Modeling and Simulation of the Stability of ORSC Main Combustion Chambers

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-08-C-0033
Agency Tracking Number: F064-005-0078
Amount: $499,933.00
Phase: Phase II
Program: STTR
Awards Year: 2008
Solicitation Year: 2006
Solicitation Topic Code: AF06-T005
Solicitation Number: N/A
Small Business Information
1220 Potter Drive, Suite 100, West Lafayette, IN, 47906
DUNS: 132073946
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 William Anderson
 Associate Professor
 (765) 496-2658
 wanderso@purdue.edu
Business Contact
 Benjamin Austin, Jr.
Title: General Manager
Phone: (765) 775-2107
Email: bjaustin@inspacellc.com
Research Institution
 PURDUE UNIV.
 William Anderson
 Aeronautics and Astronautics
315 North Grant Street
West Lafayette, IN, 47907
 (765) 496-2658
 Nonprofit college or university
Abstract
The potential for combustion instability has historically been a hindrance in developing rocket engines, and nearly always represents the major technical risk in engine developments. This proposal addresses innovative approaches toward prediction of liquid rocket engine combustion instability, as well as innovations in full-scale engine stability verification. Specific objectives are to demonstrate modern experimental diagnostics for measuring combustion stability margin in conjunction with a three-level predictive approach comprising classical linear modeling, moderate-fidelity computational fluid dynamics, and high-fidelity hybrid RANS/LES simulations. This companion experimental/computational/analytical approach provides coupling between the experimental results and analyses at multiple levels of validation enabling a validated predictive tool for fullscale analysis. An existing oxidizer-rich preburner rated at 3600 psia is used to generate warm oxidizer for the experimental study of real-scale ORSC main chamber injectors. The final objective is to perform a stability analysis for a notional 250,000 lbf engine and define a protocol for stability verification of the full-scale engine. The end goals are to provide a revolutionary stability prediction methodology for demonstration during the IHPRPT Hydrocarbon Boost Engine project, and to provide the US propulsion community with a stability analysis methodology that takes full advantage of modern tools and commercial software.

* Information listed above is at the time of submission. *

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