A Navier-Stokes Analysis of a Controlled-Diffusion Compressor Cascade at Increasing Flow Angles
Loading...
Authors
Hobson, Garth V.
Subjects
Advisors
Date of Issue
1992
Date
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Language
Abstract
The extensive set or experimental data, which was measured primarily for code validation. was used for comparison with a finite volume, incompressible, Navier-Stokes solution of the viscous flow through a set of controlled-diffusion compressor blades. This was done at increasing inlet-flow angles, and the solution was optimized for the design inlet-flow angles. The main objective of this paper is to predict the losses through the cascade, however; another objective is to predict the turbulence field upstream, through and aft of the blade row. Excellent comparisons were achieved at design incidence, however; at increasing flow angles the losses were not accurately predicted with the code.
Type
Conference Paper
Description
28th Joint Propulsion Conference and Exhibit
Series/Report No
Department
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
15 p.
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright proection is not available for this work in the United States.