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  • 1
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    Advanced secondary power system for transport aircraft (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A concept for an advanced aircraft power system was identified that uses 20-kHz, 440-V, sin-wave power distribution. This system was integrated with an electrically powered flight control system and with other aircraft systems requiring secondary power. The resulting all-electric secondary power configuration reduced the empty weight of a modern 200-passenger, twin-engine transport by 10 percent and the mission fuel by 9 percent.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-2463 , E-2434 , NAS 1.60:2463
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Small, low-cost, expendable turbojet engine. 1: Design, fabrication, and preliminary testing (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A small experimental axial-flow turbojet engine in the 2,669-Newton (600-lbf) thrust class was designed, fabricated, and tested to demonstrate the feasibility of several low-cost concepts. Design simplicity was stressed in order to reduce the number of components and machining operations. Four engines were built and tested for a total of 157 hours. Engine testing was conducted at both sea-level static and simulated flight conditions for engine speeds as high as 38,000 rpm and turbine-inlet temperatures as high as 1,255 K (1,800 F).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3392 , E-8590
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Small, low cost, expendable turbojet engine. 2: Performance characteristics (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A small experimental axial-flow turbojet engine was tested at sea level static conditions and over a range of simulated flight conditions to evaluate its performance as well as to demonstrate the feasibility of low-cost concepts utilized in its design. Testing was conducted at engine speeds as high as 37,000 rpm and at turbine inlet temperatures as high as 1,272 K. For maximum speed the engine produced a net thrust of 3,118 newtons at sea level static operation and 2,318 newtons at its cruise condition of M0 = 0.8 and 6,096 meters. Data obtained over a range of inlet Reynolds number indexes for nominal M0 of 0.38 revealed similar effects or trends on compressor characteristics of those previously established for much larger engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3463 , E-8775
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experience with integrally-cast compressor and turbine components for a small, low-cost, expendable-type turbojet engine (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Experiences with integrally-cast compressor and turbine components during fabrication and testing of four engine assemblies of a small (29 cm (11 1/2 in.) maximum diameter) experimental turbojet engine design for an expendable application are discussed. Various operations such as metal removal, welding, and re-shaping of these components were performed in preparation of full-scale engine tests. Engines with these components were operated for a total of 157 hours at engine speeds as high as 38,000 rpm and at turbine inlet temperatures as high as 1256 K (1800 F).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71782 , E-8441 , Presentation at 1975 Aerospace Eng. and Manuf. Meeting; Nov 17, 1975 - Nov 20, 1975; Los Angeles, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The aerodynamic design and performance of the NASA/GE E3 low pressure turbine (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic design and scaled rig test results of the low pressure turbine (LPT) component for the NASA/General Electric Energy Efficient Engine (E3) are presented. The low pressure turbine is a highly loaded five-stage design featuring high outer wall slope, controlled vortex aerodynamics, low stage flow coefficient, and reduced clearances. An assessment of its performance has been made based on a series of scaled air turbine tests which were divided into two phases: Block I (March through August, 1979) and Block II (June through September, 1981). Results from the Block II five-stage test, summarized in the paper, indicate that the E3 LPT will attain an efficiency level of 91.5 percent at the Mach 0.8/35,000 ft. max. climb altitude design point. This is relative to program goals of 91.1 percent for the E3 demonstrator engine and 91.7 percent for a fully developed flight propulsion system LPT.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1162
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Experience with integrally-cast compressor and turbine components for a small, low-cost, expendable-type turbojet engine (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A discussion regarding experiences with integrally-cast compressor and turbine components during fabrication and testing of four engine assemblies of a small (29 cm (11-1/2 in.) maximum diameter) experimental turbojet engine design for an expendable application is presented. Various operations such as metal removal, welding, and re-shaping of these components are performed in preparation of full-scale engine tests. Engines with these components have been operated for a total of 157 hours at engine speeds as high as 38,000 rpm and at turbine inlet temperatures as high as 1256 K (1800 F).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 751048 , National Aerospace Engineering and Manufacturing Meeting; Nov 17, 1975 - Nov 20, 1975; Culver City, CA
    Format: text
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    NASA TECHNICAL REPORTS
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