Hybrid Approach for Modeling Chemical Kinetics and Turbulence Effects on Combustion-Instability

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX11CG64P
Agency Tracking Number: 104909
Amount: $99,923.00
Phase: Phase I
Program: SBIR
Awards Year: 2011
Solitcitation Year: 2010
Solitcitation Topic Code: A2.02
Solitcitation Number: N/A
Small Business Information
CFD Research Corporation
AL, Huntsville, AL, 35805-1944
Duns: 185169620
Hubzone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Ranjan Mehta
 Principal Investigator
 (256) 726-4858
 sxh@cfdrc.com
Business Contact
 Silvia Harvey
Title: Business Official
Phone: (256) 726-4858
Email: sxh@cfdrc.com
Research Institution
 Stub
Abstract
Combustion instabilities pose a significant technical risk in the development of liquid and solid rocket motors. Much of the effort in modeling combustion instabilities has focused either on systems-level tools, or use of detailed computational fluid dynamics (CFD) to simulate all the involved processes. The important effects of finite-rate chemical kinetics and turbulence-chemistry interactions have been neglected in combustion instability modeling. In this SBIR project, CFD Research Corporation (CFDRC) will team up with Gloyer-Taylor Laboratories (GTL) to develop a hybrid approach by combining CFD capabilities with a systems-level instability modeling approach, the latter based on the Universal Combustion Device Stability (UCDS) process. These capabilities will be used to quantify the effects of finite-rate chemistry and turbulence-chemistry interactions on combustion instabilities. In Phase I, feasibility of the proposed approach will be demonstrated by combining 2-D Reynolds Averaged Navier Stokes and Large Eddy Simulation computations with the UCDS framework. In Phase II, the instability analysis will be enhanced by coupling: (1) 3-D CFD analysis; and (2) Improved UCDS process with more accurate treatment of boundary conditions and the flame. The proposed approach will enable an accurate combustion instability analysis of rocket motors, gas turbine combustors, and ramjet and scramjet engines.

* information listed above is at the time of submission.

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