SBIR/STTR
High Performance Multiphase Combustion Tool Using Level Set-Based Primary Atomization Coupled with Flamelet Models, Phase I
Project Introduction
The innovative methodologies proposed in this STTR Phase 1 project will enhance Loci-STREAM which is a high performance, high fidelity simulation tool already being used at NASA 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 (using propellants such as LOX, LCH4, RP-1, LH2, etc.). The proposed enhancements to Loci-STREAM in this project are: (1) Level-Set methodology (which will be of high fidelity and highly scalable for massively parallel computing) for tracking liquid propellant interface for primary atomization, and (2) Adaptive tabulation for flamelet models for turbulent combustion designed for distributed parallel computing architectures. The following methodologies are already available in Loci-STREAM: (a) Lagrangian particle tracking for motion of droplets, (b) Droplet evaporation model, and (c) Flamelet models in Hybrid RANS-LES framework for unsteady turbulent combustion. Integration of the methodologies proposed in this project 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 Space Launch System (SLS).
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Anticipated Benefits
The outcome of the proposed Phase 1 and Phase 2 research and development activities will be a powerful and advanced version of a CFD-based multiphase combustion code (called Loci-STREAM) for propulsion engines at NASA. This code is envisioned to be a powerful design and analysis tool for propulsion devices including full rocket engine simulations, injector design, etc. This tool will have a direct impact on development of propulsion systems relevant to the SLS by enabling design improvements of injectors involving liquid propellants such as LOX, LH2, LCH4, RP1, etc. Specific applications at NASA of this capability will include: (a) Fast and accurate simulation of turbulent combustion in existing or new/modified liquid space propulsion engines including J-2X, RS-68, F-1, etc., (b) Fast and accurate 3D unsteady simulations of multi-element injectors coupled with fuel and oxidizer feed lines and manifolds which will yield high-fidelity information for combustion instability models, (c) Prediction of stability and stability margins, (d) Design of acoustic cavities for combustion stability, etc.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Marshall Space Flight Center
(MSFC)
|
Lead Organization | NASA Center | Huntsville, AL |
| Mississippi State University | Supporting Organization | Industry | |
| Streamline Numerics, Inc. | Supporting Organization | Industry | Gainesville, FL |
Primary U.S. Work Locations
-
Alabama
-
Florida
-
Mississippi
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Marshall Space Flight Center (MSFC)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Project Manager:
Principal Investigator:
- Siddharth Thakur
Project Duration
Start: May 2013
End: May 2014
Technology Maturity (TRL)
| Start: | 2 |
| Current: | 2 |
| Estimated End: | 5 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TA 1 Launch Propulsion Systems
- TA 1.2 Liquid Rocket Propulsion Systems
- TA 1.2.6 Fundamental Liquid Propulsion Technologies