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Artificial Neural Net Chemistry Module for Large Eddy Simulations

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NAS3-03012
Agency Tracking Number: 023975
Amount: $69,923.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Timeline
Solicitation Year: N/A
Award Year: 2003
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
215 Wynn Dr.
Huntsville, AL 35805
United States
DUNS: N/A
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Steven Cannon
 Principal Investigator
 (256) 726-4800
 jls@cfdrc.com
Business Contact
 Ashok K. Singhal
Title: President & Technical Director
Phone: (256) 726-4841
Email: jls@cfdrc.com
Research Institution
N/A
Abstract

Combustion Large Eddy Simulation (LES) is a vastly improved method of modeling turbulent-combustion in gas turbine combustors, and will provide improved emissions/instability prediction capability of UEET combustors. It is widely recognized that one of the best subgrid turbulence-combustion models is the Linear Eddy Mixing (LEM) model with multi-step reactions. However, this model is not commonly used in the design environment for one main reason: computational time. In this SBIR, we propose to develop a subgrid LEM module with multi-step Jet-A kinetics that is 100 times faster than the state-of-the-art direct LEM. This new, innovative method performs off-line LEM calculations over a range of turbulence levels and compositions to train an artificial neural net (ANN). The ANN is then used to determine the chemical source terms required in the combustion LES calculation. In Phase I of this SBIR, the feasibility of developing the LEM/ANN module will be demonstrated by training a one-step, five species Jet-A fuel oxidation mechanism. The preliminary LEM/ANN module will be implemented into the CFD-ACE+ code, validation performed, and speed-up demonstrated. At the end of Phase I, the module will be delivered to NASA for incorporation into the NCC code. In Phase II, the LEM/ANN approach will be extended to include multi-step Jet-A kinetic mechanisms, and applied to UEET combustor configurations.

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

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