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  • Aircraft Propulsion and Power
  • 2015-2019  (300)
  • 1945-1949  (126)
  • 1940-1944  (16)
  • 1935-1939  (5)
  • 1
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    NASA Engine Icing Research Overview: Aeronautics Evaluation and Test Capabilities (AETC) Project (2015)
    In:  CASI
    Details
    Publication Date: 2016-12-20
    Description: The occurrence of ice accretion within commercial high bypass aircraft turbine engines has been reported by airlines under certain atmospheric conditions. Engine anomalies have taken place at high altitudes that have been attributed to ice crystal ingestion by the engine. The ice crystals can result in degraded engine performance, loss of thrust control, compressor surge or stall, and flameout of the combustor. The Aviation Safety Program at NASA has taken on the technical challenge of a turbofan engine icing caused by ice crystals which can exist in high altitude convective clouds. The NASA engine icing project consists of an integrated approach with four concurrent and ongoing research elements, each of which feeds critical information to the next element. The project objective is to gain understanding of high altitude ice crystals by developing knowledge bases and test facilities for testing full engines and engine components. The first element is to utilize a highly instrumented aircraft to characterize the high altitude convective cloud environment. The second element is the enhancement of the Propulsion Systems Laboratory altitude test facility for gas turbine engines to include the addition of an ice crystal cloud. The third element is basic research of the fundamental physics associated with ice crystal ice accretion. The fourth and final element is the development of computational tools with the goal of simulating the effects of ice crystal ingestion on compressor and gas turbine engine performance. The NASA goal is to provide knowledge to the engine and aircraft manufacturing communities to help mitigate, or eliminate turbofan engine interruptions, engine damage, and failures due to ice crystal ingestion.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN20926 , Department of Aerospace Engineering and Engineering Mechanics Graduate Seminar; 4 May 2015; Cincinnati, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental Investigation of a One-Sided Ejector Nozzle (2019)
    In:  CASI
    Details
    Publication Date: 2019-05-07
    Description: A fundamental exploratory experiment is conducted assessing the performance of a one-sided ejector with the eventual goal of noise reduction for jet engines. The hardware is comprised of an 8:1 rectangular nozzle together with an ejector box whose lower surface is flush with the lower lip of the nozzle. Secondary flow is allowed through a gap between the upper lip of the nozzle and a flap that constitutes the upper surface of the ejector. Wall static pressures and Pitot probe surveys are conducted to evaluate the performance of the ejector with variation of geometric parameters. It is found that addition of vortex generating tabs at the upper lip of the nozzle significantly increases secondary flow entrainment. The entrainment is further enhanced by a divergence of the ejector upper surface. Limited noise measurements are done. The baseline ejector (without tabs) often encounters flow resonance with accompanying tones. The tabs have the additional benefit of eliminating those tones in all cases. However, for the tabbed case, addition of the ejector produces insignificant further noise reduction. This is due to the fact that the flow remains unmixed on the lower half of the ejector. The focus of ongoing and future efforts is to achieve sufficient mixing of the flow so that the exhaust velocities are uniformly low, while keeping the ejector hardware short and lightweight.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2019-220064 , GRC-E-DAA-TN65186 , E-19654
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Performance Charts for the Turbojet Engine (1947)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet engine for any given set of operating conditions and component efficiencies. The effects of the pressure losses in the inlet duct and combustion chamber, the variation in the physical properties of the gas as it passes through the cycle, and the change in mass flow by the addition of fuel are included. The principle performance charts show the effects of the primary variables and correction charts provide the effects of the secondary variables.
    Keywords: Aircraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    X-57 Maxwell Battery From Cell Level to System Level Design and Testing (2018)
    In:  CASI
    Details
    Publication Date: 2019-03-07
    Description: This presentation is on Electric and Hybrid Electric Propulsion: NASA's Approach, expectations, design and project requirements, and the motivation behind it.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN59208 , BEYOND LITHIUM ION XI; 24-26 Jul. 2018; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Preliminary Investigation Directed Toward Improvement of the NACA Cowling (1942)
    In:  CASI
    Details
    Publication Date: 2018-08-03
    Description: The development of new cowlings, applicable to a short-nose radial engine, is described. These cowlings, designated the NACA cowlings D(sub s) and D(sub sf), employ a larger spinner and a higher inlet-velocity ratio than does the conventional NACA cowling C. The pressures available for cooling and the estimated critical Mach number were found to be higher with the new cowlings than are usually encountered with the conventional NACA cowling C. Large-chord propeller cuffs were found to have a stabilizing effect on the flow entering the cowling and resulted in increased front pressures. Fan blades mounted on the spinner in the inlet opening had a similar effect.
    Keywords: Aircraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Performance Possibilities of the Turbojet System as a Power Plant for Supersonic Airplanes (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The performance of hypothetical turbojet systems, without thrust augmentation, as power plants for supersonic airplanes has been calculated. The thrust, thrust power, air-fuel ratio, 1 specific fuel consumption, cross-sectional area, and thrust coefficient are shown for free-stream Mach numbers from 1.2 to 3. For comparison, the performance of ram-jet systems over the same Mach number range has also been calculated. For Mach numbers between 1.2 and 2 the calculated thrust coefficient of the turbojet system was found to be larger than the estimated drag coefficient, and the specific fuel consumption was calculated to be considerably less than the specific fuel consumption of the ram-jet system. The turbojet system therefore appears to merit consideration as a propulsion method for free-stream Mach numbers between approximately 1.2 and 2.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-L7H05a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    NACA Investigation of a Jet-Propulsion System Applicable to Flight (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-528 , NACA-ACR-L4D26
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Performance Charts for a Turbojet System (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Convenient charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet system. These charts take into account the effects of ram pressure, compressor pressure ratio, ratio of combustion-chamber-outlet temperature to atmospheric temperature, compressor efficiency, turbine efficiency, combustion efficiency, discharge-nozzle coefficient, losses in total pressure in the inlet to the jet-propulsion unit and in the combustion chamber, and variation in specific heats with temperature. The principal performance charts show clearly the effects of the primary variables and correction charts provide the effects of the secondary variables. The performance of illustrative cases of turbojet systems is given. It is shown that maximum thrust per unit mass rate of air flow occurs at a lower compressor pressure ratio than minimum specific fuel consumption. The thrust per unit mass rate of air flow increases as the combustion-chamber discharge temperature increases. For minimum specific fuel consumption, however, an optimum combustion-chamber discharge temperature exists, which in some cases may be less than the limiting temperature imposed by the strength temperature characteristics of present materials.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-241 , NACA-ARR-E6E14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Use of Internal Coolant as a Means of Permitting Increase in Engine Take-Off Power (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that this 25-percent increase in power will permit an approximate usable increase of 8.5 percent in the take-off load of existing military airplanes. This increase in load is equivalent to an increase in the weight of gasoline normally carried of between 30 and 65 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-117 , NACA-RB-4A25
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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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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