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  • Aircraft Propulsion and Power
  • 1995-1999  (51)
  • 1950-1954  (3)
  • 1945-1949  (7)
  • 1930-1934  (1)
  • 11
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    Elevated Temperature Ballistic Impact Testing of PBO and Kevlar Fabrics for Application in Supersonic Jet Engine Fan Containment Systems (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Ballistic impact tests were conducted on fabric made from both Poly(phenylene benzobizoxazole) (PBO) and Kevlar 29 which were selected to be similar in weave pattern, areal density, and fiber denier. The projectiles were 2.54-cm- (1-in.-) long aluminum cylinders with a diameter of 1.27 cm (0.5 in.). The fabric specimens were clamped on four sides in a 30.5-cm- (12-in.-) square frame. Tests on PBO were conducted at room temperature and at 260 C (500 F). A number of PBO specimens were aged in air at 204 and 260 C (400 and 500 F) before impact testing. Kevlar specimens were tested only at room temperature and with no aging. The PBO absorbed significantly more energy than the Kevlar at both room and elevated temperatures. However, after aging at temperatures of 204 C (400 F) and above, the PBO fabric lost almost all of its energy absorbing ability. It was concluded that PBO fabric is not a feasible candidate for fan containment system applications in supersonic jet engines where operating temperatures exceed this level.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-107532 , NAS 1.15:107532 , E-10852
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Flight and Static Exhaust Flow Properties of an F110-GE-129 Engine in an F-16XL Airplane During Acoustic Tests (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The exhaust flow properties (mass flow, pressure, temperature, velocity, and Mach number) of the F110-GE-129 engine in an F-16XL airplane were determined from a series of flight tests flown at NASA Dryden Flight Research Center, Edwards, California. These tests were performed in conjunction with NASA Langley Research Center, Hampton, Virginia (LARC) as part of a study to investigate the acoustic characteristics of jet engines operating at high nozzle pressure conditions. The range of interest for both objectives was from Mach 0.3 to Mach 0.9. NASA Dryden flew the airplane and acquired and analyzed the engine data to determine the exhaust characteristics. NASA Langley collected the flyover acoustic measurements and correlated these results with their current predictive codes. This paper describes the airplane, tests, and methods used to determine the exhaust flow properties and presents the exhaust flow properties. No acoustics results are presented.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-104326 , H-2122 , NAS 1.15:104326
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Development of an Intelligent Monitoring and Control System for a Heterogeneous Numerical Propulsion System Simulation (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The NASA Numerical Propulsion System Simulation (NPSS) project is exploring the use of computer simulation to facilitate the design of new jet engines. Several key issues raised in this research are being examined in an NPSS-related research project: zooming, monitoring and control, and support for heterogeneity. The design of a simulation executive that addresses each of these issues is described. In this work, the strategy of zooming, which allows codes that model at different levels of fidelity to be integrated within a single simulation, is applied to the fan component of a turbofan propulsion system. A prototype monitoring and control system has been designed for this simulation to support experimentation with expert system techniques for active control of the simulation. An interconnection system provides a transparent means of connecting the heterogeneous systems that comprise the prototype.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-202435 , NAS 1.26:202435
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    High-speed engine/component performance assessment using exergy and thrust-based methods (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation summarizes a comparative study of two high-speed engine performance assessment techniques based on energy (available work) and thrust-potential (thrust availability). Simple flow-fields utilizing Rayleigh heat addition and one-dimensional flow with friction are used to demonstrate the fundamental inability of conventional energy techniques to predict engine component performance, aid in component design, or accurately assess flow losses. The use of the thrust-based method on these same examples demonstrates its ability to yield useful information in all these categories. Energy and thrust are related and discussed from the stand-point of their fundamental thermodynamic and fluid dynamic definitions in order to explain the differences in information obtained using the two methods. The conventional definition of energy is shown to include work which is inherently unavailable to an aerospace Brayton engine. An engine-based energy is then developed which accurately accounts for this inherently unavailable work; performance parameters based on this quantity are then shown to yield design and loss information equivalent to the thrust-based method.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-198271 , NAS 1.26:198271
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Influence of Geometry and Flow Variations on NO Formation in the Quick Mixer of a Staged Combustor (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Staged combustion, such as Rich-Burn/Quick-Mix/Lean-Burn (RQL), is a viable strategy to meet nitric oxide (NO) emission goals for both stationary and propulsion gas turbine engines. A critical element of the design is the quick mixer section where the potential for NO production is high. While numerical calculations of the quick mixer under reacting conditions have been conducted, the hostile environment and lack of appropriate diagnostics have, to date, precluded experimental probing of the reacting case. As an alternative to understanding the effect of geometry and flow variations on the production of NO in the quick mixer, the present paper presents (1) a series of non-reacting parametric studies, and (2) a computational method to extrapolate the results of the non-reacting experiments to reacting conditions. The results show that the rate of NO production is highest in the immediate vicinity of the injection plane. For a given momentum flux ratio between the jets and mainstream, the most effective mixing geometry is that which mixes effectively in both (1) the plane of injection, and (2) the wall regions downstream of the plan of injection. The tailoring of the mixing is key to minimize the NO formed. As a result, the best overall mixer with respect to the minimization of NO production may depend on the system specific characteristics of the particular application.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-105639 , E-6985 , NAS 1.15:105639
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Two-Dimensional Bifurcated Inlet/Engine Tests Completed in 10- by 10-Foot Supersonic Wind Tunnel (1999)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: A Two-Dimensional Bifurcated (2DB) Inlet was successfully tested in NASA Lewis Research Center s 10- by 10-Foot Supersonic Wind Tunnel. These tests were the culmination of a collaborative effort between the Boeing Company, General Electric, Pratt & Whitney, and Lewis. Extensive support in-house at Lewis contributed significantly to the progress and accomplishment of this test. The results, which met or exceeded many of the High-Speed Research (HSR) Program goals, were used to revise system studies within the HSR Program. The HSR Program is focused on developing low-noise, low-polluting, high-efficiency supersonic commercial aircraft. A supersonic inlet is an important component of an efficient, low-noise vehicle.
    Keywords: Aircraft Propulsion and Power
    Type: Research and Technology 1998; NASA/TM-1999-208815
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Some Characteristics of Sprays Obtained from Pintle-type Injection Nozzles (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests made with the pintle-type injection nozzles, one having a pintle angle of 8 degrees, the other a pintle angle of 30 degrees. The fuel was injected into a glass-windowed pressure chamber and the spray photographed by means of the N.A.C.A. spray photography apparatus. Curves are presented that give the penetration of the spray tips when fuel oil is injected by pressures of 1,500 to 4,000 pounds per square inch into air at room temperature and densities of 11 to 18 atmospheres. High-speed spark photographs show the appearance of the sprays in air at a density of 18 atmospheres. The results indicate that the pintle angles have little effect on the size of the spray cone angle, which is about the same as that of sprays from plain round hole orifices. The penetration of the spray from the nozzle with an 8 degree pintle is slightly higher than that of the spray from the nozzle with a 30 degree pintle. The penetration of the sprays from the pintle nozzles, for comparable conditions of injection pressure and air density, is about the same as that of sprays from round-hole orifices. Increase in air density decreases the penetration in about the same ratio with all the injection pressures.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-465
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine I : Cooling Characteristics (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differed slightly in that the barrel of the single-cylinder engine runs cooler than the barrel of te flight engine for the same head temperatures and engine conditions.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-271 , NACA-MR-E5J04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Effect of Maximum Cruise-power Operation at Ultra-lean Mixture and Increased Spark Advance on the Mechanical Condition of Cylinder Components (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A continuous 50-hour test was conducted to determine the effect of maximum cruise-power operation at ultra-lean fuel-air mixture and increased spark advance on the mechanical conditions of cylinder components. The test was conducted on a nine-cylinder air-cooled radial engine at the following conditions:brake horsepower, 750; engine speed, 1900 rpm; brake mean effective pressure, 172 pounds per square inch; fuel-air ratio, 0.052; spark advance, 30 deg B.T.C.; and maximum rear-spark-plug-bushing temperature, 400 F. In addition to the data on corrosion and wear, data are presented and briefly discussed on the effect of engine operation at the conditions of this test on economy, knock, preignition, and mixture distribution. Cylinder, piston, and piston-ring wear was small and all cylinder component were in good condition at the conclusion of the 50-hour test except that all exhaust-valve guides were bellmouthed beyond the Army's specified limit and one exhaust-valve face was lightly burned. It is improbable that the light burning in one spot of the valve face would have progressed further because the burn was filled with a hard deposit so that the valve face formed an unbroken seal and the mating seat showed no evidence of burning. The bellmouthing of the exhaust-valve guides is believed to have been a result of the heavy carbon and lead-oxide deposits, which were present on the head end of the guided length of the exhaust-valve stem. Engine operational the conditions of this test was shown to result In a fuel saving of 16.8 percent on a cooled-power basis as compared with operation at the conditions recommended for this engine by the Army Air Forces for the same power.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-268 , NACA-MR-5I27a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    Numerical Evaluation of the Wake-Survey Equations for Subsonic Flow Including the Effect of Energy Addition (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-5 , NACA-ARR-L5H27
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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