NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Inlet flow distortion in turbomachinery. I - Comparison of theory and experiment in a transonic fan stage. II - A parameter studyIn the present paper, a semi-actuator-disk theory is reviewed that was developed previously for the distorted inflow to a single-stage axial-flow compressor. Flow distortion occurs far upstream; it may be a distortion in stagnation temperature, stagnation pressure, or both. Losses, quasi-steady deviation angles, and reference incidence correlations are included in the analysis, and both subsonic and transonic relative Mach numbers are considered. The theory is compared with measurements made in a transonic fan stage, and a parameter study is carried out to determine the influence of solidity on the attenuation of distortions in stagnation pressure and stagnation temperature.
Document ID
19800054725
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seidel, B. S.
(Delaware Univ. Newark, DE, United States)
Matwey, M. D.
(Delaware, University Newark, Del., United States)
Adamczyk, J. J.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-1076
Meeting Information
Meeting: Joint Propulsion Conference
Location: Hartford, CT
Start Date: June 30, 1980
End Date: July 2, 1980
Sponsors: AIAA, SAE, and ASME,
Accession Number
80A38895
Funding Number(s)
CONTRACT_GRANT: NSG-3189
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available