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High Fidelity Tool for Turbulent Combustion in Liquid Launch Propulsion Systems Based on Spray-Flamelet Methodology

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX14CM43P
Agency Tracking Number: 140034
Amount: $124,145.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: T1.01
Solicitation Number: N/A
Solicitation Year: 2014
Award Year: 2014
Award Start Date (Proposal Award Date): 2014-06-20
Award End Date (Contract End Date): 2014-12-19
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) 271-8841
Business Contact
 Siddharth Thakur
Title: Business Official
Phone: (352) 271-8841
Research Institution
 Stanford University
 Timothy Leung
3160 Porter Drive, Suite 100
Palo Alto, CA 94304-8445
United States

 (650) 725-5966
 Domestic Nonprofit Research Organization

The innovation proposed here is a high-performance, high-fidelity simulation capability for simulating liquid rocket spray combustion based on a novel spray-flamelet methodology which will be integrated into Loci-STREAM which is a CFD solver developed by the proposing personnel under funding from NASA over the last several years. A new spray-flamelet formulation will be incorporated into Loci-STREAM. The particular advantages of this formulation are (i) its consistency with the single-phase flamelet-formulation (already available in Loci-STREAM), (ii) its formulation in mixture-fraction space, overcoming the non-uniqueness of the classical mixture-fraction parameterization, and (iii) its applicability to finite Stokes-number, thereby accounting for particle evaporation, slip-velocity, and poly-dispersed spray-phase. The flamelet methodology already available in Loci-STREAM – in conjunction with Hybrid RANS-LES (HRLES) methodology – has facilitated an order of magnitude improvement in simulation turnaround times for NASA applications involving complex physics in 3D geometries. This project is aimed at extending this flamelet methodology to spray combustion resulting in a state-of-the-art design and analysis tool to enable accurate, fast and robust simulations of multiphase combustion in liquid rocket engines (involving liquid propellants such as LOX and LH2/LCH4/RP-1/RP-2), combustion stability analysis, etc. which constitute critical components of NASA's upper stage launch propulsion systems

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

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