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  • 1
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    The aerodynamic design and performance of the General Electric/NASA EEE fan (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic design and test results of the fan and quarter-stage component for the GE/NASA Energy Efficient Engine (EEE) are presented. The fan is a high bypass ratio, single-stage design having 32 part-span shrouded rotor blades, coupled with a unique quarter-stage arrangement that provides additional core-stream pressure ratio and particle separation. The fan produces a bypass pressure ratio of 1.65 at the exit of the low aspect ratio vane/frame and a core-stream pressure ratio of 1.67 at the entrance to the core frame struts. The full-scale fan vehicle was instrumented, assembled and tested as a component in November 1981. Performance mapping was conducted over a range of speeds and bypass ratios using individually-controlled bypass and core-stream discharge valves. The fan bypass and core-stream test data showed excellent results, with the fan exceeding all performance goals at the important engine operating conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1160
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Performance of a 1380-foot-per-second-tip-speed axial-flow compressor rotor with a blade tip solidity of 1.3 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic design parameters are presented along the overall and blade element performance, of an axial flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.844 and occurred at an equivalent weight flow of 63.5 lb/sec with a total pressure ratio of 1.801. Design efficiency, pressure ratio, and weight flow 0.814, 1.65, and 65.3(41.1 lb/sec/sq ft of annulus area), respectively. Stall margin for design speed was 6.4 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2448 , E-6503
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Performance of 1380-foot-per-second tip-speed axial-flow compressor rotor with blade tip solidity of 1.1 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic design parameters are presented along with the overall and blade element performance, of an axial-flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.853 and occured at an equivalent weight flow of 65.7lb/sec. The total pressure ratio was 1.68. Design efficiency, weight flow, pressure ratio, and temperature ratio were 0.822, 65.3, 1.65, and 1.187, respectively. Stall margin for design speed was 14 percent based on the weight flows and pressure ratios at peak efficiency and just prior to stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2449 , E-6686
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effects of four inlet and outlet tip-annulus-area blockage configurations on the performance of an axial-flow fan rotor (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An axial-flow fan rotor was tested with four configurations of tip-annulus-area blockage to speeds as high as 0.8 of design speed. The rotor performance with the four blockage configurations is compared with the unblocked rotor performance and with blockage configurations previously investigated. The blockage configurations enable the rotor to operate in a stable condition, to much lower flows than the unblocked rotor, with no evidence of rotating stall. The blockage configurations were effective in reducing rotor torque and weight flow but were accompanied by reductions in pressure ratio and efficiency.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8131 , E-8466
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Test of a cracked compressor blade repaired by electron beam welding (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Feasibility of electron beam welding for repairing cracked compressor blades
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TM-X-1341
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Analysis of internal flow of J85-13 multistage compressor (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Interstage data recorded on a J85-13 engine were used to analyze the internal flow of the compressor. Measured pressures and temperatures were used as input to a streamline analysis program to calculate the velocity diagrams at the inlet and outlet of each blade row. From the velocity diagrams and blade geometry, selected blade-element performance parameters were calculated. From the detailed analysis it is concluded that the compressor is probably hub critical (stall initiates at the hub) in the latter stages for the design speed conditions. As a result, the casing treatment over the blade tips has little or no effect on stall margin at design speed. Radial inlet distortion did not appear to change the flow in the stages that control stall because of the rapid attenuation of the distortion within the compressor.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3513 , E-8493
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall and blade-element performance of two configurations of a moderately high aspect ratio transonic compressor rotor are presented. The subject rotor has conventional blade dampers. The performance is compared with a rotor utilizing dual wire friction dampers. At design speed the subject achieved a pressure ratio of 1.52 and efficiency of 0.89 at a near design weight flow of 72.1 pounds per second. The rotor with wire dampers gave consistently higher pressure ratios at each speed, but efficiencies for the two rotors were about the same. Stall margin for the subject rotor was 20.4 percent, but for the wire damped rotor only 4.0 percent.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3041 , E-7068
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Use of wire lacing to reduce blade vibration in an axial-flow compressor rotor (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Stress analysis and wear tests in use of lacing wire as vibration damper on turbocompressor blades
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-1603
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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