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Performance of a single-stage axial-flow transonic compressor stage with a blade tip solidity of 1.7The overall and blade-element performance of a transonic compressor stage is presented over the stable operating range at rotative speeds from 50 to 100 percent of design speed. Stage peak efficiency of 0.784 was obtained at a weight flow of 28.6 kilograms per second and a pressure ratio of 1.706. Stall margin at design speed was 11.4 percent. The peak efficiency being significantly less than design efficiency was attributed to: (1) the stator loss and the radial gradient of losses being much higher than design, (2) the losses and blockages associated with the rotor part-span dampers not being incorporated into the design, and (3) mismatch of the rotor and stator badle elements.
Document ID
19730006256
Document Type
Technical Memorandum (TM)
Authors
Moore, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Reid, L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
December 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
E-6730
NASA-TM-X-2658
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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