Chemical Kinetics Modeling Tools for Hydrocarbon Scramjet Propulsion System Design

Award Information
Agency:
Department of Defense
Branch
Office of the Secretary of Defense
Amount:
$99,978.00
Award Year:
2005
Program:
STTR
Phase:
Phase I
Contract:
FA8650-05-M-2618
Award Id:
76630
Agency Tracking Number:
O054-002-1016
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
8940 Old Annapolis Road Suite L, Columbia, MD, 21045
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
018413208
Principal Investigator:
Michael Klassen
Principal Research Engineer
(410) 884-3266
mklassen@csefire.com
Business Contact:
Doug Carpenter
Vice President
(410) 884-3266
dcarpenter@csefire.com
Research Institution:
GEORGIA INSTITUTE OF TECHNOLOGY
James Berkowitz
Office of Sponsored Programs
Atlanta, GA, 30332
(404) 894-6922
Nonprofit college or university
Abstract
Reliable design tools are of paramount importance to predict the combustion processes under supersonic conditions, as obtaining ground experimental data under these conditions is difficult and expensive. Combustion Science & Engineering, Inc. (CSE) proposes to develop a global approach for creating and implementing reduced chemical kinetic mechanisms for hydrocarbon fuels in the design process of scramjet propulsion for hypersonic flight. This approach will use a detailed CH2O/H2/O2 reaction sub-set to allow for accurate predictions of non-equilibrium phenomena such as ignition and extinction assuming break-down of the fuel molecule into CH2O and H2. The rate constant for the fuel decomposition step will be evaluated from available experimental data. The reduced mechanism will consist of 14 species and 44 reactions, irrespective of the type of fuel is used. This model has been successfully demonstrated for propane to predict ignition and extinction under subsonic conditions. In this project, this approach will be extended to hydrocarbon fuels including hypersonic fuels such as JP-7 to predict non-equilibrium combustion phenomenon under supersonic conditions. The reduced model will be validated and optimized against available experimental data in the literature. Then, the reduced kinetic mechanism coupled with mixing model will be implemented in various CFD codes to test the compatibility and convergence criteria under supersonic conditions.

* information listed above is at the time of submission.

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