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Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine PerformanceStrain-gages were used to measure blade vibrations causing failures in the third stage of a production 11-stage axial-flow compressor. After the serious third-stage vibration was detected, a series of investigations were conducted with second-stage vane assemblies of varying angles of incidence. Curves presented herein show the effect of varying the angle of incidence of second-stage vane assembly on third-stage rotor-blade vibration amplitude and engine performance. A minimum vibration amplitude was obtained without greatly affecting the engine performance with a second-stage vane assembly of 9deg. greater angle of incidence than the assembly normally furnished with the engine.
Document ID
20050019444
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Meyer, Andre J., Jr. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Calvert, Howard F. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 22, 2013
Publication Date
June 12, 1951
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-SE51F08
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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