Publication:
Development of a cascade simulation of fan-passage flow

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Authors
Tapp, Eric A.
Subjects
Shock-boundary layer interaction
Transonic fan simulation
Boundary layer separation
Advisors
Shreeve, Raymond P.
Date of Issue
1993-12
Date
December 1993
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
A small-scale blowdown wind tunnel apparatus was developed to investigate techniques to alleviate the negative effects of shock-boundary layer interaction in the blading of aircraft engine fans. Using shadowgraph and surface injection techniques, probe surveys and static pressure measurements, it was shown that acceptable periodicity and repeatability could be obtained in a two-passage cascade model at M=1.4 if air supply pressure, back pressure and porous-wall bleed pressures were properly controlled. It was also shown that local separation due to shock boundary layer interaction was present at the design flow incidence of 1. 15 degrees, but not at 0.85 degrees. Complete data are reported for the design condition to serve as a baseline for separation alleviation experiments. Necessary hardware and software developments are also documented.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautical and Astronautical Engineering
Other Units
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
130 p.
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.
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