High Performance Multiphase Combustion Tool Using Level Set-Based Primary Atomization Coupled with Flamelet Models

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX14CM46C
Agency Tracking Number: 120021
Amount: $749,611.00
Phase: Phase II
Program: STTR
Awards Year: 2014
Solicitation Year: 2012
Solicitation Topic Code: T1.01
Solicitation Number: N/A
Small Business Information
3221 North West 13th Street, Suite A, Gainesville, FL, 32609-2189
DUNS: 090574786
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Siddharth Thakur
 Principal Investigator
 (352) 271-8841
 st@snumerics.com
Business Contact
 Siddharth Thakur
Title: Business Official
Phone: (352) 271-8841
Email: st@snumerics.com
Research Institution
 Mississippi State University
 Angela Templeton
 133 Etheridge Hall, 449 Hardy Road
Mississippi State, MS, 39762
 (662) 325-7404
 Domestic nonprofit research organization
Abstract
The innovative methodologies proposed in this STTR Phase 2 project will enhance Loci-STREAM which is a high performance, high fidelity simulation tool already being used at NASA/MSFC for a variety of CFD applications. This project will address critical needs in order to enable fast and accurate simulations of liquid space propulsion systems of relevance to NASA's Space Launch System (SLS) program (LOX/RP-1 engines such as F-1 or potential replacement of RD-180, and LOX/LH2 engines such as RS-25, RS-25D/E, RL10, J-2X). The key methodologies which will be integrated into a production version of the Loci-STREAM code are the following: (a) Primary atomization modeling using Level Set methodology to model the liquid (core) jet, (b) Lagrangian particle tracking (LPT) for the droplets resulting from primary atomization, (c) Evaporation models for the droplets, (d) Flamelet models for turbulent combustion, (e) Adaptive tabulation for flamelet models, and (f) Hybrid RANS-LES (HRLES) methodology. Integration of the above methodologies into Loci-STREAM will result in a state-of-the-art multiphase combustion modeling tool which will enable fast and accurate design and analysis of liquid rocket engine flow environments, combustion stability analysis, etc. which constitute critical components of space propulsion engines that are part of NASA's SLS.

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

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