Publication Date:
2019-06-27
Description:
A series of high hub tip radius ratio compressor stages representative of the middle and latter stages of axial flow compressors is discussed. The effects of aspect ratio, diffusion factor, and solidity on rotor and stage performance are determined. Fourteen middle stages are tested to study the effects on performance of varying both diffusion through the rotor and stator blades and blade aspect ratio. The design parameters in the streamline analysis program, the blade geometry program, and the blade coordinate program are presented.
Keywords:
AIRCRAFT PROPULSION AND POWER
Type:
NASA-TP-1523
,
E-9943
Format:
application/pdf
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