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Combustion LES Software For Improved Emissions Predictions of High Performance Gas Turbine Combustors

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N00421-03-C-0063
Agency Tracking Number: N022-0977
Amount: $69,974.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Solicitation Year: N/A
Award Year: 2002
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
215 Wynn Dr., 5th Floor
Huntsville, AL 35805
United States
DUNS: 003133563
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Steven Cannon
 Group Leader
 (256) 726-4873
Business Contact
 Ashok Singhal
Title: President & Technical Dir
Phone: (256) 726-4829
Research Institution

"Turbulent-combustion emissions modeling (NOx, CO, UHC and smoke) of military gas turbine combustors is a very difficult challenge. Although current RANS steady-state modeling can provide trends, it fails to give quantitatively - accurate predictions ofemissions. A more accurate way to model combustor flows, and proposed for development in this SBIR, is combustion Large Eddy Simulation (LES). Practical combustion LES calculations (1-2 million cells) can now be performed in ten days on a Beowulf PCcluster, and in five years, the run time will be less than a day as computers become substantially faster. We will start with an existing combustion LES code under development the past two years. In Phase I, a ten species mechanism, that includes JP8 fuel oxidation coupled with CO and NOx chemistry, will be used. We will model subgrid turbulence-combustioninteraction with the Conditional Moment Closure (CMC) model developed by Stanford University. The Rolls-Royce AE3007 combustor will be modeled, and experimental data (exit temperature profile, CO, and NOx) will be compared with predictions. In Phase II,the software will be improved, including development of a more detailed chemical mechanism for accurate computation of unburned hydrocarbons and smoke. The final code will be applied to the Rolls-Royce JSF F136 combustor, and modifications to reduceemissions will be assessed. The combustion LES software developed in this SBIR will b

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

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