ADVANCED MODELLING OF COMBUSTION SYSTEMS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$49,957.00
Award Year:
1990
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
11949
Agency Tracking Number:
11949
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
P.o. Box 71, Hanover, NH, 03755
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Christopher J. Crowley
Principal Engineer
(603) 643-3800
Business Contact:
JAMES A. BLOCK
PRESIDENT
(603) 643-3800
Research Institute:
n/a
Abstract
THE ACCURATE PREDICTION OF FLOW, SPECIES CONCENTRATION AND TEMPERATURE IS ESSENTIAL TO THE CHARACTERIZATION AND DESIGN OPTIMIZATION OF COMBUSTORS. TO THIS END, IT IS ESSENTIAL TO INCLUDE THE EFFECTS OF NON-GRAY RADIATION AND FINITE RATE CHEMICAL KINETICS IN COMBUSTION MODELLING. THE PROPOSAL DESCRIBES NOVEL AND HIGHLY PARALLEL TECHNIQUES FOR THIS PURPOSE. THE DISCRETE TRANSFER MODEL IS USED FOR NON-GRAY RADIATION. FOR STIFF KINETICS, A POINT-WISE SOLUTION TECHNIQUE USING STIFF SOLVERS FOR ORDINARY DIFFERENTIAL EQUATIONS IS PROPOSED. THE PHASE I PROGRAM CONSISTS OF EVALUATING THESE TECHNIQUES WITHIN THE FRAMEWORK OF OUR COMMERCIAL CODE FLUENT; VERIFICATION PROBLEMS FROM THE LITERATURE WILL BE USED TO ESTABLISH THE CORRECTNESS OF RESULTS OBTAINED. IF THE INITIAL IMPLEMENTATION PROVES FEASIBLE, THE PHASE II PLAN IS TO EXTEND THE IMPLEMENTATION TO NON-ORTHOGONAL GRIDSIN OUR CODE FLUENT/BFC. AT CULMINATION, THE PROPOSED WORK WILL DEVELOP FOR NASA A COMPREHENSIVE TOOL FOR THE MODELLINGOF TURBULENT, REACTING SUBSONIC FLOW AND HEAT TRANSFER IN COMPLEX COMBUSTOR GEOMETRIES.

* information listed above is at the time of submission.

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