Accession Number : AD0708386

Title :   AN INVESTIGATION OF THE EFFECT OF A TANGENTIAL GAS VELOCITY ON COMBUSTION INSTABILITY.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s) : Kiel,Joseph Alan

Report Date : JUN 1969

Pagination or Media Count : 75

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 as 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. (Author)

Descriptors :   (*COMBUSTION, STABILITY), HYBRID ROCKET PROPELLANTS, ROCKET IGNITERS, VORTICES, COMBUSTION CHAMBERS, PRESSURE, THESES, ROCKET NOZZLES, FLOW FIELDS, OXYGEN, ALKANES

Subject Categories : Combustion and Ignition
      Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE