Real Time Measurements in a Transonic Compressor
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Authors
Shreeve, R.P.
Subjects
Advisors
Date of Issue
1976-02
Date
February 1976
Publisher
Language
Abstract
The purpose of this brief presentation is to report work in
progress at the Turbopropulsion Laboratory at the Naval Postgraduate
School to determine experimentally the behavior of the
flow in a transonic compressor stage. The intent is to develop
an input into the design method which accounts , in some way, for the three dimensional and periodic nature of the flow. While this
has been the goal of continuing research efforts, no significant
change in the basic design model has been reported. The essential
three dimensional nature of transonic flow is acknowledged,
but no design method is three dimensional. Within the pseudo
two dimensional analytical framework, secondary flows are known
to become more significant as the blade loading is increased, and wall effects become important as the passage depth is decreased.
While the effects are qualitatively known to be significant, the
understanding that comes from favorable comparisons of observation.
with analyses is lacking . First, definitive measurements
from different stage designs are needed to define the relative importance
of different effects and thus provide the basis for a representative
analytical design model. In order to achieve higher performance
from a new design without a costly empirical development
process, a design model which more nearly represents the actual
flow In the blade rows is essential.
Type
Conference Paper
Description
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Naval Air Systems Command, Code 310
Funder
Naval Air Systems Command, Code 310
Format
16 p.
Citation
Shreeve, R.P. "Real Time Measurements in a Transonic Compressor". Published in "Transonic flow problems in turbomachinery." NASA STI/Recon Technical Report N 77 (1977): 27361
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.