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  • Aircraft Propulsion and Power  (40)
  • ASTROPHYSICS
  • LC QA3
  • 1955-1959  (43)
  • 11
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    Aircraft-Fuel-Tank Design for Liquid Hydrogen (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E55F22
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Adaptation of Combustion Principles to Aircraft Propulsion (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E54I07
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    A Preliminary Investigation of the Performance of a Short-length Turbojet Combustor Using Vaporized Hydrocarbon Fuels (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors. The over-all combustion lengths, for the two configurations were 13.5 and 11.0 inches, approximately one-half the length of the shortest conventional combustors. These short combustors did not provide combustion efficiencies as high as those for conventional combustors at low pressures. However, over the range of combustor-inlet total-pressures expected in aircraft capable of flight at Mach numbers of 2.5 and above, these short combustors gave very high efficiencies. A combustion efficiency of 97 percent was obtained at a combustor-inlet total-pressure of 25.0 inches of mercury absolute, reference velocity of 120 feet per second, and inlet-air total temperature of 1160 deg R. By proportioning the fuel flow between the manifold rows of can combustor elements, control of the combustor-outlet radial total-temperature profile was demonstrated. Combustor totalpressure loss varied from 0.75 percent of the inlet total pressure at isothermal conditions and a reference velocity of 75 feet per second to 5.5 percent at a total-temperature ratio of 1.8 and a reference velocity of 180 feet per second.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E57J03
    Format: application/pdf
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  • 14
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    Turbine Engines for High-Speed Flight (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This analysis investigates the application of gas turbine engines at a cruise Mach number of 4.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-60935 , NACA-C-8548
    Format: application/pdf
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  • 15
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    Some Effects of Rapid Inlet Pressure Oscillation on the Operation of a Turbojet Engine (1958)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A program was conducted in an altitude facility at the NACA Lewis laboratory to investigate the effects of rapid inlet pressure oscillations on the operation of a current turbo jet engine. These pressure oscillations were approximately sinusoidal in form and were generated to cover a frequency range of 2 to 75 cycles per second and an amplitude range of 10 to 70 percent of the free-stream total pressure. As the oscillation progressed through the compressor, the amplitude was attenuated considerably and a relatively large phase shift (lag) occurred. Engine stall limits obtained during pressure oscillations differed from quasi-steady-state stall limits as defined by over-all compressor pressure ratio.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E58A03
    Format: application/pdf
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  • 16
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    Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The multistage turbine from the J73 turbojet engine has previously been investigated with standard and with reduced-chord rotor blading in order to determine the individual performance characteristics of each configuration over a range of over-all pressure ratio and speed. Because both turbine configurations exhibited peak efficiencies of over 90 percent, and because both units had relatively wide efficient operating ranges, it was considered of interest to determine the performance of the first stage of the turbine as a separate component. Accordingly, the standard-bladed multistage turbine was modified by removing the second-stage rotor disk and stator and altering the flow passage so that the first stage of the unit could be operated independently. The modified single-stage turbine was then operated over a range of stage pressure ratio and speed. The single-stage turbine operated at a peak brake internal efficiency of over 90 percent at an over-all stage pressure ratio of 1.4 and at 90 percent of design equivalent speed. Furthermore, the unit operated at high efficiencies over a relatively wide operating range. When the single-stage results were compared with the multistage results at the design operating point, it was found that the first stage produced approximately half the total multistage-turbine work output.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E53L28A
    Format: application/pdf
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  • 17
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    Over-All Performance of J65-B3 Turbojet Engine for Reynolds Number Indices from 0.8 to 0.2 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The steady-state over-all performance characteristics of the J65-B3 turbojet engine were determined in an altitude test chamber for four exhaust-nozzle areas at Reynolds number indices of 0.8, 0.4, and 0.2. This range of Reynolds number indices corresponds to a range of altitudes from about sea level to 51,500 feet at a flight Mach number of 0.8. Generalized data are presented to allow calculation of engine performance at any flight condition corresponding to a Reynolds number index within the range investigated. Engine performance calculated from these generalized data is presented for seven altitudes over a range of flight speeds from zero to about 1100 knots. The use of an exhaust nozzle sized to give rated perforce at sea level would permit operation near the point of minimum specific fuel consumption for a wide range of flight conditions and engine speeds.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE55C08
    Format: application/pdf
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  • 18
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    Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in a representative nonafterburning position. Jet-thrust and air-handling data were obtained in quiescent air for 11 selected ejector configurations over a wide range of operation. Additional data, at specific operating conditions, were obtained which indicate the ejector diameter ratio for peak jet-thrust performance. The experimental ejector data are presented in both graphical and tabulated form.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E56E23
    Format: application/pdf
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  • 19
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    Altitude Performance of Modified J71 Afterburner with Revised Engine Operating Conditions (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was conducted in an altitude test chamber at the NACA Lewis laboratory to determine the effect of a revision of the rated engine operating conditions and modifications to the afterburner fue1 system, flameholder, and shell cooling on the augmented performance of the J71-A-2 (x-29) turbo jet engine operating at altitude . The afterburner modifications were made by the manufacturer to improve the endurance at sea-level, high-pressure conditions and to reduce the afterburner shell temperatures. The engine operating conditions of rated rotational speed and turbine-outlet gas temperature were increased. Data were obtained at conditions simulating flight at a Mach number of 0.9 and at altitudes from 40,000 to 60,000 feet. The afterburner modifications caused a reduction in afterburner combustion efficiency. The increase in rated engine speed and turbine-outlet temperature coupled with the afterburner modifications resulted in the over-all thrust of the engine and afterburner being unchanged at a given afterburner equivalence ratio, while the specific fuel consumption was increased slightly. A moderate shift in the range of equivalence ratios over which the afterburner would operate was encountered, but the maximum operable altitude remained unaltered. The afterburner-shell temperatures were also slightly reduced because of the modifications to the afterburner.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE55D12
    Format: application/pdf
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  • 20
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    Aerodynamic Design of Axial-Flow Compressors. VII - Blade-Element Flow in Annular Cascades (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Annular blade-element data obtained primarily from single-stage compressor installations are correlated over a range of inlet Mach numbers and cascade geometry. The correlation curves are presented in such a manner that they are related directly to the low-speed two-dimensional-cascade data of part VI of this series. Thus, the data serve as both an extension and a verification of the two-dimensional-cascade data. In addition, the correlation results are applied to compressor design.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E55G02
    Format: application/pdf
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