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)