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  • 1
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    Energy efficient engine low-pressure compressor component test hardware detailed design report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic and mechanical design description of the low pressure compressor component of the Energy Efficient Engine were used. The component was designed to meet the requirements of the Flight Propulsion System while maintaining a low cost approach in providing a low pressure compressor design for the Integrated Core/Low Spool test required in the Energy Efficient Engine Program. The resulting low pressure compressor component design meets or exceeds all design goals with the exception of surge margin. In addition, the expense of hardware fabrication for the Integrated Core/Low Spool test has been minimized through the use of existing minor part hardware.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165354 , NAS 1.26:165354 , PWA-5594-157
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Energy efficient engine fan component detailed design report (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The fan component which was designed for the energy efficient engine is an advanced high performance, single stage system and is based on technology advancements in aerodynamics and structure mechanics. Two fan components were designed, both meeting the integrated core/low spool engine efficiency goal of 84.5%. The primary configuration, envisioned for a future flight propulsion system, features a shroudless, hollow blade and offers a predicted efficiency of 87.3%. A more conventional blade was designed, as a back up, for the integrated core/low spool demonstrator engine. The alternate blade configuration has a predicted efficiency of 86.3% for the future flight propulsion system. Both fan configurations meet goals established for efficiency surge margin, structural integrity and durability.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165466 , NAS 1.26:165466 , PWA-5594-165
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    High-loading, 1800 ft/sec tip speed transonic compressor fan stage. 1: Aerodynamic and mechanical design (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A single stage fan with a tip speed of 1800 ft/sec (548.6m/sec) and hub/tip ratio of 0.5 was designed to produce a pressure ratio of 2.285:1 with an adiabatic efficiency of 84.0%. The design flow per inlet annulus area is 38.7 lbm/sq ft-sec (188.9KG/sqm-sec). Rotor blades have modified multiple-circular-arc and precompression airfoil sections. The stator vanes have multiple-circular-arc airfoil sections.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-120907 , PWA-4534
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Redesigned rotor for a highly loaded, 1800 ft/sec tip speed compressor fan stage 1: Aerodynamic and mechanical design (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A highly loaded, high tip-speed fan rotor was designed with multiple-circular-arc airfoil sections as a replacement for a marginally successful rotor which had precompression airfoil sections. The substitution of airfoil sections was the only aerodynamic change. Structural design of the redesigned rotor blade was guided by successful experience with the original blade. Calculated stress levels and stability parameters for the redesigned rotor are within limits demonstrated in tests of the original rotor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134835 , PWA-5266
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Ultra high tip speed (670.6 m/sec) fan stage with composite rotor: Aerodynamic and mechanical design (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A highly loaded, single-stage compressor having a tip speed of 670.6 m/sec was designed for the purpose of investigating very high tip speeds and high aerodynamic loadings to obtain high stage pressure ratios at acceptable levels of efficiency. The design pressure ratio is 2.8 at an adiabatic efficiency of 84.4%. Corrected design flow is 83.4 kg/sec; corrected design speed is 15,200 rpm; and rotor inlet tip diameter is 0.853 m. The rotor uses multiple-circular-arc airfoils from 0 to 15% span, precompression airfoils assuming single, strong oblique shocks from 21 to 43% span, and precompression airfoils assuming multiple oblique shocks from 52% span to the tip. Because of the high tip speeds, the rotor blades are designed to be fabricated of composite materials. Two composite materials were investigated: Courtaulds HTS graphite fiber in a Kerimid 601 polyimide matrix and the same fibers in a PMR polyimide matrix. In addition to providing a description of the aerodynamic and mechanical design of the 670.0 m/sec fan, discussion is presented of the results of structural tests of blades fabricated with both types of matrices.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135122 , PWA-5487
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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