An investigation of the effect of a tangential gas velocity on combustion instability.
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Authors
Kiel, Joseph Alan
Subjects
bi-phase
combustion
gas
instability
liquid
propellant
rocket
combustion
gas
instability
liquid
propellant
rocket
Advisors
Netzer, David W.
Date of Issue
1969-06
Date
June 1969
Publisher
Monterey, California. U.S. Naval Postgraduate School
Language
en_US
Abstract
A small, uncooled research rocket motor was built to study the
effects of a vortex flow on combustion instability. Normal heptane
and air were used as propellants with the air being divided into two
flows; a primary flow at the center of the combustion chamber and a
secondary flow at the periphery of the chamber. The secondary air
provided the swirl which could be directed clockwise or counterclockwise
at various angles or a straight mode of operation. Runs were
made at various flow rates with the direction of swirl changed during
the run.
A first tangential high frequency mode of combustion instability
was developed and a significant change in stability conditions was
found when a vortex flow was generated within the combustion
chamber. It was found that a swirl in one direction tended to decrease
the instability while a flow in the opposite direction increased it.
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
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.