An investigation of the effect of a tangential gas velocity on combustion instability.

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.

Department dc:contributor.department

Aeronautics

Grantor dc:publisher

Monterey, California. U.S. Naval Postgraduate School

Year dc:date.issued

1969

Author dc:creator

• Kiel, Joseph Alan

Advisor dc:contributor.advisor

• Netzer, David W.

Statement dc: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.

Language dc:language.iso

en_US

Handle dc:identifier.uri

https://hdl.handle.net/10945/12423

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/12423