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Theoretical Innovations in Combustion Stability Research: Integrated Analysis and Computation

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-10-C-0088
Agency Tracking Number: F09B-T38-0180
Amount: $100,000.00
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): 2010-06-11
Award End Date (Contract End Date): 2011-03-11
Small Business Information
2000 Kohler Dr.
Boulder, CO 80305
United States
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 David R Kassoy
 (303) 494-9017
Business Contact
 David Kassoy
Title: Owner
Phone: (303) 494-9017
Research Institution
 Jet Propulsion Laboratory
 Josette Bellan
4800 Oak Grove Dr
Pasadena, CA 91109
United States

 (818) 354-6959
 Federally Funded R&D Center (FFRDC)

Quantitative predictions of reactive flow dynamics from large-scale simulations of Liquid Rocket Engines (LRE) appear to be model dependent. Relationships and coupling among the dominant mechanisms most responsible for destabilization are obscured by the complexities of the model and subtle consequences of inherent ad hoc approximations not supported by mathematical rationale. The reliability of predictions is difficult to quantify. These uncertainties provide opportunities for novel theoretical (integrated analysis and computation) research aimed at reducing complexity and identifying primary drivers of instability (dominant coupling mechanisms). Phase I research will demonstrate that thermomechanical concepts and analysis can be employed to address stability processes in a LRE. Systematic asymptotic analysis is used to identify dominant physical processes occurring in an idealized supercritical LRE, and their inherent time and length scales. This form of analysis leads to model equations of reduced complexity, based on derived approximations with an a priori understanding of model limitations. Anticipated Phase II research will apply proven Phase I methodologies to very general equation systems capable of describing coupled chemico-physical phenomena in supercritical pressure, turbulent reacting flows, characteristic of an operational LRE. Computational solutions of the reduced equations will produce quantitative predictions of combustion stability, including concepts that will facilitate improved design practice BENEFIT: Simplified Liquid Rocket Engine computer codes with predictive reliability will; * facilitate LRE design practices based on first principles, * reduce the computational expense of design, * foster more cost-effective LRE design process, * enable the construction of stable LRE''s.

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

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