Combustion Stability Innovations for Liquid Rocket

Period of Performance: 08/22/2006 - 05/22/2007

$100K

Phase 1 STTR

Recipient Firm

Metacomp Technologies, Inc.
28632 Roadside Drive, #255
Agoura Hills, CA 91301
Principal Investigator
Firm POC

Research Institution

Pennsylvania State University
110 Technology Center Building
University Park, PA 16802
Institution POC

Abstract

The proposed effort can provide the framework for a unified modeling & simulation program to substantially improve the capability for understanding, analyzing, and predicting the underlying mechanisms dictating the combustion stability characteristics of liquid-propellant rocket engines. Emphasis will be placed on the effects of atomization, mixing, and distributed combustion of liquid oxygen (LOX) and kerosene propellants under conditions representative of oxygen-rich preburner staged-combustion cycle (ORPSC) engines. New models and solution methodologies will be developed and validated, where necessary, to further enhance the solution accuracy and efficiency. The Phase I effort will focus on the flow evolution and flame dynamics of single element coaxial swirl injectors typical of the preburner and main chamber applications with liquid/liquid and gas/liquid mixtures, respectively.