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New Paradigms in High Pressure Combustion Dynamics Prediction and Control

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-14-C-2502
Agency Tracking Number: F12B-T15-0074
Amount: $1,485,382.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: AF12-BT15
Solicitation Number: 2012.2
Solicitation Year: 2012
Award Year: 2014
Award Start Date (Proposal Award Date): 2014-08-13
Award End Date (Contract End Date): 2018-11-13
Small Business Information
2629 Townsgate Road Suite 105
Westlake Village, CA 91361-2981
United States
DUNS: 005100560
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Ramakanth Munipalli
 Sr. Computational Physicist
 (805) 371-7500
Business Contact
 Vijaya Shankar
Title: Vice-President
Phone: (805) 371-7556
Research Institution
 The University of Utah
 Dongbin Xiu
155 S 1400 E Room 233
Salt Lake City, UT 84112-0090
United States

 (202) 642-4808
 Nonprofit College or University

ABSTRACT:In this project we seek to transition major recent developments in the mathematics of model reduction to industrial grade computing applications in liquid rocket combustion instability. From the mathematical side, we are interested in unsteady nonlinear dynamical systems which exhibit limit-cycle behavior and large oscillations and potentially discontinuous solutions. From the applications perspective, we are interested in a practical simulation capability for large multi-injector liquid hydrocarbon fueled rocket engines such as the Hydrocarbon Boost demonstration (HCB) engine that are of contemporary interest. Combustion instability is a key concern in new rocket development efforts. Predictive computer modeling can serve a vital role in risk reduction at a relatively low cost. Present day simulation tools, while trending towards a comprehensive self-consistent physical model set and becoming increasingly better verified and validated, still place enormous demands on computer resources needed for realistic simulations.A software suite named HDrbm developed here will address black-box capabilities in model reduction for nonlinear multiphysical applications. HyPerComp will team with the Scientific Computing and Imaging Institute at the University of Utah in developing mathematical methods and software system in this project. The team will also benefit from consulting support from key researchers in applied mathematics and turbulent combustion modeling.BENEFIT:This work has direct relevance to major ongoing liquid rocket engine programs where stability studies are overwhelmed by the computational problem size, and can benefit from improvements in methodology. The models and methodologies developed here are also directly relevant to solid propellant rockets and gas turbine combustors. The general scope of the methods developed here is indeed rather vast. The reduced basis method has applications in numerous markets: automotive, nuclear, image processing, and atmospheric science to name a few. Successful phase-II research automatically enables control algorithms, optimization and uncertainty based predictions for combustion dynamics.

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

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