Conversion of inlet temperature distortions to vorticity for an axial-flow compressor.
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Authors
Iverson, Michael Martin
Subjects
compressor stall
aircraft inlet/temperature distortion
aircraft gas turbines
compressor inlet temperature distortion
steam ingestion
missile exhaust gas ingestion
rocket exhaust gas ingestion
aircraft inlet/temperature distortion
aircraft gas turbines
compressor inlet temperature distortion
steam ingestion
missile exhaust gas ingestion
rocket exhaust gas ingestion
Advisors
Fuhs, Allan E.
Date of Issue
1972-06
Date
June 1972
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
A survey of the literature on pressure , temperature and
foreign gas inlet distortions is made. For interpretation of
the influence of inlet distortion on engine stability , a break
is made with distortion methods which use temperature or pressure
distortion maps . The distortion in the form of temperature
contours is transformed to vorticity using appropriate
equations derived for both incompressible and compressible flow. Crocco's theorem has been expanded in scope to include
multispecie, nonuniform, perfect gas mixtures . The derivation
of the equations and specialization to cases of interest involved a thorough order of magnitude analysis . A numerical solution of Poisson's equation as formulated by Squire and
Winter to describe secondary flow arising from convected vorticity is presented. Deficient areas of knowledge relating to
the general temperature/foreign gas problem are outlined . A
conceptual mode l involving compressor stage transfer functions
and feedback mechanisms is introduced and discussed at several
points. Although not essential to understanding the vorticity
stall logic chain , this mode l is a useful conceptual tool and
may be worthy of additional study .
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funding
Format
92 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.