Inlet flow distortion in turbomachineryA single stage axial compressor with distorted inflow is studied. The inflow distortion occurs far upstream and may be a distortion in stagnation temperature, stagnation pressure or both. The blade rows are modeled as semi-actuator disks. Losses, quasi-steady deviation angles, and reference incidence correlations are included in the analysis. Both subsonic and transonic relative Mach numbers are considered. A parameter study is made to determine the influence of such variables as Mach number and swirl angle on the attenuation of the distortion.
Document ID
19810033548
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 11, 2013
Publication Date
March 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 80-GT-20
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: New Orleans, LA
Start Date: March 10, 1980
End Date: March 13, 1980
Sponsors: American Society of Mechanical Engineers