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  • Other Sources  (80)
  • AIRCRAFT PROPULSION AND POWER
  • Biochemistry and Biotechnology
  • General Chemistry
  • Landwirtschaft
  • 1970-1974  (63)
  • 1945-1949  (14)
  • 1915-1919
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Years
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  • 1
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    Investigation of the aerodynamic noise generating region of a jet engine by means of the simple source fluid dilatation model (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An experiment was conducted on a full-scale jet engine to investigate the aerodynamic noise generating regions in the free jet. Cross-correlation measurements were made between the static pressure fluctuations and the farfield radiated sound. These measurements were made for two different static pressure probe positions and a large number of farfield positions (at various angles). In addition, each test geometry was run for four different jet exit velocities. The measured, normalized cross-correlation functions varied between 0.004 and 0.155. A new Q-function, based on the above normalized cross correlation is defined and plotted. This function represents the source strength per unit volume within the jet region. This Q-function shows dependence on the probe position, the angular position of the farfield microphone, and the jet exit Mach number. Third-octave analyses of both the probe signal and the farfield radiated sound were made. The results show that cross-correlation techniques are a valuable tool in the investigation of the aerodynamic noise generating regions of an actual jet engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America; vol. 56
    Format: text
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  • 2
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    Preliminary Mach 6 aim test results. Hypersonic research engine project-phase 2 (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-163016
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  • 3
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    Quiet Clean Short-Haul Experimental Engine (QSCEE). Preliminary analyses and design report, volume 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental propulsion systems to be built and tested in the 'quiet, clean, short-haul experimental engine' program are presented. The flight propulsion systems are also presented. The following areas are discussed: acoustic design; emissions control; engine cycle and performance; fan aerodynamic design; variable-pitch actuation systems; fan rotor mechanical design; fan frame mechanical design; and reduction gear design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134838 , R74AEG479-VOL-1
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  • 4
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    Quiet Clean Short-Haul Experimental Engine (QCSEE). Preliminary analyses and design report, volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental and flight propulsion systems are presented. The following areas are discussed: engine core and low pressure turbine design; bearings and seals design; controls and accessories design; nacelle aerodynamic design; nacelle mechanical design; weight; and aircraft systems design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134839 , R74AEG479-VOL-2
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  • 5
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    The 727 airplane target thrust reverser static performance model test for refanned JT8D engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a scale model static performance test of target thrust reverser configurations for the Pratt and Whitney Aircraft JT8D-100 series engine are presented. The objective of the test was to select a series of suitable candidate reverser configurations for the subsequent airplane model wind tunnel ingestion and flight controls tests. Test results indicate that adequate reverse thrust performance with compatible engine airflow match is achievable for the selected configurations. Tapering of the lips results in loss of performance and only minimal flow directivity. Door pressure surveys were conducted on a selected number of lip and fence configurations to obtain data to support the design of the thrust reverser system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134652 , DG-41964
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  • 6
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    Acoustic and aerodynamic performance of a 1.83 meter (6 foot) diameter 1.2 pressure ratio fan (QF-6) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 1.2-pressure-ratio, 1.83-meter-(6-ft-) diameter experimental fan stage with characteristics suitable for use in STOL aircraft engines was tested for acoustic and aerodynamic performance. The design incorporated features for low noise, including absence of inlet guide vanes, low rotor-blade-tip speed, low aerodynamic blade loading, and long axial spacing between the rotor and stator rows. The stage was run with four nozzles of different area. The perceived noise along a 152.4 meter (500-ft) sideline was rear-quadrant dominated with a maximum design-point level of 103.9 PNdb. The acoustic 1/3-octave results were analytically separated into broadband and pure-tone components. It was found that the stage noise levels generally increase with a decrease in nozzle area, with this increase observed primarily in the broadband noise component. A stall condition was documented acoustically with a 90-percent-of-design-area nozzle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TN-D-7809 , E-7996
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  • 7
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    Aerodynamic performance of 0.5 meter-diameter, 337 meter-per-second tip speed, 1.5 pressure-ratio, single-stage fan designed for low noise aircraft engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Overall and blade-element aerodynamic performance of a 0.271-scale model of QF-1 are presented, examined, and then compared and evaluated with that from similar low noise fan stage designs. The tests cover a wide range of speeds and weight flows along with variations in stator setting angle and stator axial spacing from the rotor. At design speed with stator at design setting angle and a fixed distance between stage measuring stations, there were no significant effects of increasing the axial spacing between rotor stator from 1.0 to 3.5 rotor chords on stage overall pressure ratio, efficiency or stall margin.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TN-D-7836 , E-7779
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  • 8
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    Combustion generated noise in gas turbine combustors (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments were conducted to determine the noise power and spectra emitted from a gas turbine combustor can exhausting to the atmosphere. Limited hot wire measurements were made of the cold flow turbulence level and spectra within the can. The fuels used were JP-4, acetone and methyl alcohol burning with air at atmospheric pressure. The experimental results show that for a fixed fuel the noise output is dominated by the airflow rate and not the fuel/air ratio. The spectra are dominated by the spectra of the cold flow turbulence spectra which were invariant with airflow rate in the experiments. The effect of fuel type on the noise power output was primarily through the heat of combustion and not the reactivity. A theory of combustion noise based upon the flame radiating to open surroundings is able to reasonably explain the observed results. A thermoacoustic efficiency for noise radiation as high as .00003 was observed in this program for JP-4 fuel. Scaling rules are presented for installed configurations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134843
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  • 9
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    Engineering simulation evaluation of the two-segment noise abatement approach in the Douglas DC-8-61 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development and operational evaluation are discussed of a noise abatement two-segment approach which is safe and operationally acceptable for routine use in air carrier service. An engineering simulation evaluation was conducted; it was found that the entry speed and initial configuration are more important in the DC-8-61 than in the 727 because of the DC-8's aerodynamic cleanliness and drag programming constraints. It was also found that the altitude required for the DC-8 upper and lower transitions is less than the 727 transitions principally due to the pitching moment from the underslung DC-8 engines as compared to the 727 engines which produce no pitching moment with a change in thrust. The 727 approach was a reduced flaps (30 degrees) procedure with a 10-knot airspeed bleed in the lower transition; the DC-8 approach is a full flaps (50 degrees) procedure with constant airspeed established as soon as possible after upper segment transition.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-137665
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  • 10
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    Wind tunnel test of model target thrust reversers for the Pratt and Whitney aircraft JT8D-100 series engines installed on a 727-200 airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a low speed wind tunnel test of 0.046 scale model target thrust reversers installed on a 727-200 model airplane are presented. The full airplane model was mounted on a force balance, except for the nacelles and thrust reversers, which were independently mounted and isolated from it. The installation had the capability of simulating the inlet airflows and of supplying the correct proportions of primary and secondary air to the nozzles. The objectives of the test were to assess the compatibility of the thrust reversers target door design with the engine and airplane. The following measurements were made: hot gas ingestion at the nacelle inlets; model lift, drag, and pitching moment; hot gas impingement on the airplane structure; and qualitative assessment of the rudder effectiveness. The major parameters controlling hot gas ingestion were found to be thrust reverser orientation, engine power setting, and the lip height of the bottom thrust reverser doors on the side nacelles. The thrust reversers tended to increase the model lift, decrease the drag, and decrease the pitching moment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134709 , D6-41900
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  • 11
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    Theoretical studies on tone noise from a ducted fan rotor (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The method of computing radiated noise from a ducted rotor due to inflow distortion and turbulence are examined. Analytical investigations include an appropriate description of sources, the cut-off conditions imposed on the modal propagation of the pressure waves in the annular duct, and reflections at the upstream end of the duct. Far field sound pressure levels at blade passing frequency due to acoustic radiation from a small scale low speed fan are computed. Theoretical predictions are in reasonable agreement with experimental measurements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-137620
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  • 12
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    Modifications that improve performance of a double annular combustor at simulated engine idle conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques were evaluated to determine if simple combustor modifications could be used to reduce the engine ground idle emissions of a double annular combustor designed for Mach 3.0 cruise operation. These techniques were radial fuel staging, the use of radial-inflow rather than axial-flow air swirlers, and the optimization of fuel-nozzle spray angle and differential pressure. Radial fuel staging and the use of radial-inflow air swirlers significantly improved performance at two ground idle test conditions simulating both low- and high-compression ratio engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3127 , E-7960
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  • 13
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    The cost of noise reduction in commercial tilt rotor aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The relationship between direct operating cost (DOC) and departure noise annoyance was developed for commercial tilt rotor aircraft. This was accomplished by generating a series of tilt rotor aircraft designs to meet various noise goals at minimum DOC. These vehicles were spaced across the spectrum of possible noise levels from completely unconstrained to the quietest vehicle that could be designed within the study ground rules. A group of optimization parameters were varied to find the minimum DOC while other inputs were held constant and some external constraints were met. This basic variation was then extended to different aircraft sizes and technology time frames. It was concluded that reducing noise annoyance by designing for lower rotor tip speeds is a very promising avenue for future research and development. It appears that the cost of halving the annoyance compared to an unconstrained design is insignificant and the cost of halving the annoyance again is small.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-137552 , FTL-R74-5
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  • 14
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    Ordered structures and jet noise (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A series of measurements of near field pressures and turbulent velocity fluctuations were made in a jet having a Reynolds number of about 50,000 in order to investigate more quantitatively the character and behavior of the large scale structures, and to ascertain their importance to the jet noise problem. It was found that the process of interaction between vortices can be inhibited by artificially exciting the shear layers with periodic disturbances of certain frequency. The turbulent fluctuation amplitudes measured at four diameters downstream decreased considerably. Finally, it was observed that the passage frequency of the structures decreased with x in a similar manner as the frequency corresponding to the maximum intensity radiation emanating from the same value of x.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134733
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  • 15
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    Scramjet nozzle design and analysis as applied to a highly integrated hypersonic research airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The configuration and performance of the propulsion system for the hypersonic research vehicle are discussed. A study of the interactions between propulsion and aerodynamics of the highly integrated vehicle was conducted. The hypersonic research vehicle is configured to test the technology of structural and thermal protection systems concepts and the operation of the propulsion system under true flight conditions for most of the hypersonic flight regime. The subjects considered are: (1) research vehicle and scramjet engine configurations to determine fundamental engine sizing constraints, (2) analytical methods for computing airframe and propulsion system components, and (3) characteristics of a candidate nozzle to investigate vehicle stability and acceleration performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71972
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  • 16
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    Interim prediction method for low frequency core engine noise (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A literature survey on low-frequency core engine noise is presented. Possible sources of low frequency internally generated noise in core engines are discussed with emphasis on combustion and component scrubbing noise. An interim method is recommended for predicting low frequency core engine noise that is dominant when jet velocities are low. Suggestions are made for future research on low frequency core engine noise that will aid in improving the prediction method and help define possible additional internal noise sources.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71627 , E-8154
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  • 17
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    Performance of a model cascade thrust reverser for short-haul applications (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic and acoustic characteristics are presented for a cowl-mounted, model cascade thrust reverser suitable for short-haul aircraft. Thrust reverser efficiency and the influence on fan performance were determined from isolated fan-driven models under static and forward velocity conditions. Cascade reverser noise characteristics were determined statically in an isolated pipe-flow test, while aerodynamic installation effects were determined with a wind-tunnel, fan-powered airplane model. Application of test results to short-haul aircraft calculations demonstrate that such a cascade thrust reverser may be able to meet both the performance and noise requirements for short-haul aircraft operation. However, aircraft installation effects can be quite significant.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 74-1171 , American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference; Oct 21, 1974 - Oct 23, 1974; San Diego, CA
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  • 18
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    Potential and viscous flow prediction in V/STOL propulsion system inlets (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Highlights of the method of analysis of inlet flow are given. To indicate the accuracy of the method, several comparisons with experiments for different V/STOL inlet configurations and various operating conditions are given. Applications to inlet design and analysis are then discussed. A summary of current efforts is given, and areas of possible future work are indicated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71776 , E-8434 , Workshop on Prediction Methods for Jet V/STOL propulsion Aerodynamics; Jul 28, 1975 - Jul 31, 1975; Arlington, VA; United States
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  • 19
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    Influence of mixer nozzle velocity decay characteristics on CTOL-OTW jet noise shielding (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Jet noise shielding benefits for CTOL engine-over-the-wing configurations were obtained with model scale multitube and lobed mixer nozzles and various shielding surface geometries. Spectral data were obtained with jet velocities from 585 to 1110 ft/sec. Correlation equations for predicting jet noise shielding benefits with single conical nozzle installations were modified to correlate the mixer nozzle data. The modification included consideration of the number of nozzle elements and the peak axial velocity decay in the flow field adjacent to the shielding surface. The effect of forward velocity on jet noise attenuation by a shielding surface is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71631 , E-8168 , Aerospace Sci. Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA; United States
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  • 20
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    Effect of swirling flow on augmentor performance (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A test program was conducted with an augmentor which employed swirling flow as a means of promoting rapid flame propagation. The program evaluated the effect of augmentor length, swirl intensity, fuel zoning and Mach number on augmentor performance. Combustion efficiencies near 100% were demonstrated over most of the operating range which extended from an equivalence ratio of 0.2 to over 1.0. The tests were conducted at an inlet temperature of 649 C (1200 F) and at a pressure of 2 atmospheres. The augmentor total pressure losses were typical of current state of the art augmentors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134639 , FR-6534
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  • 21
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    Fluid dynamic aspects of jet noise generation (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The location of the noise sources within jet flows, their relative importance to the overall radiated field, and the mechanisms by which noise generation occurs, are studied by detailed measurements of the level and spectral composition of the radiated sound in the far field. Directional microphones are used to isolate the contribution to the radiated sound of small regions of the flow, and for cross-correlation between the radiated acoustic field and either the velocity fluctuations or the pressure fluctuations in the source field. Acquired data demonstrate the supersonic convection of the acoustic field and the resulting limited upstream influence of the signal source, as well as a possible increase of signal strength as it propagates toward the centerline of the flow.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-140673
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  • 22
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    Spinning mode sound propagation in ducts with acoustic treatment (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Recent acoustic data have shown larger noise attenuations than predicted for acoustically treated aircraft engine inlets without splitter rings. These data have stimulated a more detailed theoretical study of the acoustic propagation of spinning modes in acoustically treated open circular ducts. In addition, the suppressor with splitter rings was modeled by using the rectangular approximation to the annular duct. The theoretical models were used to determine optimum impedance and maximum attenuation for several spinning lobe numbers from 0 to 50. It is found that for circular ducts the maximum possible attenuation and the optimum wall impedance are strong functions of the lobe number. For annular ducts the attenuation and optimum wall impedance are insensitive to the spinning lobe number for well cut-on modes. The results help explain why suppressors with splitter rings have been quite effective in spite of the lack of detailed information on the noise-source modal structure. Conversely, effective use of outer-wall treatment alone will require expanded knowledge of the noise-source structure. Approximate solutions are presented to help interpret the more exact theoretical results.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America, Meeting; Nov 04, 1974 - Nov 08, 1974; St. Louis, MO
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  • 23
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    Test techniques for obtaining off-nominal compressor data during engine tests (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Several unique techniques and related devices are in use at the Lewis Research Center for off-design testing of fan and compressor sections in full-scale jet engines. The devices presented not only permit a wide range of experimental conditions but also minimize downtime for hardware changes. The techniques involve use of such devices as inlet pressure distortion jets, a hydrogen burner for inlet temperature distortions, fan back pressure jets to simulate a variable area nozzle, and either an inflow-outflow bleed system or a fuel spurt system to alter compressor discharge pressure.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 740822 , Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting; Oct 01, 1974 - Oct 03, 1974; San Diego, CA
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  • 24
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    Fretting in aircraft turbine engines (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Fretting usually produces both polished and pitted areas. Fretting occurs in connection with the relative motion between contacting surface elements. Particular attention is given to fretting in seals, splines, fans, compressors, and turbine blades. Recommended approaches to mitigate fretting problems include a reduction of the adhesion between two surfaces. Approaches for doing this may include the development of alloys which spontaneously generate a self-healing surface film, different in composition from the bulk alloy. Other fundamental adhesion studies have shown that surface crystal structure and crystallographic orientation significantly affect the adhesion properties of alloys.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NATO, AGARD, Meeting of the Structures and Materials Panel; Oct 06, 1974 - Oct 12, 1974; Munich
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  • 25
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    Titanium honeycomb acoustic lining structural and thermal test report (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results are presented of static, fatigue and thermal testing of titanium honeycomb acoustic panels representing the acoustic tailpipe for the Pratt and Whitney Aircraft JT8D Refan engine which is being studied for use on the Boeing 727-200 airplane. Test specimens represented the engine and tailpipe flange joints, the rail to which the thrust reverser is attached and shear specimens of the tailpipe honeycomb. Specimens were made in four different batches with variations in configuration, materials and processes in each. Static strength of all test specimens exceeded the design ultimate load requirements. Fatigue test results confirmed that aluminum brazed titanium, as used in the Refan tailpipe design, meets the fatigue durability objectives. Quality of welding was found to be critical to life, with substandard welding failing prematurely, whereas welding within the process specification exceeded the panel skin life. Initial fatigue testing used short grip length bolts which failed prematurely. These were replaced with longer bolts and subsequent testing demonstrated the required life. Thermal tests indicate that perforated skin acoustic honeycomb has approximately twice the heat transfer of solid skin honeycomb.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134783 , D6-42352
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  • 26
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    An experimental study of the effect of treated length on fan inlet noise suppressors (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effect of length of acoustic treatment was studied on a full scale fan using two different inlets. Analysis of the data revealed that measured suppression varied linearly with the length of the ringed liner segments as anticipated. Further analysis indicated that the wall only portion of the treatment was substantially more effective than anticipated, suggesting that, if only moderate suppression is needed, wall only treatment may suffice. The two inlets behaved similarly. Introduction of a hard exhaust splitter into the configuration resulted in a noise increase at certain frequencies.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71628 , E-7999 , Aerospace Sci. Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA; United States
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  • 27
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    Advanced supersonic technology concept study: Hydrogen fueled configuration (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Conceptual designs of hydrogen fueled supersonic transport configurations for the 1990 time period were developed and compared with equivalent technology Jet A-1 fueled vehicles to determine the economic and performance potential of liquid hydrogen as an alternate fuel. Parametric evaluations of supersonic cruise vehicles with varying design and transport mission characteristics established the basis for selecting a preferred configuration which was then studied in greater detail. An assessment was made of the general viability of the selected concept including an evaluation of costs and environmental considerations, i.e., exhaust emissions and sonic boom characteristics. Technology development requirements and suggested implementation schedules are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-114718 , LR-26323
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  • 28
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    Implications of multiplane-multispeed balancing for future turbine engine design and cost (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes several alternative approaches, provided by multiplane-multispeed balancing, to traditional gas turbine engine manufacture and assembly procedures. These alternatives, which range from addition of trim-balancing at the end of the traditional assembly process to modular design of the rotating system for assembly and balancing external to the engine, require attention by the engine designer as an integral part of the design process. Since multiplane-multispeed balancing may be incorporated at one or more of several points during manufacture-assembly, its deliberate use is expected to provide significant cost and performance (reduced vibration) benefits. Moreover, its availability provides the designer with a firm base from which he may advance, with reasonable assurance of success, into the flexible rotor dynamic regime.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 740865 , Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting; Oct 01, 1974 - Oct 03, 1974; San Diego, CA
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  • 29
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    Quasi-three-dimensional flow solution by meridional plane analysis (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computer program has been developed to obtain subsonic or shock-free transonic, nonviscous flow analysis on the hub-shroud midchannel flow surface of a turbomachine. The analysis may be for any annular passage, with or without blades. The blades may be fixed or rotating and may be twisted and leaned. The flow may be axial, radial, or mixed. Blade surface velocities over the entire blade are approximated, based on the rate of change of angular momentum. This gives a three-dimensional flow picture based on a two-dimensional analysis. This paper discusses the method used for the program and shows examples of the type of passages and blade rows which can be analyzed. Also, some numerical examples are given to show how the program can be used for practical assistance in design of blading, annular passages, and annular diffusers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 740850 , Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting; Oct 01, 1974 - Oct 03, 1974; San Diego, CA
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  • 30
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    Noise of model target type thrust reversers for engine-over-the-wing applications (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of experiments on the noise generated by V-gutter and semicylindrical target reversers with circular and short-aspect-ratio slot nozzles having diameters of about 5 cm are presented. The experiments were conducted with cold-flow jets at velocities from 190-290 m/sec. The reversers at subsonic jet velocities had a more uniform noise distribution and higher frequency than the nozzles alone. The reverser shape was shown to be more important than the nozzle shape in determining the noise characteristics. The maximum sideline pressure level varied with the sixth power of the jet velocity, and the data were correlated for angles along the sideline. An estimate of the noise level along the 152 m sideline for an engine-over-the-wing powered-lift airplane was made.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71621 , E-8142 , 88th Meeting of the Acoust. Soc. of Am; Nov 05, 1974 - Nov 08, 1974; St Louis, MO; United States
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  • 31
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    Emission calibration of a J-58 afterburning turbojet engine at simulated supersonic, stratospheric flight conditions (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Emissions of total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from a J-58 engine at simulated flight conditions of Mach 2.0, 2.4, and 2.8 at 19.8 km altitude are reported. For each flight condition, measurements were made for four engine power levels from maximum power without afterburning through maximum afterburning. These measurements were made 7 cm downstream of the engine primary nozzle using a single point traversing gas sample probe. Results show that emissions vary with flight speed, engine power level, and with radial position across the exhaust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: International Conference on the Environmental Impact of Aerospace Operations in the High Atmosphere; Jul 08, 1974 - Jul 10, 1974; San Diego, CA
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  • 32
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    Effect of forward velocity on the noise characteristics of dual-flow jet nozzles (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Acoustic results of jet noise tests conducted on scale-model nozzles at a wall isolation facility are presented and analyzed. The test fixture featured a triple-flow system for the purpose of simulating freestream flow around hot dual-flow jet nozzles. Test nozzles included 1/20th scale models of the exhaust system for the JT8D-9 engine, power plant for the Boeing 727 airplane (bypass ratio 1) and of the JT8D-109 refan engine (bypass ratio 2). It was found that overall jet noise is reduced by the forward velocity in proportion to the fifth and sixth power of the relative primary jet velocity. Spectral and directivity characteristics are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 74-WA/AERO-4 , American Society of Mechanical Engineers, Winter Annual Meeting; Nov 17, 1974 - Nov 22, 1974; New York, NY
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  • 33
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    Turbulent mixing of multiple co-axial gaseous fuel jets in a supersonic airstream (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental and analytical investigation of a strut-mounted, four-nozzle, downstream-facing, gaseous fuel-injector assembly was conducted in a Mach 4 airstream at 154 psia and 520 R. Helium was used as the injectant in order to simulate a low molecular weight fuel, and the interjet spacing (S/D) was the main parameter varied. The principal data are in the form of helium concentration profiles at seven axial stations, Mach number distributions at three axial stations, and Schlieren photographs of the flow field at different interjet spacings. An approximate analysis was developed based upon a linearization in the Von Mises plane, Crocco integrals for the temperature and concentrations fields, and an eddy viscosity model. Good agreement with the data was achieved. It was found that, at these conditions, interjet spacing has a significant effect on mixing only up to S/D of approximately 2.5, with the concentration of the injectant at a given point becoming smaller as S/D is increased.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 74-1157 , American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference; Oct 21, 1974 - Oct 23, 1974; San Diego, CA
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  • 34
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    Unified analysis of ducted turbomachinery noise (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The methodologies of Hanson and Zorumski are combined to yield a unified analysis of ducted turbomachinery noise. It is shown that the far-field broad-band and discrete noise spectral components can be expressed in terms of modal cross-spectral matrices and directivity vectors which are derivable from the duct analysis.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-72633 , 88th Meeting of the Acoust. Soc. of Am.; Nov 05, 1974 - Nov 08, 1974; St. Louis, MO; United States
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  • 35
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    Development of self-acting seals for helicopter engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental evaluation of a NASA-designed self-acting face seal for use in advanced gas turbine main shaft positions was conducted. The seal incorporated Rayleigh step pads (self-acting geometry) for lift augmentation. Satisfactory performance of the gas film seal was demonstrated in a 500-hour endurance test at speeds to 183 m/s (600 ft/sec, 54,000 rpm) and air pressure differential of 137 newtons per square centimeter (198.7 psi). Carbon wear was minor. Tests were also conducted with seal seat runout greater than that expected in engine operation and in a severe sand and dust environment. Seal operation was satisfactory in both these detrimental modes of operation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134739 , LYC-74-55
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  • 36
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    Cascade tests of serrated leading edge blading at high subsonic speeds (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Cascade tests of two-dimensional fan rotor blade rows were performed to investigate the effects of leading edge serration on acoustic and aerodynamic performance. The test configurations covered a range of serration tooth geometries. Tests were performed to investigate effects of inlet air angle and velocity on performance. Aerodynamic performance was determined by flow surveys at the mid-span of the blade exit. Acoustic performance was determined by wake turbulence surveys and sound measurements in the semireverberent exhaust chamber. Measured acoustic and aerodynamic performance was comparable and indicated that a serration length of about six percent blade chord yields minimum noise generation and minimum total pressure losses.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2472
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  • 37
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    Measurement and analysis of aircraft far-field aerodynamic noise (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A systematic investigation of aircraft far-field radiated, aerodynamically generated noise was conducted. The test phase of the original program involved the measurement of the noise produced by five gliding aircraft in an aerodynamically clean configuration during low altitude flyovers. These aircraft had gross weights that ranged from 5785 to 173 925N (1300 to 39,000 pounds), fly-by velocities from 30 to 98.5m/sec (58 to 191.5 knots or 98 to 323 ft/sec) and wing aspect ratios from 6.59 to 18.25. The results of these measurements were used to develop an equation relating aerodynamic noise to readily evaluated physical and operational parameters of the aircraft. A non-dimensional frequency spectrum, based on the mean wing thickness, was also developed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2377 , LR-26195
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  • 38
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    A 727/JT8D-100 series engine exhaust system propulsion performance model test (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented from testing one-eighth scale models of the Pratt and Whitney aircraft reference and Boeing nozzles for the JT8D-100 series mixed flow engines. The objective of the test was to obtain the nozzle velocity and flow coefficients for the reference configurations and compare these with the Boeing configurations which incorporated a longer splitter between the fan and primary flows. A further comparison was made between the JT8D-100 series nozzles and the Boeing JT8D-9/727 production nozzle performance. A statistical analysis was used to compare configurations which showed the performance (velocity coefficient) of the reference and the Boeing configuration was the same for the JT8D-109. It also showed no difference between reference and the Boeing configuration for the JT8D-115 and no difference for the JT8D-117 nozzles. Bypass ratio (match) was shown to be equally dependent on splitter position as on nozzle area within the range investigated. The nozzles were very similar in flow coefficient within an engine family. Excellent profile data was recorded. The effects of swirl on the nozzle performance was examined and found to degrade the velocity and flow coefficients.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134617 , D6-41805
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  • 39
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    Effect of treated length on performance of full scale turbofan inlet noise suppressors (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two inlet noise suppressors containing wall treatment plus three treated rings were tested on a fan in an outdoor noise facility. Sound power attenuations were measured for three treated lengths of each suppressor. The noise reduction from the segment of liner closest to the fan, which contained a segment of wall treatment downstream of the splitter rings, was greater than the reduction from either of the other segments. The decibel attenuations of the ringed liner segments were linear with liner length as predicted by theory. The acoustic attenuation of the wall treatment was considerably greater than expected for available theory. This inordinate effectiveness of the wall treatment strongly suggests the possibility of using no-ring inlet suppressors when the required noise reduction is moderate. The decibel attenuations were higher than predicted above 2000 hertz, and the two suppressors behaved similarly despite the prediction of different behavior.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TN-D-7826 , E-7999
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  • 40
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    Fundamental and applied research on core engine/combustion noise of aircraft engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Some results of a study of the importance of geometrical features of the combustor to combustion roughness and resulting noise are presented. Comparison is made among a perforated can flame holder, a plane slotted flame holder and a plane slotted flame holder which introduces two counter swirling streams. The latter is found to permit the most stable, quiet combustion. Crosscorrelations between the time derivative of chamber pressure fluctuations and far field noise are found to be stronger than between the far field noise and the direct chamber pressure signal. Temperature fluctuations in the combustor nozzle are also found to have a reasonably strong crosscorrelation with far field sound.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-140860 , AR-1
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  • 41
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    A forebody design technique for highly integrated bottom-mounted scramjets with application to a hypersonic research airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An inviscid technique for designing forebodies which produce uniformly precompressed flows at the inlet entrance for bottom-mounted scramjets has been developed so that geometric constraints resulting from design trade-offs can be effectively evaluated. The flow fields resulting from several forebody designs generated in support of a hypersonic research airplane conceptual design study have been analyzed in detail with three-dimensional characteristics calculations to verify the uniform flow conditions. For the designs analyzed, uniform flow is maintained over a wide range of flight conditions (Mach number equals 4 to 10; angle of attack equals 6 deg to 10 deg) corresponding to scramjet operation flight envelope of the research airplane.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71971
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  • 42
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    Distortion in a full-scale bicone inlet with internal focused compression and 45 percent internal contraction (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The distortion characteristics were investigated at the subsonic diffuser exit of a full-scale, Mach 2.5, axisymmetric, mixed compression inlet. Performance and steady-state distortion characteristics were obtained at zero and maximum angle of attack and during an inlet unstart-restart sequence. For the configuration with no cowl bleed, steady-state distortion P(max)P(min)P(bar) ranged from 0.10 for critical inlet operation at 0 deg angle-of-attack to 0.306 for supercritical inlet operation at 6.84 deg angle-of-attack. Vortex generators provided a 50 percent reduction in steady-state distortion for critical operation. Bleed has a smaller effect on steady-stated distortion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3133 , E-7992
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  • 43
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    Continuous-output terminal-shock-position sensor for mixed-compression inlets evaluated in wind tunnel tests of YF-12 aircraft inlet (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An electronic sensor was built to measure the position of the terminal shock in a supersonic inlet. The sensor uses several static-pressure taps in the inlet wall. The sensor output is continuously proportional to shock position. When the sensor was installed in a YF-12 aircraft flight inlet during wind tunnel tests, it indicated shock position within + or - 5 percent of the total distance covered by the static-pressure-tap region. The maximum error caused by an angle of attack change of 4 deg was less than 25 percent. In the region of normal inlet operation, the angle of attack error is negligible. Frequency-response tests show the amplitude ratio is constant out to 60 Hz, and decreases to about 50 percent at 100 Hz, with a phase lag of 50 deg.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3144 , E-7808
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  • 44
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    A comparison of optimum JP and LH2 turbofan engines designed for two subsonic transport missions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of liquid hydrogen fuel instead of JP fuel for two subsonic commercial transports was examined. The following determinations which are important to meeting noise reduction requirements were calculated: (1) take off gross weight, (2) energy consumption, and (3) direct operating costs. The optimum engine cycles were found to be the same for both fuels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71622 , E-8145
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  • 45
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    Two-stage fan. 2: Data and performance with redesigned second stage rotor uniform and distorted inlet flows (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two-stage fan with a first rotor tip speed of 1450 ft/sec (441.96 m/sec) and no inlet guide vanes was tested with uniform and distorted inlet flows, with a redesigned second rotor having a part span shroud to prevent flutter, with variable-stagger stators set in nominal positions, and without rotor casing treatment. The fan achieved a pressure ratio 2.8 at a corrected flow of 185.4 lbm/sec (84.0 kg/sec), an adiabatic efficiency of 85.0 percent, and a stall margin of 12 percent. The redesigned second rotor did not flutter. Tip radial distortion reduced the stall margin at intermediate speed, but had little effect on stall margin at high or low speeds. Hub radial distortion reduced the stall margin at design speed but increased stall margin at low speed. Circumferential distortion reduced stall pressure ratio and flow to give approximately the same stall lines with uniform inlet flow. Distortions were attenuated by the fan. For Vol. 1, see N74-11421.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134710 , PWA-5087
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  • 46
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    Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors, part 8 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted with an 0.8 hub/tip ratio, single-stage, axial flow compressor to determine the potential of tandem-airfoil blading for improving the efficiency and stable operating range of compressor stages. The investigation included testing of a baseline stage with single-airfoil blading and two tandem-blade stages. The overall performance of the baseline stage and the tandem-blade stage with a 20-80% loading split was considerably below the design prediction. The other tandem-blade stage, which had a rotor with a 50-50% loading split, came within 4.5% of the design pressure rise (delta P(bar)/P(bar) sub 1) and matched the design stage efficiency. The baseline stage with single-airfoil blading, which was designed to account for the actual rotor inlet velocity profile and the effects of axial velocity ratio and secondary flow, achieved the design predicted performance. The corresponding tandem-blade stage (50-50% loading split in both blade rows) slightly exceeded the design pressure rise but was 1.5 percentage points low in efficiency. The tandem rotors tested during both phases demonstrated higher pressure rise and efficiency than the corresponding single-airfoil rotor, with identical inlet and exit airfoil angles.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134713 , FR-6247-PT-8
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  • 47
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    Real-time simulation of the TF30-P-3 turbofan engine using a hybrid computer (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A real-time, hybrid-computer simulation of the TF30-P-3 turbofan engine was developed. The simulation was primarily analog in nature but used the digital portion of the hybrid computer to perform bivariate function generation associated with the performance of the engine's rotating components. FORTRAN listings and analog patching diagrams are provided. The hybrid simulation was controlled by a digital computer programmed to simulate the engine's standard hydromechanical control. Both steady-state and dynamic data obtained from the digitally controlled engine simulation are presented. Hybrid simulation data are compared with data obtained from a digital simulation provided by the engine manufacturer. The comparisons indicate that the real-time hybrid simulation adequately matches the baseline digital simulation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3106 , E-7904
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  • 48
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    Isolated rotor noise due to inlet distortion or turbulence (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Theoretical formulation, analysis, and results are presented that are necessary to analyze quadrupole noise generated from a loaded, subsonic rotor because of its interaction with an inflow distortion or inlet turbulence. The ratio of quadrupole to dipole noise is largely a function of the axial Mach number, wheel tip Mach number, rotor solidity, and total pressure ratio across the rotor. It is relatively independent of the specific form of the inflow distortion or inlet turbulence. Comparisons with experimental data only succeed in predicting gross levels at a given speed and fail to predict the variation of noise at fixed speed with flow and pressure ratio. Likely sources of this discrepancy are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2479
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  • 49
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    Strengthening of oxidation resistant materials for gas turbine applications (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Silicon nitride and silicon carbide ceramics were treated to form compressive surface layers. On the silicon carbide, quenching and thermal exposure treatments were used, and on the silicon nitride, quenching, carburizing, and a combination of quenching and carburizing were used. In some cases substantial improvements in impact resistance and/or flexural strength were observed. The presence of compressive surface stresses was demonstrated by slotted rod tests.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134661
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  • 50
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    Reliability of laboratory tests of VSTOL and other long duration noises (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Paired-comparison and magnitude estimations of the subjective noisiness or unacceptability of noise from fixed wing jet aircraft and simulated noise of VSTOL aircraft were obtained from groups of subjects given different instructions. These results suggest that VSTOL noises can be evaluated in terms of their noisiness or unwantedness to people with reasonable accuracy by units of the physical measures designated as PNdBM, with or without tone corrections, and dBD sub 2. Also, that consideration should be given to the use of D sub 2 as an overall frequency weighting function for sound level meters instead of the presently available A weighting. Two new units of noise measurement, PLdB and dB(E), used for predicting subjective noisiness, were found to be less accurate than PNdBM or dBD sub 2 in this regard.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2471
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  • 51
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    Scale model testing of the jet noise characteristics of the JT8D refan engine nozzle system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of static scale model acoustic tests of the nozzle system for the JT8D-9 baseline engine and candidate nozzle systems for JT8D-109, JT8D-115, and JT8D-117 refan engines. The objective of these tests was to determine the jet noise benefit of the three refan engine cycles relative to the baseline JT8D-9, and to provide acoustic information toward selection of the optimum primary-secondary area match and centerbody contour for the refan engine cycles. One of the nozzle configurations was tested with and without simulated turbine exit swirl to determine what effect, if any, swirl has no jet noise. The JT8D-109 cycle was found to afford approximately 9 db (0ASPL) jet noise reduction relative to the JT8D-9 when compared on an equal static thrust basis. The JT8D-115 and JT8D-117 afford an 8 db and 6 db reduction, respectively, relative to the JT8D-9, at equal static thrust. Turbine exit swirl was found to have no significant effect on the jet noise of the JT8D-109 nozzle system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134618 , D6-41529
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  • 52
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    Highly loaded multi-stage fan drive turbine: Performance of final three configurations (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results for a three-stage highly loaded fan drive turbine follow-on test program are presented. The effects of combinations of tandem and leaned bladerows on three-stage turbine performance were tested. The three-stage turbine with a tandem stator in stage two exhibited a total-to-total efficiency of approximately 0.887 as compared to 0.886 for the plain blade turbine base case.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2446 , GE73AEG481
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  • 53
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    Erosion in radial inflow turbines. Volume 3: Trajectories of erosive particles in radial inflow turbines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The theoretical trajectories that erosive particles follow in the gas flow fields of a typical radial inflow turbine were investigated. A discussion of the theoretical trajectories that the particles follow in the scroll, in the nozzles, in the vortex between the nozzles and the rotor, and in the rotor passages is included. The results are presented in terms of the characteristic length, a similarity parameter which relates the particles that follow the same trajectory in equivalent flow fields. For Vol, 1, see N74-19395.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134700
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  • 54
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    Flight test results of an automatic support system on board a YF-12A airplane (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An automatic support system concept that isolated faults in an existing nonavionics subsystem was flight tested up to a Mach number of 3. The adaptation of the automated support concept to an existing system (the jet engine automatic inlet control system) caused most of the problems one would expect to encounter in other applications. These problems and their solutions are discussed. Criteria for integrating automatic support into the initial design of new subsystems are included in the paper. Cost effectiveness resulted from both the low maintenance of the automated system and the man-hour saving resulting from the real time diagnosis of the monitored subsystem.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 55
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    Status of the JT8D refan noise reduction program (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The present work describes measures being taken to suppress jet noise in the JT8D engine and reports on some preliminary acoustic tests to evaluate noise characteristics of the engine. To reduce noise generation without sacrificing other essential engine performance or durability characteristics, the two stage fan will be replaced by a larger-diameter single stage fan. Refanned engines have an increased bypass ratio that contributes to the reduction of jet exhaust noise. Advanced acoustical design features will be incorporated in the larger, single-stage fan, and acoustic treatment will be incorporated in both the engine and the nacelle. First tests have shown that engine component noise levels are about as predicted and the acoustic treatment sections tested to date are providing predicted levels of attenuation. Further work is required to demonstrate engine performance goals and compatibility with 727 and DC-9 installations.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 56
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    Measurements of supersonic jet aircraft wakes in the stratosphere (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Progress is reported in an experimental program consisting of making supersonic aircraft wakes visible in the stratosphere so that photographs can be taken which yield wake dimensions vs time, and so that aircraft equipped with instruments which measure key exhaust species can find and penetrate the wakes. The object is to provide verification of fluid dynamic and chemical models. Three available models are summarized, and the experimental methods used are described. The Lockheed model predictions correspond in general most closely to experimental wake cross-sectional aerea. NO data are in reasonable agreement with NO predictions, but chemical models are relatively undeveloped, and additional measurements of exhaust products are needed before verification of chemical models becomes possible. However, the overall feasibility of wake visualization for model verification is substantiated. It is emphasized that significant model differences exist that must be resolved before reliable predictions can be made in the wake regimes studied.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: International Conference on the Environmental Impact of Aerospace Operations in the High Atmosphere; Jul 08, 1974 - Jul 10, 1974; San Diego, CA
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  • 57
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    Unified analysis of ducted turbomachinery noise (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An approach for an analysis of ducted turbomachinery noise is developed by combining features of the analysis of fan stator noise reported by Hanson (1973) with results obtained by Zorumski (1974). Hanson's analysis is briefly examined and a formula is derived for the far-field pressure due to a dipole pulse. Questions of transmission and reflection are discussed and attention is given to the radiation from ducted dipoles.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America, Meeting; Nov 04, 1974 - Nov 08, 1974; St. Louis, MO
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  • 58
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    Noise of model target type thrust reversers for engine-over-the-wing applications (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The present work reports on experiments concerning the noise generated by V-gutter and semicylindrical target reversers with circular and short-aspect-ratio slot nozzles having equivalent diameters of about 5 cm. At subsonic jet velocities of interest for engine-over-the-wing (OTW) powered-lift aircraft, the reversers were noisier than the nozzles alone and had a more uniform directional distribution and more high-frequency noise. Reverser shape was more important than nozzle shape in determining the reverser noise characteristics. An estimate is made of perceived noise level along the 152-m sideline for a hypothetical OTW powered-lift airplane.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Acoustical Society of America, Meeting; Nov 04, 1974 - Nov 08, 1974; St. Louis, MO
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  • 59
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    QCSEE task 2: Engine and installation preliminary design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: High-bypass turbofan engines with features required for commercial short haul powered lift transports were designed. Two engines were configured for each of the externally blown flap installations, under-the-wing and over-the-wing. Estimates of installed and uninstalled performance, noise, and weight were defined for each propulsion system.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134738
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  • 60
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    Acoustic results from tests of a 36-inch (0.914 m) diameter statorless lift fan (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A statorless, turbotip lift fan was tested statically outdoors to determine its acoustic characteristics. Spectral and directivity results are presented with comparison to data from the same family of lift fan designs having stator vanes. Modifications to the fan were tested to evaluate circular inlet guide vanes and exhaust treatment. A comparison was made of results obtained at General Electric Edwards Flight Test Center and NASA Ames Research Center with regards to test data and differences in site characteristics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-137621 , R73AEG360
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  • 61
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    Turbine gas temperature measurement and control system (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A fluidic Turbine Inlet Gas Temperature (TIGIT) Measurement and Control System was developed for use on a Pratt and Whitney Aircraft J58 engine. Based on engine operating requirements, criteria for high temperature materials selection, system design, and system performance were established. To minimize development and operational risk, the TIGT control system was designed to interface with an existing Exhaust Gas Temperature (EGT) Trim System and thereby modulate steady-state fuel flow to maintain a desired TIGT level. Extensive component and system testing was conducted including heated (2300F) vibration tests for the fluidic sensor and gas sampling probe, temperature and vibration tests on the system electronics, burner rig testing of the TIGT measurement system, and in excess of 100 hours of system testing on a J58 engine. (Modified author abstract)
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-140971 , AD-784901 , PWA-FR-6094 , AFAPL-TR-73-116
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  • 62
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    Acoustic attenuation design requirements established through EPNL parametric trades (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An optimization procedure for the provision of an acoustic lining configuration that is balanced with respect to engine performance losses and lining attenuation characteristics was established using a method which determined acoustic attenuation design requirements through parametric trade studies using the subjective noise unit of effective perceived noise level (EPNL).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-120986 , D3-8686
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  • 63
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    Design problems of small turbomachinery (1970)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Advanced design and testing techniques developed at NASA Lewis to achieve high efficiency in small turbomachines are described. Small radial and axial turbines and compressors were built for space power systems and associated studies at the Lewis Research Center. A six stage axial compressor of 3.5 inches diameter and axial turbines of 5 and 8.5 inches diameter were included. Radial turbines and compressors ranged from 3.5 to 6 inches. Topics discussed include maximum efficiency as a function of speed, the effect of compressibility on passage size, the use of quasi-orthogonals to calculate cross-channel velocity gradients, a design point velocity diagram study for axial turbines, and estimating off-design performance. Special turbine instruments and calibration procedures were developed to test compressors and turbines, to determine Reynolds and size number effects clearance, specific speed effects, and compressor performance. Laboratory tests conducted to study system operation and shaft and bearing motions are also reviewed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Von Karman Inst. for Fluid Dyn. Closed Cycle Gas Turbines; 11 p
    Format: text
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  • 64
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    Investigation of Icing Characteristics of Typical Light Airplane Engine Induction Systems (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The icing characteristics of two typical light-airplane engine induction systems were investigated using the carburetors and manifolds of engines in the horsepower ranges from 65 to 85 and 165 to 185. The smaller system consisted of a float-type carburetor with an unheated manifold and the larger system consisted of a single-barrel pressure-type carburetor with an oil-jacketed manifold. Carburetor-air temperature and humidity limits of visible and serious Icing were determined for various engine power conditions. Several.methods of achieving ice-free induction systems are discussed along with estimates of surface heating requirements of the various induct ion-system components. A study was also made of the icing characteristics of a typical light-airplane air scoop with an exposed filter and a modified system that provided a normal ram inlet with the filter located in a position to Induce inertia separation of the free water from the charge air. The principle of operation of float-type carburetors is proved to make them inherently more susceptible to icing at the throttle plate than pressure-type carburetors.. The results indicated that proper jacketing and heating of all parts exposed to the fuel spray can satisfactorily reduce or eliminate icing in the float-type carburetor and the manifold. Pressure-type carburetors can be protected from serious Icing by proper location of the fuel-discharge nozzle combined with suitable application of heat to critical parts.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1790
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  • 65
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    Eine Methode zur quantitativen Erfassung der Zusammenhänge zwischen Wetterablauf und Ernteertrag (1948)
    In:  Annalen der Meteorologie, S. 326-328.
    Details
    Publication Date: 1948
    Description: Entwicklung eines "Wetterschadensfaktor", der Zusammenhang zwischen Witterung und Ernteertrag beschreibt KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Schleswig-Holstein ; 1933-42 ; Kartoffeln ; Ertrag ; Korrelationsmethode ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung
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  • 66
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    A Review of propeller theory (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA: Univ. Conf. on Aerodyn.; p 71-105
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  • 67
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    Natural icing of an axial-flow turbojet engine in flight for a single icing condition (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-RM-E8F01A
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  • 68
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    Icing and De-Icing of a Propeller with Internal Electric Blade Heaters (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been made in the NACA Cleveland icing research tunnel to determine the de-icing effectiveness of an experimental configuration of an Internal electric propeller-blade heater. Two atmospheric Icing conditions and two propeller operating conditions were Investigated, In experiments with unheated blades and with heat applied to the blades both continuously and cyclically. Data are presented to show the effect of propeller speed., ambient air temperature and liquid-water concentration, and the duration of the heat-on and cycle times on the power requirements and de-Icing performance of the blade heaters. The extent of ice-covered area on the blades for various icing ax4 operating conditions has been determined. The largest iced area was obtained at the higher ambient-air temperatures and at low propeller speed. The ohord.wise extent of Icing In practically every case was greater than that covered by blade heaters. Adequate de-icing in the heated area with continuous application of heat was obtained with the power available but a maximum power, input of 1250 watts per blade was insufficient for cyclic de-Icing for the range of conditions investigated. Blade-surface temperature rates of rise of 0.2 to 0.7 F per second were obtained and the minimum cooling period for cyclic de-icing was found to be approximately 2-1/2 times the heating period.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1691
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  • 69
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    Investigation of Effectiveness of Air-Heating a Hollow Steel Propeller for Protection Against Icing. 1: Unpartitioned Blades (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation to determine the effectiveness of icing protection afforded by air-heating hollow steel unpartitioned propeller blades has been conducted In the NACA Cleveland icing research tunnel. The propeller used was a production model modified with blade shank and tip openings to permit internal passage of heated air. Blade-surface and heated-air temperatures were obtained and photographic observations of Ice formations were made with variations In icing intensity and heating rate to the blades. For the conditions of Icing to which the propeller was subjected, it was found that adequate ice protection was afforded with a heating rate of 40 1 000 Btu per hour per blade. With less than 40,000 Btu per hour per blade, ice protection failed because of significant ice accretions on the leading edge. The chordwise distribution of heat was unsatisfactory with most of the available heat dissipated well back of the leading edge on both the thrust and camber face's instead of at the leading edge where it was most needed. A low utilization of available heat for icing protection is indicated by a beat-exchanger effectiveness of approximately 47 percent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1586
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  • 70
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    Preliminary results of natural icing of an axial-flow turbojet engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-RM-E8C18
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  • 71
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    Investigation of Effectiveness of Air-Heating a Hollow Steel Propeller for Protection Against Icing. 3: 25% Partitioned Blades (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The icing protection obtained from an internally air-heated propeller blade partitioned to confine the heated air forward of 25-percent chord was investigated in the NACA Cleveland icing research tunnel. A production-model hollow steel propeller was modified with an Internal radial partition at 25-percent chord and with shank and tip openings to admit and exhaust the heated air. Temperatures were measured on the blade surfaces and in the heated-air system during tunnel icing conditions. Heat-exchanger effectiveness and photographs of Ice formations on the blades were obtained. Surface temperature measurements indicated that confining the heated air forward of the 25-percent chord gave.a more economical distribution of the applied heat as compared with unpartitioned and 50-percent partitioned blades, by dissipating a greater percentage of the available heat at the leading edge. At a propeller speed of 850 rpm, a heating rate of 7000 Btu per hour per blade at a shank air temperature of 400 F provided adequate Icing protection at ambient-air temperatures of 23 F but not at temperatures as low as 15 F. With the heating rate used, a heat-exchanger effectiveness of 77 percent was obtained as compared to 56 percent for 50-percent partitioned and 47 percent for unpartitioned blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1588
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  • 72
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    Investigation of Effectiveness of Air-Heating a Hollow Steel Propeller for Protection Against Icing. 2: 50% Impartitioned Blades (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The icing protection afforded an internal air-heated propeller blade by radial partitioning at 50-percent chord to confine the heated air to the forward half of the blade was determined in the NACA Cleveland icing research tunnel. A modified production-model hollow steel propeller, was used for the investigation. Temperatures of the blade surfaces for several heating rates were measured under various tunnel Icing' conditions. Photographic observations of ice formations on blade surfaces and blade heat-exchanger effectiveness were obtained. With 50-percent partitioning of the blades, adequate icing protection at 1050 rpm was obtained with a heating rate of 26,000 Btu per hour per blade at the blade shank using an air temperature of 400 F with a flow rate of 280 pounds per hour per blade, which is one-third less heat than was found necessary for similar Ice protection with unpartitioned blades. The chordwise distribution of the applied heat, as determined by surface temperature measurements, was considered unsatisfactory with much of the heat dissipated well back of the leading edge. Heat-exchanger effectiveness of approximately 56 percent also Indicated poor utilization of available heat. This effectiveness was, however, 9 percent greater than that obtained from unpartitioned blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1587
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  • 73
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    De-icing effectiveness of external electric heaters for propeller blades (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1520
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  • 74
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    Propellers at high speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 67-76
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  • 75
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    A flight investigation of the thermal performance of air heated propeller (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1178
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  • 76
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    Wind-tunnel investigation of icing of an engine cooling-fan installation (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1246
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  • 77
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    A method for estimating heat requirements for ice prevention gas heated hollow propeller blades (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NACA-TN-1494
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  • 78
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    Über Sortenauswahl bei Getreide mit Rücksicht auf Betriebsintensität, Boden, Klima u. Kulturzustand (1919)
    Details
    Publication Date: 1919
    Description: Verteilung von Sonnenschein und Regen, aufgeteilt nach Monaten und der Bezug zu den Entwicklungsstadien verschiedener Pflanzengattungen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Schlesien ; Anfang des 20. Jahrhunnderts ; Anbautermine ; Boden ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Wachstum ; Witterung ; Düngung ; Hackfrüchte
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  • 79
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    Einfluss der Witterungsverhältnisse auf das Auftreten von Pflanzenkrankheiten und tierischen Schädlingen 1916 und 1917 (1918)
    In:  Zeitschr. Pflanzenkrankh. 28; p.116-142 und p.201-210
    Details
    Publication Date: 1918
    Description: Vergleich der Witterungsverhältnisse und des Schaderregerauftretens der Jahre 1916 und 1917, sowie Diskussion klimatischer Einflüsse auf das Auftreten pflanzlicher und tierischer Schädlinge an diversen Kulturpflanzen aus Ackerbau, Obstbau und Forstwirtschaft anhand von Beobachtungen. Die meisten Beobachtungen dürften aus der Gegend um Weihenstephan (Bayern) stammen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1916-1917 ; Forst ; Getreide ; Landwirtschaft ; Pflanzenkrankheit ; Pflanzenschädling ; Hackfrüchte ; Obst
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  • 80
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    Luftdruckverteilung, Winde und Niederschläge in Nord- und Mitteleuropa nebst Bemerkugnen über die Beziehung dieser klimatischen Elemente zur Landwirtschaft (1917)
    In:  Landwirtschaftl. Jahrbuch 50: 585
    Details
    Publication Date: 1917
    Description: Beschreibung de Niederschlagsverteilung und Bedeutung für die Vegetation und Anbaubedingungen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Nord- und Mitteleuropa ; 1850-1915 ; Landwirtschaft ; Niederschlag ; Wind
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