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  • Aircraft Propulsion and Power
  • Earth model, also for more shallow analyses !
  • 1995-1999
  • 1990-1994  (28)
  • 1950-1954  (26)
  • 1994  (28)
  • 1954  (5)
  • 1951  (21)
Collection
Keywords
Publisher
Years
  • 1995-1999
  • 1990-1994  (28)
  • 1950-1954  (26)
Year
  • 1
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    Constraints on Himalayan deformation inferred from vertical velocity fields in Nepal and Tibet (1994)
    In:  J. Geophys. Res., Amsterdam, Schweizerbart'sche Verlagsbuchhandlung, vol. 99, no. 2, pp. 13897-13912, pp. L07302, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Details
    Publication Date: 1994
    Keywords: China ; Tectonics ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Deep seismic sounding (espec. cont. crust) ; Velocity depth profile ; Earth model, also for more shallow analyses ! ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Structures and kinematics in the northeastern Mediterranean: A study of an irregular plate boundary (1994)
    In:  Tectonophys., New York, Allerton Press, vol. 234, no. 13, pp. 5-18, pp. L13315, (ISSN: 1340-4202)
    Details
    Publication Date: 1994
    Keywords: Earth model, also for more shallow analyses ! ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Plate tectonics ; Turkey
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    The density contrast at the Mohorovicic discontinuity (1994)
    In:  Geophys. J. Int., Zagreb, 3-4, vol. 117, no. 3, pp. 539-544, pp. B06305, (ISSN: 1340-4202)
    Details
    Publication Date: 1994
    Keywords: Mohorovicic disc. ; Earth model, also for more shallow analyses ! ; Physical properties of rocks ; Gravimetry, Gravitation ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Regional scale tectonic evolution and the seismic velocity structure of the lithosphere and upper mantle: The Mediterranean region (1994)
    In:  J. Geophys. Res., London, Geological Society, vol. 99, no. 11, pp. 12091-12108, pp. L11303, (ISBN 1-86239-117-3)
    Details
    Publication Date: 1994
    Keywords: Tectonics ; Turkey ; Earth model, also for more shallow analyses ! ; Tomography ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Seismic velocities and Q-factors in the uppermost crust beneath the SVEKA profile in Finland (1994)
    In:  Tectonophys., Warszawa, Icelandic Meteorological Office, Ministry for the Environment,, vol. 230, no. 4, pp. 1-19, pp. 1567, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1994
    Keywords: Seismics (controlled source seismology) ; Attenuation ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; Quality factor
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Pn velocities beneath continental collision zones: The Turkish-Iranian Plateau (1994)
    In:  Geophys. J. Int., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 117, no. 1, pp. 273-283, pp. 1549, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1994
    Keywords: P-waves ; Plate tectonics ; Velocity analysis ; earth mantle ; Mohorovicic disc. ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Seismological constraints on the gabbro-eclogite transition in subducted oceanic crust (1994)
    In:  Earth planet. Sci. Lett., Kleinmachnow, Dt. Geophys. Ges. e. V., vol. 122, no. 6, pp. 89-101, pp. B05401, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1994
    Keywords: Seismology ; Earth model, also for more shallow analyses ! ; Subduction zone ; phase ; transition
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Shear-wave velocity variations in the upper mantle beneath central Europe (1994)
    In:  Geophys. J. Int., Kunming, China, 3-4, vol. 117, no. 1, pp. 695-715, pp. B05S18, (ISSN: 1340-4202)
    Details
    Publication Date: 1994
    Keywords: Shear waves ; Earth model, also for more shallow analyses ! ; Velocity depth profile ; earth mantle ; GJI
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Differenti tipi di litosfera e differenti stili di subduzione negli Appennini (1994)
    Gruppo Nazionale di Geofisica della Terra Solida
    In:  Atti del 13. Convegno Annuale del Gruppo Nazionale di Geofisica della Terra Solida, Roma, Gruppo Nazionale di Geofisica della Terra Solida, vol. C 560, 183 pp., no. 70, pp. 13-24, (ISBN 3-933346-037)
    Details
    Publication Date: 1994
    Keywords: Subduction zone ; Italy ; Earth model, also for more shallow analyses ! ; Elasticity
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Angolo di subduzione in astenosfera in moto (1994)
    Gruppo Nazionale di Geofisica della Terra Solida
    In:  Atti del 13. Convegno Annuale del Gruppo Nazionale di Geofisica della Terra Solida, Roma, Gruppo Nazionale di Geofisica della Terra Solida, vol. C 560, 183 pp., no. 78 (?), pp. 193-210, (ISBN 3-933346-037)
    Details
    Publication Date: 1994
    Keywords: Subduction zone ; Italy ; Earth model, also for more shallow analyses ! ; Elasticity
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Flight Research Using F100 Engine P680063 in the NASA F-15 Airplane (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The value of flight research in developing and evaluating gas turbine engines is high. NASA Dryden Flight Research Center has been conducting flight research on propulsion systems for many years. The F100 engine has been tested in the NASA F-15 research airplane in the last three decades. One engine in particular, S/N P680063, has been used for the entire program and has been flown in many pioneering propulsion flight research activities. Included are detailed flight-to-ground facility tests; tests of the first production digital engine control system, the first active stall margin control system, the first performance-seeking control system; and the first use of computer-controlled engine thrust for emergency flight control. The flight research has been supplemented with altitude facility tests at key times. This paper presents a review of the tests of engine P680063, the F-15 airplanes in which it flew, and the role of the flight test in maturing propulsion technology.
    Keywords: Aircraft Propulsion and Power
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    NASA TECHNICAL REPORTS
  • 12
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    Effects of Mistuning on the Forced Response of Turbomachinery Rotors (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The basic purpose of this research has been to develop a fundamental understanding of the effects of blade-to-blade dissimilarities, or mistuning, on the dynamics of nearly cyclic bladed-disk assemblies. This topic is of importance as mistuning has been shown to increase the forced response amplitudes of some blades significantly, and even to lead to blade failure. Furthermore, the current trend toward high performance propulsion turbomachinery designed for finite service life demands an accurate prediction of system performance and dynamics at the design stage. This objective has been achieved by carrying out the following tasks. First, the investigation of the free and forced responses of representative, yet sufficiently simple blade assembly models that capture all the important characteristics of typical turbomachinery rotors. Second, the development of computational methods that predict the effects of mistuning in a systematic and reliable way, along with the development of a systematic reduced-order modeling procedure for mistuned bladed disks. Third, the application of these findings and the tools developed to an industrial rotor, namely the first stage of turbine blades of the oxidizer turbopump in the space shuttle main rocket engine (SSME). The research supported by NASA has led to the development of a coherent theory for mistuned blade assemblies. The further implementation of these computational tools into the forced response prediction system currently under development in the Structural Dynamics Branch-FREPS-would enable the designer and the analyst to: (1) identify types of blade assemblies highly sensitive to mistuning in various frequency and other parameter ranges and (2) characterize mistuning effects on their forced response by predicting true response amplitudes and fatigue life estimates.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-205484 , NAS 1.26:205484
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  • 13
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    In Operation Detection and Correction of Rotor Imbalance in Jet Engines Using Active Vibration Control (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Jet Engines may experience severe vibration due to the sudden imbalance caused by blade failure. This research investigates employment of on board magnetic bearings or piezoelectric actuators to cancel these forces in flight. This operation requires identification of the source of the vibrations via an expert system, determination of the required phase angles and amplitudes for the correction forces, and application of the desired control signals to the magnetic bearings or piezo electric actuators. This paper will show the architecture of the software system, details of the control algorithm used for the sudden imbalance correction project described above, and the laboratory test results.
    Keywords: Aircraft Propulsion and Power
    Type: SAE-TP-941151 , (ISSN 0148-7191)|Aerospace Atlantic Conference and Exposition; Apr 18, 1994 - Apr 22, 1994; Dayton, OH; United States
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    NASA TECHNICAL REPORTS
  • 14
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    Analytical Studies of Prompt NO(x) Emissions from Aircraft Gas Turbine Combustors (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The reduction of oxides of nitrogen (NO(x)) emissions from aircraft gas turbines is a vital part of the NASA High Speed Research Program (HSRP). Emissions reduction studies are critical to the feasibility of future civil aircraft operating at supersonic speeds in the stratosphere. It is believed that large fleets of supersonic aircraft using conventional gas turbine engines would emit levels of NO(x) that are harmful to the stratospheric ozone layer.
    Keywords: Aircraft Propulsion and Power
    Type: 31st AIAA/SAE/ASME/ASEE Joint Propulsion Conference; Jul 10, 1995 - Jul 12, 1995; San Diego, CA; United States
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  • 15
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    Measurements of Forward Flight Effects on the Advanced Ducted Propulsion Demonstrator Engine (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The performance of the Pratt & Whitney Advanced Ducted Propulsion (ADP) UHB concept has been recently evaluated with studies of a 17 in. diameter fan simulator. Following the model scale tests, a 118 in. diameter demonstrator was tested at the NASA Ames 40- by 80-Foot Wind Tunnel. The 18 blade fan was driven by the low compressor shaft of a PW2037 core through a reduction gear system fabricated by Fiat with approximately 1:3.7 reduction ratio. ne variable pitch fan was hydraulically actuated with settings for take-off, cruise, feather, and reverse thrust. The low-pressure turbine was built by MTU to provide higher shaft power in comparison with the standard PW2037. The demonstrator was provided with 45 vanes located 2.6 fan chords downstream of the rotor, and 10 case struts approximately 1 fan chord downstream of the vanes. The inlet, mid-duct, and exhaust linings were acoustically treated. Acoustic surveys were taken in the for-ward thrust mode for fan speeds of 898, 1120, 1205, and 1302 R.P.M., and at tunnel speeds of 25, 50, 100, and 140 kts. The lowest speed was achieved with the wind tunnel fans at flat pitch, but with the engine pumping the test section Microphone signals were recorded for 30 seconds at 5 deg. increments. These measurements will be used to assess the effects of forward speed on UHB engines, to compare these effects with the corresponding characteristics of conventional bypass ratio engines, and to discuss the various aspects of testing large engines in the wind tunnel.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA/ASME/ASEE Joint Propulsion and Exhibit; Jul 10, 1995 - Jul 12, 1995; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 16
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    Flight Testing of Hypersonic Airbreathing Propulsion for Developing Computational Design Technology (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The objective of this paper is to present and discuss a scenario and the requirements for flight testing of hypersonic airbreathing propulsion leading to the development of computational design technology. Flight Testing for this development is a significant part of a triad/synergistic, design approach which integrates computations, flight testing, and ground testing. These three complementary, design developmental tools have various capabilities and limitations. An incremental approach is necessary to use and to develop these tools effectively and efficiently. This computational technology must be developed keeping in focus the aerospace plane that is to be developed. The criteria for selecting the right plane are presented and consequently, the appropriate flight tests are identified. Two conceptual, flight-test systems are suggested considering the following: (1) the relevant, lessons learned from previous and current United States hypersonic programs, from the Apollo program, from the Space Shuttle program, and from the space station program; (2) the current need for a low risk, affordable access to space; and (3) the design challenge for hypersonic airbreathing propulsion testing. How these systems may be used for developing the computational design technology is described. The requirements for conducting propulsion- design computations, sources of uncertainties in these computations, and a guide for establishing the credibility of these computations are also presented.
    Keywords: Aircraft Propulsion and Power
    Type: Second European Symposium on Aerothermodynamics for Space Vehicles; Nov 22, 1994 - Nov 25, 1994; Noordwijk; Netherlands|Fourth European High-Speed Database Workshop; Nov 22, 1994 - Nov 25, 1994; Noordwijk; Netherlands
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    NASA TECHNICAL REPORTS
  • 17
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    Simulation of Unsteady Combustion in a Ramjet Engine Using a Highly Parallel Computer (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Combustion instability in ramjets is a complex phenomenon that involve nonlinear interaction between acoustic waves, vortex motion and unsteady heat release in the combustor. To numerically simulate this 3-D, transient phenomenon, enormous computer resources (time, memory and disk storage) are required. Although current generation vector supercomputers are capable of providing adequate resources for simulations of this nature, their high cost and limited availability, makes such machines less than satisfactory for routine use. The primary focus of this study is to assess the feasibility of using highly parallel computer systems as a cost-effective alternative for conducting such unsteady flow simulations. Towards this end, a large-eddy simulation model for combustion instability was implemented on the Intel iPSC/860 and a careful study was conducted to determine the benefits and the problems associated with the use of such machines for transient simulations. Details of this study along with the results obtained from the unsteady combustion simulations carried out on the iPSC/860 are discussed in this paper.
    Keywords: Aircraft Propulsion and Power
    Type: 1994 Simulation Multi Conference; Apr 10, 1994 - Apr 15, 1994; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 18
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    Large Scale Scramjet Propulsion Testing In The Mach 8 and 16 Regime At NASA Ames Research Center (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: The objective of this paper is to describe the affordable, large scale scramJet test capability for flight Mach numbers between 8 and 16 which has been developed at the NASA Ames Research Center. Details of the Direct Connect Arc Facility DCAF, which can produce combustor test conditions with fuel-on testing for 10 seconds at conditions representative of Mach 8 - 12 flight, are presented and typical test results are described. Likewise, a description of the full scale combustor test capability of the 16 inch shock tunnel is outlined. This facility is characterized by long run times (〉 5 milliseconds) for an impulse facility, and it can provide conditions representative of flight conditions from Mach 12 - 16. Typical test results for this shock tunnel are discussed as well. Future upgrades to both facilities are outlined and new uses for their capabilities are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: Twelfth International Symposium on Airbreathing Engines; Sep 10, 1995 - Sep 15, 1995; Melbourne; Australia
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    NASA TECHNICAL REPORTS
  • 19
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    High temperature turbine engine structure (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A high temperature ceramic/metallic turbine engine includes a metallic housing which journals a rotor member of the turbine engine. A ceramic disk-like shroud portion of the engine is supported on the metallic housing portion and maintains a close running clearance with the rotor member. A ceramic spacer assembly maintains the close running clearance of the shroud portion and rotor member despite differential thermal movements between the shroud portion and metallic housing portion.
    Keywords: Aircraft Propulsion and Power
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    NASA TECHNICAL REPORTS
  • 20
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    Low NO.sub.x combustor (1994)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A combustor includes a dome assembly having radially outer and inner liners joined thereto and defining therebetween a combustion zone. The dome assembly includes at least one annular dome having a pair of axially extending first flanges between which are disposed a plurality of circumferentially spaced apart carburetors for discharging a fuel/air mixture into the combustion zone for generating combustion gases. An annular heat shield includes a pair of axially extending legs integrally joined to a radially extending face in a generally U-shaped configuration, with the face including a plurality of circumferentially spaced apart ports disposed concentrically with perspective ones of the carburetors for allowing the fuel/air mixture to be discharged therefrom through the heat shield. At least one of the heat shield legs includes a plurality of circumferentially spaced apart mounting holes disposed adjacent to a respective one of the dome flanges, and a plurality of mounting pins are fixedly joined to the dome flange and extend radially through respective ones of the mounting holes without interference therewith for allowing unrestrained thermal movement between the heat shield and the dome while supporting the heat shield against axial pressure loads thereon. In a preferred embodiment, the dome assembly includes three domes having respective ones of the heat shield, and respective baffles are spaced from the heat shields for providing impingement cooling thereof.
    Keywords: Aircraft Propulsion and Power
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    NASA TECHNICAL REPORTS
  • 21
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    Combustor liner support assembly (1994)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A support assembly for a gas turbine engine combustor includes an annular frame having a plurality of circumferentially spaced apart tenons, and an annular combustor liner disposed coaxially with the frame and including a plurality of circumferentially spaced apart tenons circumferentially adjoining respective ones of the frame tenons for radially and tangentially supporting the liner to the frame while allowing unrestrained differential thermal radial movement therebetween.
    Keywords: Aircraft Propulsion and Power
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  • 22
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    Jet mixer noise suppressor using acoustic feedback (1994)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The present invention generally relates to providing an improved jet mixer noise suppressor for high speed jets that rapidly mixes high speed air flow with a lower speed air flow, and more particularly, relates to an improved jet mixer noise suppressor that uses feedback of acoustic waves produced by the interaction of sheer flow instability waves with an obstacle downstream of the jet nozzle.
    Keywords: Aircraft Propulsion and Power
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    NASA TECHNICAL REPORTS
  • 23
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    Investigation of Methods for the Structural Weight Analysis of a Mach 2.4 Axisymmetric Inlet (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Structural design and analysis tools appropriate for estimating the structural weight of an axisymmetric inlet designed for Mach 2.4 cruise were evaluated. Little information regarding the inlet mechanical design is available in the preliminary design phase, so it is necessary to first develop a reasonable structural design before estimating the inlet weight. The Internally Pressurized Structure Synthesis and Optimization (IPSSO) program, employing an analytical approach, was chosen for evaluation due to its combined design and analysis capabilities. The inlet design produced by IPSSO was then analyzed using the NASTRAN finite element program. The finite element analysis was performed to help identify the limitations of the analytically based code as well as to evaluate NASTRAN for this application. Comparison between the IPSSO inlet weight and that of a similar inlet developed by the Boeing Commercial Airplane Group was also made. Program evaluation concluded that the combined use of IPSSO to create an initial design and NASTRAN to perform a numerical analysis would provide the capability to evaluate a limited number of inlet design The development of a new tool for the minimum weight design and analysis of inlet structures would be required for greater flexibility in evaluating inlet conceptual designs.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-106693 , E-9048 , NAS 1.15:106693
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  • 24
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    Sound suppression mixer (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A gas turbine engine flow mixer includes at least one chute having first and second spaced apart sidewalls joined together at a leading edge, with the sidewalls having first and second trailing edges defining therebetween a chute outlet. The first trailing edge is spaced longitudinally downstream from the second trailing edge for defining a septum in the first sidewall extending downstream from the second trailing edge. The septum includes a plurality of noise attenuating apertures.
    Keywords: Aircraft Propulsion and Power
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  • 25
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    Rotating stall suppression (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Rotating stall in an axial-flow compressor is suppressed by the positioning of a fixed inlet flow divider in the annular inlet flow passage upstream of the compressor. The inlet flow divider is aligned with the flow of fluid through the duct and acts to block or interfere with any rotating wave in the inlet and thereby suppresses rotating stall in the compressor.
    Keywords: Aircraft Propulsion and Power
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    NASA TECHNICAL REPORTS
  • 26
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    Control of an Axisymmetric Jet Using Vortex Generators (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of an experimental investigation on the effect of vortex generators, in the form of small tabs at the nozzle exit on the evolution of a jet, are reported in this paper. Primarily tabs of triangular shape are considered, and the effect is studied up to a jet Mach number of 1.8. Each tab is found to produce a dominant pair of counter-rotating streamwise vortices having a sense of rotation opposite to that expected from the wrapping of the boundary layer. This results in an inward indentation of the mixing layer into the core of the jet. A triangular-shaped tab with its apex leaning downstream, referred to as a delta tab, is found to be the most effective in producing such vortices, with a consequential large influence on the overall jet evolution. Two delta tabs, spaced 180 deg apart, completely bifurcate the jet. Four delta tabs stretch the mixing layer into four 'fingers,' resulting in a significant increase in the jet mixing downstream. For six delta tabs the mixing layer distortion settles back to a three finger configuration through an interaction of the streamwise vortices. The tabs are found to be equally effective in jets with turbulent or laminar initial boundary layers. Two sources of streamwise vorticity are postulated for the flow under consideration. One is the upstream 'pressure hill,' generated by the tab, which constitutes the main contributor of vorticity to the dominant pair. Another is due to vortex filaments shed from the sides of the tab and reoriented downstream by the mean shear of the mixing layer. Depending on the orientation of the tab, the latter source can produce a vortex pair having a sense of rotation opposite to that of the dominant pair. In the case of the delta tab, vorticity from the two sources add, explaining the strong effect in that configuration.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-204348 , NAS 1.26:204348 , E-7637 , Phys. Fluids (ISSN 1070-6631); 6; 2; 778-793
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  • 27
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    Liner mounting assembly (1994)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A mounting assembly includes an annular supporting flange disposed coaxially about a centerline axis which has a plurality of circumferentially spaced apart supporting holes therethrough. An annular liner is disposed coaxially with the supporting flange and includes a plurality of circumferentially spaced apart mounting holes aligned with respective ones of the supporting holes. Each of a plurality of mounting pins includes a proximal end fixedly joined to the supporting flange through a respective one of the supporting holes, and a distal end disposed through a respective one of the liner mounting holes for supporting the liner to the supporting flange while unrestrained differential thermal movement of the liner relative to the supporting flange.
    Keywords: Aircraft Propulsion and Power
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    NASA TECHNICAL REPORTS
  • 28
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    Ramjet bypass duct and preburner configuration (1994)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A combined turbofan and ramjet aircraft engine includes a forward bypass duct which allows the engine to operate more efficiently during the turbofan mode of operation. By mounting a ramjet preburner in the forward duct and isolating this duct from the turbofan bypass air, a transition from turbofan operation to ramjet operation can take place at lower flight Mach numbers without incurring pressure losses or blockage in the turbofan bypass air.
    Keywords: Aircraft Propulsion and Power
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  • 29
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    Investigation of Noise Field and Velocity Profiles of an Afterburning Engine (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sound pressure levels, frequency spectrum, and jet velocity profiles are presented for an engine-afterburner combination at various values of afterburner fuel - air ratio. At the high fuel-air ratios, severe low-frequency resonance was encountered which represented more than half the total energy in the sound spectrum. At similar thrust conditions, lower sound pressure levels were obtained from a current fighter air craft with a different afterburner configuration. The lower sound pressure levels are attributed to resonance-free afterburner operation and thereby indicate the importance of acoustic considerations in afterburner design.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E54G07
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    NASA TECHNICAL REPORTS
  • 30
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    An Investigation in the Ames 40- by 80-Foot Wind Tunnel of a YT-56A Turboprop Engine Incorporating a Decoupler and a Controlled-Feathering Device (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of a decoupler and a controlled-feathering device incorporated with the YT-56A turboprop engine has been made to determine the effectiveness of these devices in reducing the high negative thrust (drag) which accompanies power failure of this type of engine. Power failures were simulated by fuel cut-off, both without either device free to operate, and with each device free to operate singly. The investigation was made through an airspeed range from 50 to 230 mph. It was found that with neither device free to operate, the drag levels realized after power failures at airspeeds above 170 mph would impose vertical tail loads higher than those allowable for the YC-130, the airplane for which the test power package was designed. These levels were reached in approximately one second. The maximum drag realized after power failure was not appreciably altered by the use of the decoupler although the decoupler did put a limit on the duration of the peak drag. The controlled-feathering device maintained a level of essentially zero drag after power failure. The use of the decoupler in the YT-56A engine complicates windmilling air-starting procedures and makes it necessary to place operating restrictions on the engine to assure safe flight at low-power conditions,
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SA54I09
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  • 31
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    Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet Engine (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes between 15,000 and 66,000 feet in the Lewis altitude wind tunnel. Included in this study is a discussion of fuel nozzle coking, the altitude operating limits with and without the standard engine control, the compressor surge characteristics, and the engine starting and windmilling characteristics. Severe circumferential turbine outlet temperature gradients which occurred at high altitude as a result of fuel nozzle coking were alleviated by the manufacturer's change in the fuel flow divider schedule and in a nozzle gasket material. Compressor air bleed is required to prevent surge of the outboard compressor in the low engine speed region. The maximum altitude at which the engine was operated without the control was about 66,000 feet at 0.8 flight Mach number and at a reduced engine speed to avoid compressor surge; with the engine control in operation, the altitude operating limit is reduced to approximately 59,000 feet. The maximum altitude at which the engine was started was about 40,000 feet.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE54C31
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  • 32
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    Design and Evaluation of a Turbojet Exhaust Simulator, Utilizing a Solid-Propellant Rocket Motor, for use in Free-Flight Aerodynamic Research Models (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A method has been developed for modifying a rocket motor so that its exhaust characteristics simulate those of a turbojet engine. The analysis necessary to the design is presented along with tests from which the designs are evaluated. Simulation was found to be best if the exhaust characteristics to be duplicated were those of a turbojet engine at high altitudes and with the afterburner operative.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-L54I15
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  • 33
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    Experimental Permeability Measurements on a Strut-Supported Transpiration-Cooled Turbine Blade with Stainless-Steel Shell made by the Federal-Mogul Corporation under Bureau of Aeronautics Contract N0as 51613-C (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A turbine blade with a porous stainless-steel shell sintered to a supporting steel strut has been fabricated for tests at the NACA by Federal-Mogul Corporation under contract from the Bureau of Aeronautics, Department of the Navy. The apparent permeability of this blade, on the average, more nearly approaches the values specified by the NAGA than did two strut-supported bronze blades in a previous investigation. Random variations of permeability in the present blade are substantialy greater than those of the bronze blades, but projected improvements in certain phases of the fabrication process are expected to reduce these variations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE54D29
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  • 34
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    Crustal layers of the continents and oceans (1951)
    In:  Bull. Geol. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 62, no. 6, pp. 427-440, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: CRUST ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 35
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    Strain characteristics of the earth's interior (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. XV:, pp. 382-407, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Earth model, also for more shallow analyses ! ; Strain ; TIDES ; (The Earth's free) oscillations
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    BIBLIOGRAPHY SEISMOLOGY
  • 36
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    Colloquium on plastic flow and deformation within the earth (Hershey, Pennsylvania, September 12-14, 1950) (1951)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 32, no. 6, pp. 497-543, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Elasticity ; Rock mechanics ; Rheology ; Fluids ; Earth model, also for more shallow analyses ! ; EOS ; BIBTEX? ; ENDNOTE?
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    BIBLIOGRAPHY SEISMOLOGY
  • 37
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    Internal constitution of the earth - Physic of the earth (1951)
    Dover Publ.
    In:  Dover, 439 pp., Dover Publ., vol. 7, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1951
    Keywords: Handbook of geophysics ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 38
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    Hypotheses on the development of the earth (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. IX:, pp. 178-226, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Earth model, also for more shallow analyses ! ; evolution
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    BIBLIOGRAPHY SEISMOLOGY
  • 39
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    Forces in the earth (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. VIII:, pp. 167-177, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Earth model, also for more shallow analyses ! ; Elasticity ; TIDES ; (The Earth's free) oscillations ; Geothermics
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  • 40
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    Preface (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. VIIa, pp. 438-470, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Review article ; Earth model, also for more shallow analyses !
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  • 41
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    The cooling of the earth and the temperature in its interior (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. VII:, pp. 150-166, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Geothermics ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 42
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    Structure of the crust (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. XII:, pp. 314-339, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: CRUST ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 43
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    Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made using a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and outer-race bearing operating temperatures are compared for the laboratory test rig and the turbojet engine. Inner- and outer-race cooling-correlation curves were obtained for the turbojet-engine turbine-roller bearing with the same inner- and outer-race correlation parameters and exponents as those determined for the laboratory test-rig bearing. The inner- and outer-race turbine roller-bearing temperatures may be predicted from a single curve, regardless of variations in speed, load, oil flow, oil inlet temperature, oil inlet viscosity, oil-jet diameter or any combination of these parameters. The turbojet-engine turbine-roller-bearing inner-race temperatures were 30 to 60 F greater than the outer-race-maximum temperatures, the exact values depending on the operating condition and oil viscosity; these results are in contrast to the laboratory test-rig results where the inner-race temperatures were less than the outer-race-maximum temperatures. The turbojet-engine turbine-roller bearing, maximum outer-race circumferential temperature variation was approximately 30 F for each of the oils used. The effect of oil viscosity on inner- and outer-race turbojet-engine turbine-roller-bearing temperatures was found to be significant. With the lower viscosity oil (6x10(exp -7) reyns (4.9 centistokes) at 100 F; viscosity index, 83), the inner-race temperature was approximately 30 to 35 F less than with the higher viscosity oil (53x10(exp -7) reyns (42.8 centistokes) at 100 F; viscosity index, 150); whereas the outer-race-maximum temperatures were 12 to 28 F lower with the lower viscosity oil over the DN range investigated.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51I05
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  • 44
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    Tests of Two-Blade Propellers in the Langley 8-Foot High-Speed Tunnel to Determine the Effect on Propeller Performance of a Modification of Inboard Pitch Distribution (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of two propellers having two blades and differing only in the inboard pitch distribution were made in the Langley 8-foot highspeed tunnel to determine the effect of inboard pitch distribution on propeller performance. propeller was designed for operation in the reduced velocity region ahead of an NACA cowling; the inboard pitch distribution of the modified propeller was increased for operation at or near free-stream velocities, such as would be obtained in a pusher installation. conditions covering climb, cruise, and high-speed operation. Wake surveys were taken behind the propellers in order to determine the distribution of thrust along the blades and to aid in the analysis of the results. Test results showed that the modified propeller was about 2.5 percent less efficient for a typical climb condition at all altitudes, 2 percent more efficient for one cruise condition, and 5 percent more efficient for high-speed operation. speed condition, the modified propeller showed a 6-percent loss in efficiency due to compressibility; whereas the original propeller showed an 11-percent efficiency loss due to compressiblity. The lower compressibility loss for the modified propeller resulted from the fact that the inboard sections of this propeller could operate at increased thrust loading after compressibility losses had occurred at the outboard sections.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-2268
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  • 45
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    Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is different for each blade, however. The fabrication procedures were varied and often unique. The blades were fabricated using methods most suitable for obtaining a small number of blades for use in the cooling investigations and therefore not all the fabrication procedures would be directly applicable to production processes, although some of the ideas and steps might be useful. Blade shells were obtained by both casting and forming. The cast shells were either welded to the blade base or cast integrally with the base. The formed shells were attached to the base by a brazing and two welding methods. Additional surface area was supplied in the coolant passages by the addition of fins or tubes that were S-brazed. to the shell. A number of blades with special leading- and trailing-edge designs that provided added cooling to these areas were fabricated. The cooling effectiveness and purposes of the various blade configurations are discussed briefly.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51E23 , REPT-2203
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  • 46
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    Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine Performance (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Strain-gages were used to measure blade vibrations causing failures in the third stage of a production 11-stage axial-flow compressor. After the serious third-stage vibration was detected, a series of investigations were conducted with second-stage vane assemblies of varying angles of incidence. Curves presented herein show the effect of varying the angle of incidence of second-stage vane assembly on third-stage rotor-blade vibration amplitude and engine performance. A minimum vibration amplitude was obtained without greatly affecting the engine performance with a second-stage vane assembly of 9deg. greater angle of incidence than the assembly normally furnished with the engine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE51F08
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  • 47
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    Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet. Performance of the engine at any flight Mach number in the range investigated can be predicted for those operating condition a t which critical flow exits in the exhaust nozzle with the exception of the variables corrected net thrust, and net-thrust specific fuel consumption.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E50I15
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  • 48
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    Flight Performance of a Jet Power Plant (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The performance of a jet power plant consisting of a compressor and a turbine is determined by the characteristic curves of these component parts and is controllable by the characteristics of the compressor and the turbine i n relation t o each other. The normal. output, overload, and throttled load of the Jet power plant are obtained on the basis of assumed straight-line characteristics.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1258
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  • 49
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    Graphic Analysis of American and British Axial-Flow Turbojet Engine Performance Trends (Current and Future) (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents a compilation of static sea-level data on existing or designed American and British axial-flow turbojet engines in terms of basic engine parameters such as thrust and air flow. In the data presented, changes in the over-U engine performance with time sre examined as well as the relation of the various engine parameters to each other.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-51K29
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  • 50
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    Matching Characteristics of J35-A-23 Compressor and Two-stage Turbine (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Component data on the J35-A-23 compressor and two-stage turbine were used to determine the problems in matching the two units for operatio n in a turbojet engine. Possible operating regions were determined an d an equilibrium operating line was also determined for the assumed c onditions of zero flight speed and a jet nozzle area approximately 5. 5 percent greater than the wide-open nozzle area.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51H15
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  • 51
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    Control Performance of General Electric Fuel and Torque Regulator Operating on T31-3 Turbine-Propeller Engine in Sea-Level Test Stand (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A .General Electric fuel and torque regulator was tested in conjunction with a T31-3 turbine-propeller engine in the sea-level static test stand at the NACA Lewis laboratory. The engine and control were operated over the entire speed range: 11,000 rpm, nominal flight idle, to 13,000 rpm, full power. Steady-state and transient data were recorded and are presented with a description of the four control loops being used in the system. Results of this investigation indicated that single-lever control operation was satisfactory under conditions of test. Transient data presented showed that turbine-outlet temperature did overshoot maximum operating value on acceleration but that the time duration of overshoot did not exceed approximately 1 second. This temperature limiting resulted from a control on fuel flow as a function of engine speed. Speed and torque first reached their desired values 0.4 second from the time of change in power-setting lever position. Maximum speed overshoot was 3 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE1H20
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  • 52
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    Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Similar data for engine operation i n the afterburning range, covering a range of throttle settings from the minimum value giving rated speed (throttle position, 72 degrees) to full afterburning (throttle position, ll0 degrees), is presented herein. These data thus serve to indicate the transient characteristics of the engine when the throttle is advance into, withdrawn from, and moved within the afterburning range in a stepwise manner, as well as the steady-state stability of the engine during afterburning .
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50L29
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  • 53
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    Factors Affecting the Starting Characteristics of Gas-Turbine Engines (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report summarizes the effects of fuel volatility and engine design variables on the problem of starting gas-turbine engines at sea-level and altitude conditions. The starting operation for engines with tubular combustors is considered as three steps; namely, (1) ignition of a fuel-air mixture in the combustor, (2) propagation of flame through cross-fire tubes to all combustors, and (3) acceleration of the engine from windmilling or starting speed to the operating speed range. Pertinent data from laboratory researches, single-combustor studies, and full-scale engine investigations are presented on each phase of the starting problem.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE51B02
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  • 54
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    Coolant-Flow Calibrations of Three Simulated Porous Gas-Turbine Blades (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was conducted at the NACA Lewis laboratory to determine whether simulated porous gas-turbine blades fabricated by the Eaton Manufacturing Company of Cleveland, Ohio would be satisfactory with respect to coolant flow for application in gas-turbine engines. These blades simulated porous turbine blades by forcing the cooling air onto the blade surface through a large number of chordwise openings or slits between laminations of sheet metal or wire. This type of surface has a finite number of openings, whereas a porous surface has an almost infinite number of smaller openings for the coolant flow. The investigation showed that a blade made of sheet-metal laminations stacked on a support member that passed up through the coolant passage was completely unsatisfactory because of extremely poor coolant flow distribution over the blade surface. The flow distribution for two wire-wound blades was more uniform, but the pressure drop between the coolant supply pressure and the local pressure on the outside of the blades was too low by a factor ranging from 3 to 3.5 for the required coolant flow rates. The pressure drop could be increased by forcing the wires closer together during blade fabrication.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE51C13
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