Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques
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Authors
Sanger, Nelson L.
Subjects
turbomachinery
axial flow compressor design
transonic compressor stage
axial flow compressor design
transonic compressor stage
Advisors
Date of Issue
1994-06
Date
June 13-16, 1994
Publisher
Language
Abstract
A transonic compressor stage has been designed for the Naval
Postgraduate School Turbopropulsion Laboratory. The design relied
heavily on CFD techniques while minimizing conventional empirical
design methods. The low aspect ratio (1.2) rotor has been designed
for a specific head ratio of .25 and a tip relative inlet Mach number
of 1.3. Overall stage pressure ratio is 1.56. The rotor was designed
using an Euler code augmented by a distributed body force model to
account for viscous effects. This provided a relatively quick-running
design tool, and was used for both rotor and stator calculations. The
initial stator sections were sized using a compressible, cascade panel
code. In addition to being used as a case study for teaching
purposes, the compressor stage will be used as a research stage.
Detailed measurements, including non-intrusive LDV, will be
compared with the design computations, and with the results of other
CFD codes, as a means of assessing and improving the
computational codes as design tools.
Type
Conference Paper
Description
Prepared for the 39th International Gas Turbine & Aeroengine Congress & Exposition sponsored by the American Society of Mechanical Engineers.
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
National Aeronautics and Space Administration NASA TM-106636
Funder
National Aeronautics and Space Administration NASA TM-106636
WU-505-62-52
American Society of Mechanical Engineers (ASME)
WU-505-62-52
American Society of Mechanical Engineers (ASME)
Format
18 p.
Citation
39th International Gas Turbine & Aeroengine Congress & Exposition
sponsored by the American Society of Mechanical Engineers
The Hague, NetherIands,Jime-13-16, 1994
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.