Investigation of a mach 1.4 compressor cascade with variable back pressure using flow visualization.
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Authors
Hegland, Michael George
Subjects
transonic compressor cascade
flow visualization
flow visualization
Advisors
Shreeve, Raymond P.
Date of Issue
1986-03
Date
March 1986
Publisher
Language
en_US
Abstract
Flow through a transonic compressor cascade model was
investigated at M = 1.4 using flow visualization and pressure
measurements. Shock patterns for two different blade incidences
were documented at increasing back pressures. Data
were taken up to a maximum pressure ratio of 1.53 at estimated
minimum loss incidence conditions. An oblique shock system
persisted, producing large flow turning (6.8°) and a slightly
supersonic exit mach number (1.02). Losses and blade pressure
loading were calculated using a combination of test data and
computational approximations. Failure of blade retaining tabs
occurred with both aluminum, and steel cascade blades. Failures
were attributed to fatigue from high oscillatory stress levels
and redesigned blade mounts were proposed.
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
114 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.