High Fuel-Air Ratio (FAR) Combustor Modeling

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-04-C-0013
Agency Tracking Number: N022-1106
Amount: $749,684.00
Phase: Phase II
Program: SBIR
Awards Year: 2003
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
DUNS: 966649048
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Mohammed Mawid
 President & Technical Dir
 (937) 255-2007
Business Contact
 Mohammed Mawid
Title: President & Technical Dir
Phone: (937) 255-2007
Email: mohammed.mawid@wpafb.af.mil
Research Institution
A high fuel-air ratio combustor computational model (computer code) is proposed for development in this SBIR project. The proposed computational model will address fuel-air ratio and temperature non-uniformities and fluctuations at the combustor and 1ststage high pressure turbine exit planes based upon actual JP-8 fuel chemical kinetics. A reduced chemical kinetic model will be developed using a detailed JP-8 chemistry mechanism and implemented into the combustor computational model. The proposedcomputational combustor model will also address secondary combustion in the 1st stage high pressure turbine. Steady-state as well as transient operational effects upon high fuel-air ratio fluctuations, chemical species dissociation and recombinationreactions, maximum temperature rise and fluctuations, pattern factor, and film-cooling reactivity will all be predicted in an efficient manner. The proposed combustor computational model will be capable of identifying the impact of various operatingparameters through detailed parametric studies, which can not be accomplished by the conventional multi-dimensional CFD codes. It is therefore anticipated that the proposed combustor computational model will become, once validated, an integral part of thehigh fuel-air ratio combustor design cycle. It is anticipated that the proposed high fuel-air ratio combustor computational model for development in this SBIR will be an integral part of current and future high fuel-air ratio combustors and turbine filmcooling design methodologies and database. In addition, the proposed model will quickly identify the critical design and chemical parameters that impact the high fuel-air ratio combustor designs. These features will make the proposed combustorcomputational model highly marketable to both commercial and military gas turbine engines and ground-based turbine for power generation.

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

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