Publication Date:
2019-07-12
Description:
The 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.
Keywords:
Aircraft Propulsion and Power
Type:
NACA-RM-E51L03
Format:
application/pdf