Technology elements of the propulsion system covered include: system dynamics, composite fan blades, reduction gear, lube and accessory drive system, fan frame, inlet, core cowl cooling, fan exhaust nozzle, and digital control system.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135251 , R77AEG212-VOL-3
    Format: application/pdf
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  • 56
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    Quiet Clean Short-haul Experimental Engine (QCSEE) preliminary over-the-wing flight propulsion system analysis report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The preliminary design of the over-the-wing flight propulsion system installation and nacelle component and systems design features of a short-haul, powered lift aircraft are presented. Economic studies are also presented and show that high bypass, low pressure ratio turbofan engines have the potential of providing an economical propulsion system for achieving the very quiet aircraft noise level of 95 EPNdB on a 152.4 m sideline.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135296 , R77AEG305
    Format: application/pdf
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  • 57
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    Quiet Clean Short-haul Experimental Engine (QCSEE) under-the-wing engine simulation report (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Hybrid computer simulations of the under-the-wing engine were constructed to develop the dynamic design of the controls. The engine and control system includes a variable pitch fan and a digital electronic control. Simulation results for throttle bursts from 62 to 100 percent net thrust predict that the engine will accelerate 62 to 95 percent net thrust in one second.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134914 , R75AEG444
    Format: application/pdf
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  • 58
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    Quiet Clean Short-Haul Experimental Engine (QCSEE). Under-the-wing (UTW) engine boilerplate Nacelle test report. Volume 2: Aerodynamics and performance (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The initial phase of testing of the under the wing engine and boilerplate nacelle components is discussed. The aerodynamics and performance are outlined.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135250 , R77AEG2122-VOL-2
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  • 59
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    Method of fan sound mode structure determination computer program user's manual: Modal calculation program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computer user's manual describing the operation and the essential features of the Modal Calculation Program is presented. The modal Calculation Program calculates the amplitude and phase of modal structures by means of acoustic pressure measurements obtained from microphones placed at selected locations within the fan inlet duct. In addition, the Modal Calculation Program also calculates the first-order errors in the modal coefficients that are due to tolerances in microphone location coordinates and inaccuracies in the acoustic pressure measurements.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135295 , PWA-5554-5
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  • 60
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    Method of fan sound mode structure determination computer program user's manual: Microphone location program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computer user's manual describing the operation and the essential features of the microphone location program is presented. The Microphone Location Program determines microphone locations that ensure accurate and stable results from the equation system used to calculate modal structures. As part of the computational procedure for the Microphone Location Program, a first-order measure of the stability of the equation system was indicated by a matrix 'conditioning' number.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135294 , PWA-5554-4
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  • 61
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    Method of fan sound mode structure determination (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A method for the determination of fan sound mode structure in the Inlet of turbofan engines using in-duct acoustic pressure measurements is presented. The method is based on the simultaneous solution of a set of equations whose unknowns are modal amplitude and phase. A computer program for the solution of the equation set was developed. An additional computer program was developed which calculates microphone locations the use of which results in an equation set that does not give rise to numerical instabilities. In addition to the development of a method for determination of coherent modal structure, experimental and analytical approaches are developed for the determination of the amplitude frequency spectrum of randomly generated sound models for use in narrow annulus ducts. Two approaches are defined: one based on the use of cross-spectral techniques and the other based on the use of an array of microphones.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135293 , PWA-5554-3
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  • 62
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    Optimization study for high speed radial turbine with special reference to design variables (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Numerical results of a theoretical investigation are presented to provide information about the effect of variation of the different design and operating parameters on radial inflow turbine performance. The effects of variations in the mass flow rate, rotor tip Mach number, inlet flow angles, number of rotor blades and hub to shroud radius ratio, on the internal fluid dynamics of turbine rotors, was investigated. A procedure to estimate the flow deviation angles at the turbine exit is also presented and used to examine the influence of the operating conditions and the rotor geometrical configuration on these deviations. The significance of the results obtained is discussed with respect to improved turbine performance.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-152094
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  • 63
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    An analysis of the rotor blade stresses of the three stage compressor of the Ames Research Center 11- by 11-foot transonic wind tunnel (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The static and dynamic rotor blade stresses of the three stage compressor were measured. Data are presented in terms of total blade stress for the complete operational range of compressor speeds and tunnel total pressures. Modal frequencies and variations with tunnel conditions were measured. Phase angles and coherences between various gage combinations are also presented. Recommendations for improvements are given for future rotor blade experimental investigations.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-152083
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  • 64
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    Experimental clean combustor program: Turbulence characteristics of compressor discharge flows (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The results of turbulence measurements at the entrance to the diffuser duct of a large gas turbine are presented. Hot film and hot wire measurements were conducted over a compressor discharge temperature range of 450K to 608K. It was found that the turbulent intensity at the I.D. and midspan locations increases gradually from 6 + or - 1 percent at idle to 7 + or - 1 percent at approach; the turbulent intensity at the O.D. location increases from 7.5 + or - 0.5 percent at idle to 15 + or - 0.5 percent at approach. The energy in the velocity waves is uniformly distributed over a 0.1 to 5 kHz bandwidth, and the cut-off frequency is not a strong function of the engine operation. The axial length of the Fourier components within this bandwidth varies from 0.021 to 1.05m. The turbulence near the diffuser O.D. is of sufficient amplitude and scale to affect the flow to the front end sections of the burner.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135277 , PWA-5540
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  • 65
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    Computer Program for Calculation of a Gas Temperature Profile by Infrared Emission: Absorption Spectroscopy (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computer program to calculate the temperature profile of a flame or hot gas was presented in detail. Emphasis was on profiles found in jet engine or rocket engine exhaust streams containing H2O or CO2 radiating gases. The temperature profile was assumed axisymmetric with an assumed functional form controlled by two variable parameters. The parameters were calculated using measurements of gas radiation at two wavelengths in the infrared. The program also gave some information on the pressure profile. A method of selection of wavelengths was given that is likely to lead to an accurate determination of the parameters. The program is written in FORTRAN IV language and runs in less than 60 seconds on a Univac 1100 computer.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TM-73848 , E-9436
    Format: application/pdf
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  • 66
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    Influence of oil-squeeze-film damping on steady-state response of flexible rotor operating to supercritical speeds (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Experimental data were obtained for the unbalance response of a flexible rotor to speeds above the third lateral bending critical. Squeeze-film damping coefficients calculated from measured data showed good agreement with short-journal-bearing approximations over a frequency range from 5000 to 31,000 cmp. Response of a rotor to varying amounts of unbalance was investigated. A very lightly damped rotor was compared with one where oil-squeeze dampers were applied.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TP-1094 , E-9091
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  • 67
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    Mechanical characteristics of stability-bleed valves for a supersonic inlet (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Mechanical characteristics of a set of direct-operated relief valves used in a throat-bypass stability-bleed system designed for the YF-12 aircraft inlet are described. A comparison of data taken before and after the windtunnel tests (at room temperature) showed that both the effective spring rate and the piston friction had decreased during the wind tunnel tests. In neither the effective spring rate nor the piston friction was the magnitude of change great enough to cause significant impairment of overall system effectiveness. No major valve mechanical problems were encountered in any of the tests. During high temperature bench tests, piston frictional drag increased. The friction returned to its initial room temperature value when the stability-bleed valve was disassembled and reassembled. The problem might be solved by using a different material for the piston sleeve bearing and the piston rings.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TM-X-3483 , E-8852
    Format: application/pdf
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  • 68
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    High frequency dynamic engine simulation (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A digital computer simulation of a mixed flow, twin spool turbofan engine was assembled to evaluate and improve the dynamic characteristics of the engine simulation to disturbance frequencies of at least 100 Hz. One dimensional forms of the dynamic mass, momentum and energy equations were used to model the engine. A TF30 engine was simulated so that dynamic characteristics could be evaluated against results obtained from testing of the TF30 engine at the NASA Lewis Research Center. Dynamic characteristics of the engine simulation were improved by modifying the compression system model. Modifications to the compression system model were established by investigating the influence of size and number of finite dynamic elements. Based on the results of this program, high frequency engine simulations using finite dynamic elements can be assembled so that the engine dynamic configuration is optimum with respect to dynamic characteristics and computer execution time. Resizing of the compression systems finite elements improved the dynamic characteristics of the engine simulation but showed that additional refinements are required to obtain close agreement simulation and actual engine dynamic characteristics.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135313 , PWA-5543
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  • 69
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    Advanced supersonic propulsion study, phases 3 and 4 (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An evaluation of various advanced propulsion concepts for supersonic cruise aircraft resulted in the identification of the double-bypass variable cycle engine as the most promising concept. This engine design utilizes special variable geometry components and an annular exhaust nozzle to provide high take-off thrust and low jet noise. The engine also provides good performance at both supersonic cruise and subsonic cruise. Emission characteristics are excellent. The advanced technology double-bypass variable cycle engine offers an improvement in aircraft range performance relative to earlier supersonic jet engine designs and yet at a lower level of engine noise. Research and technology programs required in certain design areas for this engine concept to realize its potential benefits include refined parametric analysis of selected variable cycle engines, screening of additional unconventional concepts, and engine preliminary design studies. Required critical technology programs are summarized.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135236 , R77AEG635
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  • 70
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    Augmentor emissions reduction technology program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Technology to reduce pollutant emissions from duct-burner-type augmentors for use on advanced supersonic cruise aircraft was investigated. Test configurations, representing variations of two duct-burner design concepts, were tested in a rectangular sector rig at inlet temperature and pressure conditions corresponding to takeoff, transonic climb, and supersonic cruise flight conditions. Both design concepts used piloted flameholders to stabilize combustion of lean, premixed fuel/air mixtures. The concepts differed in the flameholder type used. High combustion efficiency (97%) and low levels of emissions (1.19 g/kg fuel) were achieved. The detailed measurements suggested the direction that future development efforts should take to obtain further reductions in emission levels and associated improvements in combustion efficiency over an increased range of temperature rise conditions.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135215 , R77AEG593
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  • 71
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    Effect of fuel properties on performance of single aircraft turbojet combustor at simulated idle, cruise, and takeoff conditions (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The performance of a single-can JT8D combustor was investigated with a number of fuels exhibiting wide variations in chemical composition and volatility. Performance parameters investigated were combustion efficiency, emissions of CO, unburned hydrocarbons and nitrogen oxides, as well as liner temperatures and smoke. The most pronounced effects of changes in fuel composition were observed at simulated cruise and takeoff conditions where smoke and liner temperatures increased significantly as the hydrogen content of the fuel decreased. At the simulated idle condition, emissions of CO and unburned hydrocarbons increased slightly and, accordingly, combustion efficiencies decreased slightly as the hydrogen content of the fuels decreased.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TM-73780 , E-9336
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  • 72
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    ENGINEL: A single rotor turbojet engine cycle match performance program (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: ENGINEL is a computer program which was developed to generate the design and off-design performance of a single rotor turbojet engine with or without afterburning using a cycle match procedure. It is capable of producing engine performance over a wide range of altitudes and Mach numbers. The flexibility, of operating with a variable geometry turbine, for improved off-design fuel consumption or with a fixed geometry turbine as in conventional turbojets, has been incorporated. In addition, the option of generation engine performance with JP4, liquid hydrogen or methane as fuel is provided.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-145267
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  • 73
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    Evaluation of a low aspect ratio small axial compressor stage, volume 2 (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N78-12081.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135241 , PWA-FR-8499-VOL-2
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  • 74
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    Cost/benefit analysis of advanced material technologies for small aircraft turbine engines (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Cost/benefit studies were conducted on ten advanced material technologies applicable to small aircraft gas turbine engines to be produced in the 1985 time frame. The cost/benefit studies were applied to a two engine, business-type jet aircraft in the 6800- to 9100-Kg (15,000- to 20,000-lb) gross weight class. The new material technologies are intended to provide improvements in the areas of high-pressure turbine rotor components, high-pressure turbine rotor components, high-pressure turbine stator airfoils, and static structural components. The cost/benefit of each technology is presented in terms of relative value, which is defined as a change in life cycle cost times probability of success divided by development cost. Technologies showing the most promising cost/benefits based on relative value are uncooled single crystal MAR-M 247 turbine blades, cooled DS MAR-M 247 turbine blades, and cooled ODS 'M'CrAl laminate turbine stator vanes.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135265 , AIRESEARCH-21-2391 , RADC-TR-77-216
    Format: application/pdf
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  • 75
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    Evaluation of a low aspect ratio small axial compressor stage, volume 1 (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A program was conducted to evaluate the effects of scaling, tip clearance, and IGV reset on the performance of a low aspect ratio compressor stage. Stage design was obtained by scaling an existing single stage compressor by a linear factor of 0.304. The design objective was to maintain the meanline velocity field of the base machine in the smaller size. Adjustments were made to account for predicted blockage differences and to chord lengths and airfoil edge radii to obtain reasonable blade geometries. Meanline velocity diagrams of the base stage were not maintained at the scaled size. At design speed and flowrate the scaled stage achieved a pressure ratio of 1.423, adiabatic efficiency of 0.822, and surge margin of 18.5%. The corresponding performance parameters for the base stage were 1.480, 0.872, and 25.2%, respectively. The base stage demonstrated a peak efficiency at design speed of 0.872; the scaled stage achieved a level of 0.838. When the scaled stage rotor and stator tip clearances were doubled, the stage achieved a pressure ratio of 1.413, efficiency of 0.799, and surge margin of 16.0% at the design flowrate. The peak stage efficiency at design speed was 0.825 with the increased clearance. Increased prewhirl lowered the stage pressure ratio as expected. Stage efficiency was maintained with ten degrees of increased prewhirl and then decreased substantially with ten additional degrees of reset.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135240 , PWA-FR-8499-VOL-1
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  • 76
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    Altitude test of several afterburner configurations on a turbofan engine with a hydrogen heater to simulate an elevated turbine discharge temperature (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A performance test of several experimental afterburner configurations was conducted with a mixed-flow turbofan engine in an altitude facility. The simulated flight conditions were for Mach 1.4 at two altitudes, 12,190 and 14,630 meters. Turbine discharge temperatures of 889 and 1056 K were used. A production afterburner was tested for comparison. The research afterburners included partial forced mixers with V-gutter flameholders, a carburetted V-gutter flameholder, and a triple ring V-gutter flameholder with four swirl-can fuel mixers. Fuel injection variations were included. Performance data shown include augmented thrust ratio, thrust specific fuel consumption, combustion efficiency, and total pressure drop across the afterburner.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TP-1068 , E-9207
    Format: application/pdf
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  • 77
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    Effect of forward motion on engine noise (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Methods used to determine a procedure for correcting static engine data for the effects of forward motion are described. Data were analyzed from airplane flyover and static-engine tests with a JT8D-109 low-bypass-ratio turbofan engine installed on a DC-9-30, with a CF6-6D high-bypass-ratio turbofan engine installed on a DC-10-10, and with a JT9D-59A high-bypass-ratio turbofan engine installed on a DC-10-40. The observed differences between the static and the flyover data bases are discussed in terms of noise generation, convective amplification, atmospheric propagation, and engine installation. The results indicate that each noise source must be adjusted separately for forward-motion and installation effects and then projected to flight conditions as a function of source-path angle, directivity angle, and acoustic range relative to the microphones on the ground.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134954 , MDC-J7708
    Format: application/pdf
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  • 78
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    Integrated gas turbine engine-nacelle (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A nacelle for use with a gas turbine engine is presented. An integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine, provides lightweight support. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a streamlined envelope for the engine.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
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  • 79
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    JT9D engine diagnostics. Task 2: Feasibility study of measuring in-service flight loads (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The feasibility of measuring JT9D propulsion system flight inertia loads on a 747 airplane is studied. Flight loads background is discussed including the current status of 747/JT9D loads knowledge. An instrumentation and test plan is formulated for an airline-owned in-service airplane and the Boeing-owned RA001 test airplane. Technical and cost comparisons are made between these two options. An overall technical feasibility evaluation is made and a cost summary presented. Conclusions and recommendations are presented in regard to using existing inertia loads data versus conducting a flight test to measure inertia loads.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135395 , D6-44664
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  • 80
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    Analysis of the cross flow in a radial inflow turbine scroll (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Equations of motion were derived, and a computational procedure is presented, for determining the nonviscous flow characteristics in the cross-sectional planes of a curved channel due to continuous mass discharge or mass addition. An analysis was applied to the radial inflow turbine scroll to study the effects of scroll geometry and the through flow velocity profile on the flow behavior. The computed flow velocity component in the scroll cross-sectional plane, together with the through flow velocity profile which can be determined in a separate analysis, provide a complete description of the three dimensional flow in the scroll.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135320
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  • 81
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    Evaluation of Federal Aviation Administration ion engine exhaust sampling rake (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A FAA exhaust emissions rake was tested in the Experimental Clean Combustor Program, Phase 3 to permit comparison of the values of gaseous emissions and smoke measured by the FAA rake with those measured with the NASA Pratt and Whitney Aircraft (P and WA) rake used in the Phase 3 Experimental Clean Combustor Program and with station seven probes. The results showed that the levels of CO, THC, NOx and smoke measured by the FAA and NASA/P and WA rakes agree well at high power, but that CO emissions measured by the FAA rake were approximately 10 percent higher than those measured by the NASA/P and WA rake at low power.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-135213 , PWA-5534 , FAA-RD-77-115 , AD-A133422
    Format: application/pdf
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  • 82
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    Review of problems in application of supersonic combustion (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The problem of air-breathing engines capable of flying at very high Mach numbers is described briefly. Possible performance of supersonic combustion ramjets is outlined briefly and the supersonic combustion process is described. Two mechanisms of combustion are outlined: one is supersonic combustion controlled by convection process, and the second is controlled by diffusion. The parameters related to the combustion process are discussed in detail. Data and analyses of reaction rates and mixing phenomena are represented; the flame mechanism is discussed, and experimental results are presented.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Selected Papers on Advanced Design of Air Vehicles; p 13-30
    Format: text
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  • 83
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    Analysis of simple 2-D and 3-D metal structures subjected to fragment impact (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Theoretical methods were developed for predicting the large-deflection elastic-plastic transient structural responses of metal containment or deflector (C/D) structures to cope with rotor burst fragment impact attack. For two-dimensional C/D structures both, finite element and finite difference analysis methods were employed to analyze structural response produced by either prescribed transient loads or fragment impact. For the latter category, two time-wise step-by-step analysis procedures were devised to predict the structural responses resulting from a succession of fragment impacts: the collision force method (CFM) which utilizes an approximate prediction of the force applied to the attacked structure during fragment impact, and the collision imparted velocity method (CIVM) in which the impact-induced velocity increment acquired by a region of the impacted structure near the impact point is computed. The merits and limitations of these approaches are discussed. For the analysis of 3-d responses of C/D structures, only the CIVM approach was investigated.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Assessment of Technol. for Turbojet Engine Rotor Failures; p 151-215
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  • 84
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    Stalled and stall-free performance of axial-flow compressor stage with three inlet-guide-vane and stator-blade settings (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The performance of the first stage of a transonic, multistage compressor was mapped over a range of inlet-guide-vane and stator-blade settings. Both stall-free and deep-stall performance data were obtained. For the settings tested, as stall was encountered and flow was further reduced, a relatively sharp drop in pressure ratio occurred and was followed by a continuing but more gradual reduction in pressure ratio with reduced flow. The position of the stall line on the map of pressure ratio against equivalent weight flow was essentially unaffected over the range of inlet-guide-vane and stator-blade settings.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TN-D-8457 , E-8222
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  • 85
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    Single stage, low noise, advanced technology fan. Volume 4: Fan aerodynamics. Section 2: Overall and blade element performance data tabulations (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N77-17060.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134893 , R76AEG566-VOL-4
    Format: application/pdf
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  • 86
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    Single-stage, low-noise, advanced technology fan. Volume 4: Fan aerodynamics. Section 1: Results and analysis (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Test results at design speed show fan total pressure ratio, weight flow, and adiabatic efficiency to be 2.2, 2.9, and 1.8% lower than design goal values. The hybrid acoustic inlet (which utilizes a high throat Mach number and acoustic wall treatment for noise suppression) demonstrated total pressure recoveries of 98.9% and 98.2% at takeoff and approach. Exhaust duct pressure losses differed between the hardwall duct and treated duct with splitter by about 0.6% to 2.0% in terms of fan exit average total pressure (depending on operating condition). When the measured results were used to estimate pressure losses, a cruise sfc penalty of 0.68%, due to the acoustically treated duct, was projected.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134892 , R76AEG565-VOL-4
    Format: application/pdf
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  • 87
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    Oil cooling system for a gas turbine engine (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess fuel control requirements back to the aircraft fuel tank. This increases the fuel pump heat sink and decreases the pump temperature rise without the addition of valving other than normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
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  • 88
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    Analysis of dynamic inlet distortion applied to a parallel compressor model (1977)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An investigation of surge was conducted by using a parallel compressor model of the J85-13 compressor implement on an analog computer. Surges were initiated by various types of dynamic disturbances in inlet pressure. The compressor model was less sensitive to disturbances of short duration, high frequency, and long duration where the compressor discharge pressure could react. Adding steady distortion to dynamic disturbances reduced the amount of dynamic disturbance required to effect surge. Steady and unsteady distortions combined linearly to reduce surge margin.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: NASA-TM-X-3522 , E-8979
    Format: application/pdf
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  • 89
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    A computationally fast one-dimensional diffusion-photochemistry model of SST wakes (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computational technique applicable to analysis of supersonic transport (SST) wake photochemistry and diffusion is presented. Sensitivity studies of SST effluent effects upon ozone depletion are facilitated by the computational rapidity of the method. The article compares results from other studies and predictions of some variables related to global NOx input. Results indicate that the NO/NO2 ratio in an SST wake at photochemical equilibrium is a sensitive function of photolysis rates.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: AIAA Journal; 15; Aug. 197
    Format: text
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  • 90
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    State-of-the-art of turbofan engine noise control (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A description is presented of some of the recent advances in the technology of turbofan engine noise reduction, taking into account turbomachinery noise sources, new fans for low noise, fan and core noise suppression, and a new program for improving static noise testing of fans and engines. The problem of jet noise has been substantially reduced in connection with the lower jet velocities employed in the case of the high bypass turbofan engines. The dominant noise sources are now related to the turbomachinery with the fan stage, the compressor, and the turbine. Since the fan stage is the primary source of turbomachinery noise, it has been considered in a major part of the investigations designed to reduce turbofan engine noise.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: In: NOISE-CON 77; National Conference on Noise Control Engineering; Oct 17, 1977 - Oct 19, 1977; Hampton, VA
    Format: text
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  • 91
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    Effect of airstream velocity on mean drop diameters of water sprays produced by pressure and air atomizing nozzles (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A scanning radiometer was used to determine the effect of airstream velocity on the mean drop diameter of water sprays produced by pressure atomizing and air atomizing fuel nozzles used in previous combustion studies. Increasing airstream velocity from 23 to 53.4 meters per second reduced the Sauter mean diameter by approximately 50 percent with both types of fuel nozzles. The use of a sonic cup attached to the tip of an air assist nozzle reduced the Sauter mean diameter by approximately 40 percent. Test conditions included airstream velocities of 23 to 53.4 meters per second at 293 K and atmospheric pressure.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Winter Annual Meeting; Nov 27, 1977 - Dec 02, 1977; Atlanta, GA
    Format: text
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  • 92
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    General aviation energy-conservation research programs at NASA-Lewis Research Center (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A review is presented of non-turbine general aviation engine programs underway at the NASA-Lewis Research Center in Cleveland, Ohio. The program encompasses conventional, lightweight diesel and rotary engines. Its three major thrusts are, in order of priority: (1) reduced SFCs; (2) improved fuels tolerance; and (3) reducing emissions. Current and planned future programs in such areas as lean operation, improved fuel management, advanced cooling techniques and advanced engine concepts, are described. These are expected to lay the technology base, by the mid to latter 1980s, for engines whose total fuel costs are as much as 30% lower than today's conventional engines.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Conference on Energy Conservation in General Aviation; Oct 10, 1977 - Oct 11, 1977; Kalamazoo, MI
    Format: text
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  • 93
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    Output feedback regulator design for jet engine control systems (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A multivariable control design procedure based on the output feedback regulator formulation is described and applied to an F100 turbofan engine model. Full order model dynamics, are incorporated in the example design. The effect of actuator dynamics on closed loop performance is investigated. Also, the importance of turbine inlet temperature as an element of the dynamic feedback is studied. Step responses are given to indicate the improvement in system performance with this control. Calculation times for all experiments are given in CPU seconds for comparison purposes.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: National Electronics Conference; Oct 13, 1977 - Oct 14, 1977; Chicago, IL
    Format: text
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  • 94
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    Effectiveness of an inlet flow turbulence control device to simulate flight fan noise in an anechoic chamber (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A hemispherical inlet flow control device was tested on a 50.8 cm. (20-inch) diameter fan stage in the NASA-Lewis Anechoic Chamber. The control device used honeycomb and wire mesh to reduce turbulence intensities entering the fan. Far field acoustic power level results showed about a 5 dB reduction in blade passing tone and about 10 dB reduction in multiple pure tone sound power at 90% design fan speed with the inlet device in place. Hot film cross probes were inserted in the inlet to obtain data for two components of the turbulence at 65 and 90% design fan speed. Without the flow control device the axial intensities were below 1.0%, while the circumferential intensities were almost twice this value. The inflow control device significantly reduced the circumferential turbulence intensities and also reduced the axial length scale.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
    Format: text
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  • 95
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    Combustor fluctuating pressure measurements in-engine and in a component test facility - A preliminary comparison (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Combustor internal fluctuating pressure and far-field noise generated in a YF-102 turbofan engine are investigated; combustor internal measurements are also made in a duct-component test facility operating over a range of conditions encompassing those characteristic of the aircraft engine. Although directly measured spectra for the engine and the duct-component test facility show discrepancies, the results of coherence function, transfer function and phase relationship comparisons suggest that the internal dynamics of the combustor as an acoustic source may be preserved in a component test facility.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
    Format: text
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  • 96
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    An empirical model for inverted-velocity-profile jet noise prediction (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: It is known that the noise generated by inverted-velocity-profile coaxial (without center plug) and coannular (with center plug) nozzles should be modeled as the combined contributions of various source regions and noise generation mechanisms. In this paper, an empirical noise-prediction model is described which considers the noise generated by two jet-mixing regions and two potential regions of shock/turbulence interaction. Results calculated from the empirical model are compared with model-scale experimental data for static and simulated flight conditions. These comparisons are made for cases where both streams are subsonic, where the outer stream is supersonic with the inner stream subsonic, and where both streams are supersonic. The cases considered cover a range of inner-to-outer-stream area ratios and include both coaxial and coannular nozzles. It is shown that the model gives reasonable predictions of absolute noise spectra and even better predictions of incremental changes.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
    Format: text
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  • 97
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    Noise of deflectors used for flow attachment with STOL-OTW configurations (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Future STOL aircraft may utilize engine-over-the-wing (OTW) installations in which the exhaust nozzles are located above and separated from the upper surface of the wing. An external jet-flow deflector can be used with such installations to provide flow attachment to the wing/flap surfaces for lift augmentation. In the present work, the deflector noise in the flyover plane measured with several model-scale nozzle/deflector/wing configurations is examined. The deflector-associated noise is correlated in terms of velocity and geometry parameters. The data also indicate that the effective overall sound pressure level of the deflector-associated noise peaks in the forward quadrant near 40 deg from the inlet axis.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Meeting of the Acoustical Society of America; Dec 13, 1977 - Dec 16, 1977; Miami Beach, FL
    Format: text
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  • 98
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    Failure detection and correction for turbofan engines (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: In this paper, a failure detection and correction strategy for turbofan engines is discussed. This strategy allows continuing control of the engines in the event of a sensor failure. An extended Kalman filter is used to provide the best estimate of the state of the engine based on currently available sensor outputs. Should a sensor failure occur the control is based on the best estimate rather than the sensor output. The extended Kalman filter consists of essentially two parts, a nonlinear model of the engine and up-date logic which causes the model to track the actual engine. Details on the model and up-date logic are presented. To allow implementation, approximations are made to the feedback gain matrix which result in a single feedback matrix which is suitable for use over the entire flight envelope. The effect of these approximations on stability and response is discussed. Results from a detailed nonlinear simulation indicate that good control can be maintained even under multiple failures.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA; US
    Format: text
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  • 99
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    Design of turbofan engine controls using output feedback regulator theory (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A multivariable control design procedure based on output feedback regulator (OFR) theory is applied to the F100 turbofan engine. Results for the OFR design are compared to a design based on linear quadratic regulator (LQR) theory. This LQR design was obtained as part of the F100 Multivariable Control Synthesis (MVCS) program. In the MVCS program the LQR feedback control was designed in a reduced dimension state space and then applied to the original system. However, the OFR feedback control is designed in the full order state space and thus eliminates any need for model reduction techniques. Using the performance measure and control structure of the MVCS program LQR design, an equivalent OFR feedback control is obtained. The flexibility of the OFR as a control design procedure is demonstrated and differing feedback control structures are evaluated.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
    Format: text
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  • 100
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    Optimal controls for an advanced turbofan engine (1977)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Linear optimal control theory is applied to the control synthesis of a high bypass ratio, variable pitch, turbofan engine. The basic control philosophy is to use only a low order dynamic model of the plant coupled with the concept of integral-output states so as to maintain control simplicity yet guarantee integral control of thrust, turbine temperature and other important engine outputs. Linear simulation results indicate that the control system developed provides rapid control of small thrust perturbations and quickly eliminates the effect of unmodelled thrust and temperature disturbances. Large thrust accelerations are obtained in about one half second while the control maintains negligible overshoot in temperature and stall margins.
    Schlagwort(e): AIRCRAFT PROPULSION AND POWER
    Materialart: Joint Automatic Control Conference; Jun 22, 1977 - Jun 24, 1977; San Francisco, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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