NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Overall and blade-element performance of a transonic compressor stage with multiple-circular-arc blades at tip speed of 419 meters per secondA 50-centimeter-diameter axial-flow transonic compressor stage with multiple-circular-arc blades was designed and tested to study the effects of blade shape on efficiency and stall margin. At design speed, peak efficiency of 0.80 occurred at an equivalent weight flow of 29.0 kilograms per second. Measured total pressure ratio and total temperature ratio at peak efficiency were 1.69 and 1.20, respectively. The stall margin at design speed and an equivalent weight flow of 29.0 kilograms per second was 9 percent. The measured stall margin at design weight flow and speed was 15 percent. A comparison of rotor performance made with and without the stator showed a decrease in pressure ratio, peak efficiency, and maximum weight flow with the addition of the stator.
Document ID
19730011268
Document Type
Technical Memorandum (TM)
Authors
Kovich, G.
(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
March 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-2731
E-6823
Funding Number(s)
PROJECT: RTOP 502-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 19730011268.pdf STI
No Preview Available