Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 2 - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 Degrees
Description:
The stator-blade angles in the twelfth through fifteenth stages of a 16-stage axial-flow compressor were increased 3O. The over-all performance of this modified compressor is compared to the performance of the compressor with original blade angles. The matching characteristics of the modified compressor and a two-stage turbine were obtained and compared to those of the compressor with original blade angles and the same turbine.
Date:
January 5, 1952
Creator:
Hatch, James E. & Medeiros, Arthur A.
Item Type:
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Partner:
UNT Libraries Government Documents Department