Turbulent Combustion Interaction Models for LES Simulations of High Speed Flow

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-AA-M-2173
Agency Tracking Number: F10B-001-0081
Amount: $100,000.00
Phase: Phase I
Program: STTR
Awards Year: 2011
Solicitation Year: 2010
Solicitation Topic Code: OSD10-T001
Solicitation Number: 2010.B
Small Business Information
Cascade Technologies Incorporated
2445 Faber Place, #100, Palo Alto, CA, -
DUNS: 179576715
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Hung Le
 General Manager
 (650) 521-0243
 hle@turbulentflow.com
Business Contact
 Donna Carrig
Title: Chief Financial Officer
Phone: (650) 521-0243
Email: ddcarrig@turbulentflow.com
Research Institution
 Georgia Institute of Technology
 Suresh Menon
 Georgia Tech Research Corporat
PO Box 100117
Atlanta, GA, 30384-
 (404) 894-9126
 Nonprofit college or university
Abstract
At present, the predictive capability of simulation codes and models used in the conceptual planning and design of high-speed propulsion systems is limited by the ability to describe the complex flow fields inside the combustor, mixing models, detailed chemistry and turbulence-chemistry interactions, and subgrid-closure models. The objective of the proposed work is to develop and validate a high-fidelity LES combustion model based on Flamelet Progress Variable Approach for the accurate prediction of high-speed turbulent combustion. At Cascade, we have a state-of-the-art, fully unstructured, multi-physics LES solver that is currently being used to simulate turbulent combustion in military aircraft engines. Our present efforts are on extending our simulation tool to high-speed turbulent combustion, improve its performance and further validate our approach. In Phase I, a comprehensive program is proposed that consists of (i) an a priori study to evaluate critical model assumption of the flamelet-formulation for reacting jet in high speed-relevant cross-flow conditions and (ii) a posteriori validation and applicability assessment of the LES flamelet-combustion model for supersonic combustion against experimental data. The results of these studies will be leveraged towards model development/assessment, validation of the simulation tool, and improvement of the predictive capabilities of the methodology for high-speed turbulent combustion.

* information listed above is at the time of submission.

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