Combustion Stability Innovations for Liquid Rocket

Period of Performance: 07/31/2006 - 05/01/2007


Phase 1 STTR

Recipient Firm

Science and Technology Applications, LLC
530 New Los Angeles Avenue, Suite115 # 122
Moorpark, CA 93021
Principal Investigator
Firm POC

Research Institution

Georgia Institute of Technology
225 North Ave NW
Atlanta, GA 30332
Institution POC


Combustion instability in liquid rocket engines (LREs) has manifested in nearly all LRE development programs. While the driving mechanisms of combustion instability are vast and coupled, in all instances, the net result is significant cost and schedule over-runs. In today s business environment, such over-runs are rarely tolerated and generally result in program cancellations. Development of high fidelity computational codes to aide combustion devices design has been limited due to unavailability and excessive cost of high-powered computing platforms. With the current low-cost state of high-powered/multi-clustered computing systems, achieving the goal of modeling and simulation of coupled physical processes in combustion is realistic.