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Theoretical Innovations in Combining Analytical, Experimental, and Computational Combustion Stability Analysis

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-10-C-0125
Agency Tracking Number: F09B-T38-0136
Amount: $99,995.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: AF09-BT38
Solicitation Number: 2009.B
Solicitation Year: 2009
Award Year: 2010
Award Start Date (Proposal Award Date): 2010-05-12
Award End Date (Contract End Date): 2011-01-12
Small Business Information
2629 Townsgate Road Suite 105
Westlake Village, CA 91361
United States
DUNS: 005100560
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Ramakanth Munipalli
 Senior Computational Physicist
 (805) 371-7500
Business Contact
 Vijaya Shankar
Title: Vice-President
Phone: (805) 371-7556
Research Institution
 School of Aerospace Engineering
 Suresh Menon
270 Ferst Drive Georgia Instt. of Technology
Atlanta, GA 30332
United States

 (404) 894-9126
 Nonprofit College or University

Combustion stability is an important consideration in the design of liquid rocket engines. While fundamental modes of unstable operation in simple geometries are easily identified using analytical methods, recent times have seen these methods greatly expand in scope, applied in semi-numerical format to increasingly complex geometries and flow situations. Much remains to be explored in understanding the role of chemistry and turbulence interaction, nonlinear effects and coupled unstable modes and such others. While analytical models and CFD have largely been kept apart by convention, some recent advances have begun to pave the way for their effective integration. The generalized use of the Galerkin approach to complex physics has enabled a straightforward usage of eigen-functions to preempt numerical solutions such that each solution yields greater physical insight into the problem. We propose here a series of advancements to make combustion stability analysis more efficient by a natural coupling between analysis, CFD and experiments. Among others, these methods will include: the use of reduced basis methods, the ability to model uncertainty in flow calculations, high order accurate and efficient calculations of flows in complex geometries. This research will be performed jointly by HyPerComp Inc. and the Computational Combustion Laboratory at Georgia Tech. BENEFIT: Work proposed here has a broad appeal to manufacturers of solid and liquid propellant rocket motors as well as gas turbine engines. These are significant markets and will be able to sustain a niche software suite to be developed. An effective modeling strategy and an integrated simulation environment can result in tremendous cost savings in trial and error testing. Specifically, the combustion stability application will serve as a front runner to promote HyPerComp Inc.’s upcoming product line of very high order accurate simulation software for multiphysics, a first in the industry. Allied technologies such as uncertainty modeling and reduced basis methods will bring new energy into an otherwise routine set of modeling applications currently in vogue.

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

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