NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Performance with and without inlet radial distortion of a transonic fan stage designed for reduced loading in the tip regionA transonic compressor stage designed for a reduced loading in the tip region of the rotor blades was tested with and without inlet radial distortion. The rotor was 50 cm in diameter and designed for an operating tip speed of 420 m/sec. Although the rotor blade loading in the tip region was reduced to provide additional operating range, analysis of the data indicates that the flow around the damper appears to be critical and limited the stable operating range of this stage. For all levels of tip and hub radial distortion, there was a large reduction in the rotor stall margin.
Document ID
19780022114
Document Type
Technical Publication (TP)
Authors
Schmidt, J. F.
(NASA Lewis Research Center Cleveland, OH, United States)
Ruggeri, R. S.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
E-9246
NASA-TP-1294
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 19780022114.pdf STI
No Preview Available