Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig
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Authors
Vavra, Michael Hans
Subjects
Advisors
Date of Issue
1970-09-01
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
The report deals with the aerodynamic design of an axial compressor stage with symmetrical bladings for a research program to investigate tip clearance effects in a three-stage compressor. It establishes the blading data and the stage performance with an iterative three-dimensional approach, and gives criteria for the drive and the flow measuring device of the test unit. The calculated distributions of the flow properties in the stage will be used for future comparisons with test data. (Author)
Type
Technical Report
Description
Series/Report No
Department
Identifiers
NPS Report Number
NPS-57VA70091A
Sponsors
Navy Department, Naval Air Systems Command, Code 310, AIRTASK No. A310310A/551A/1R01003010
Funder
Format
Citation
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.