Upstream wake influences on the measured performance of a transonic compressor stage

Journal of Propulsion and Power

Volumn 17, Issue 1, 2001, Pages 43-48

  Gorrell, S E ^a   Copenhaver, W W ^a   Chriss, R M ^b  

^a AIR FORCE RESEARCH LABORATORY   (United States)

^b NASA GLENN RESEARCH CENTER   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

COMPUTER SIMULATION; NUMERICAL ANALYSIS; PERFORMANCE; PRESSURE MEASUREMENT; ROTORS; STATORS; TEMPERATURE MEASUREMENT; WAKES;

STAGE MATCHING INVESTIGATION; TRANSONIC AXIAL COMPRESSOR;

COMPRESSORS;

EID: 0034845629     PISSN: 07484658     EISSN: None     Source Type: Journal    
DOI: 10.2514/2.5705     Document Type: Article

References (14)

1. Casing boundary layers in multistage axial flow compressors
2. The practical importance of unsteady flow
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4. Wake ingestion propulsion benefit
5. Impact of rotor wakes on steady-state axial compressor performance
6. Wake recovery performance benefit in a high-speed axial compressor
7. Wake mixing in axial flow compressors
8. Recommended practices for measurement of gas path pressures and temperatures for performance assessment of aircraft turbine engines and components
9. Unsteady viscous flow in a high-speed core compressor
10. Turbulence intensity and length scale measurements in multistage compressors
11. Two axial compressor designs for a stage matching investigation
12. Design and test of a low aspect ratio fan stage
13. Effect of upstream rotor vortical disturbances on the time-averaged performance of axial compressor stators, Part 1: Framework of technical approach and wake-stator blade interactions
14. Investigation of flow phenomena in a transonic fan rotor using laser anemometry