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Effect of Various Blade Modifications on Performance of a 16-Stage High-pressure-ratio Axial-flow Compressor.Angles 3 deg: Effect on Over-all Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-blade Angles 3 deg - 1The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.
Document ID
20090025405
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Medeiros, Arthur A. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Hatch, James E. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Dugan, James F., Jr. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 24, 2013
Publication Date
January 1, 1952
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E51L03
Report Number: NACA-RM-E51L03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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