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Advanced Unsteady Turbulent Combustion Simulation Capability for Space Propulsion Systems

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX11CC73C
Agency Tracking Number: 090031
Amount: $594,289.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: T9.01
Solicitation Number: N/A
Timeline
Solicitation Year: 2009
Award Year: 2011
Award Start Date (Proposal Award Date): 2011-07-08
Award End Date (Contract End Date): 2013-07-07
Small Business Information
3221 North West 13th Street, Suite A
Gainesville, FL 32609-2189
United States
DUNS: 090574786
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Siddharth Thakur
 Principal Investigator
 (352) 352-8841
 st@snumerics.com
Business Contact
 Siddharth Thakur
Title: President
Phone: (352) 271-8841
Email: st@snumerics.com
Research Institution
 University of Michigan
 Matthias Ihme
 
Wolverine Tower, First Floor, Room 1061, 3003 S. State St.
Ann Arbor, MI 48109-1274
United States

 () -
 Nonprofit College or University
Abstract

The innovation proposed here is a high performance, high fidelity simulation capability to enable accurate, fast and robust simulation of unsteady turbulent, reacting flows involving propellants of relevance to NASA (GOX/GH2, LOX/LH2 and LOX/LCH4). The key features of this proposed capability are: (a) Hybrid RANS-LES (HRLES) methodology, and (b) flamelet modeling for turbulent combustion, incorporated in a proven existing solver called Loci-STREAM which has been developed by the proposing personnel under funding from NASA over the last several years. Basic flamelet methodology has been incorporated in Loci-STREAM during Phase 1 work and tested on gas-gas injectors of relevance to NASA. The enhancements in Loci-STREAM resulting from Phase 1 work have demonstrated an order of magnitude improvement in simulation turnaround times relative to existing capability for turbulent reacting flow applications at NASA. The work proposed during Phase 2 will extend the flamelet methodology to real-fluid flows, wall heat transfer and variable pressures. This will ultimately result in a state-of-the-art design and analysis tool to enable the accurate modeling of for multiphase combustion in solid and liquid rocket engines, combustion stability analysis, etc. which constitute critical components of versatile space propulsion engines part of NASA's deep space missions.

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

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