Comparison of calculated and experimental cascade performance for controlled-diffusion compressor stator blading
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Authors
Sanger, N.L.
Shreeve, R.P.
Subjects
BOUNDARY LAYERS
CASCADE FLOW
COMPARISON
COMPRESSOR BLADES
COMPRESSORS
COMPUTATION
DIFFUSION
EXPERIMENTATION
GAS TURBINE ENGINES
INVISCID FLOW
REYNOLDS NUMBER
STATORS
SURFACE LAYERS
ASPECT RATIO
CHORDS (GEOMETRY)
PRESSURE
CASCADE FLOW
COMPARISON
COMPRESSOR BLADES
COMPRESSORS
COMPUTATION
DIFFUSION
EXPERIMENTATION
GAS TURBINE ENGINES
INVISCID FLOW
REYNOLDS NUMBER
STATORS
SURFACE LAYERS
ASPECT RATIO
CHORDS (GEOMETRY)
PRESSURE
Advisors
Date of Issue
1986-06
Date
June 1986
Publisher
Language
Abstract
The mid-span section of a previously reported controlled-diffusion compressor stator has been experimentally evaluated in cascade. Measurements are taken over a range of incidence angles for blade chord Reynolds numbers from 470,000 to 690,000. Blade chord length is 12.7 cm, aspect ratio is 2.0, and solidity is 1.67. Measurements include conventional cascade performance parameters as well as blade surface pressures. Computations are made for the inviscid flow field, surface boundary layers, and loss for several of the blade inlet angle conditions, are compared against corresponding data.
Type
Conference Paper
Description
International Gas Turbine Conference and Exhibit; 8-12 Jun. 1986; Dusseldorf; Germany
Series/Report No
Department
Organization
Glenn Research Center
Identifiers
NPS Report Number
Sponsors
Funder
RTOP 505-62-21
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
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.