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The effect of rotor blade thickness and surface finish on the performance of a small axial flow turbineAn experimental investigation was conducted to determine the effect of blade profile inaccuracies and surface finish on the aerodynamic performance of a 11.13 cm tip diameter turbine. The as-received cast rotor blades had a significantly thicker profile than the design intent and a fairly rough surface finish. Stage test results showed an increase of one point in efficieny by smoothing the surface finish and another three points by thinning the blade profiles to near the design profile. Most of the performance gain between the as-cast thick and the thinned rotor blades both with the same surface finish, was attributed to reduced trailing edge losses of the recontoured blades.
Document ID
19820005241
Document Type
Conference Paper
Authors
Roelke, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Haas, J. E. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1982
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-TM-82726
TR-81-C-29
DOE/NASA/51040-34
Meeting Information
Gas Turbine Ann. Meeting,(London)
Funding Number(s)
CONTRACT_GRANT: DE-AI01-77CS-51040
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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