Publication:
Calculations for axial compressor blading with uniform inlet enthalpy and radial enthalpy gradient

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Authors
Schlachter, W
Subjects
Axial Compressor Blading
Radial Equilibrium
Advisors
Date of Issue
1981-05
Date
1981-05
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
A computer program was used to calculate the radial distribution of flow parameters in an axial compressor stage designed to have a symmetrical velocity diagram at the mean radius and particular variations of reaction from hub to tip. Uniform energy addition was assumed to occur in the rotor. Both cases of uniform enthalpy and uniform radial enthalpy gradient at the entrance to the stage were considered. Advantages were found in the selection of fully symmetric blading and in the use of the inlet enthalpy gradient as a design parameter. (Author)
Type
Technical Report
Description
Series/Report No
Department
Identifiers
NPS Report Number
NPS67-81-008
Sponsors
Naval Air Systems Command, Washington, DC
Funder
N000198WR11104
Format
NA
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.
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