ADVANCED CFD METHODOLOGY FOR FAST FLOW TRANSIENTS ENCOUNTERED IN NON-LINEAR COMBUSTION INSTABILITY PROBLEMS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$497,723.00
Award Year:
1990
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Agency Tracking Number:
10412
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Cfd Research Corp.
3325-d Triana Blvd, Huntsville, AL, 35805
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Dr Andrzej J Przekwas
() -
Business Contact:
() -
Research Institution:
n/a
Abstract
THE ROCKET THRUST CHAMBERS OFTEN EXPERIENCE COMBUSTION INSTABILITIES WHICH MAY RESULT IN REDUCED PERFORMANCE, INCREASED STRUCTURAL LOADS AND ULTIMATELY IN CATASTROPHIC ENGINE FAILURE. EXISTING ANALYTICAL METHODS ARE GENERALLY LIMITED TO LINEAR-COMBUSTION INSTABILITIES. RELATIVELY LITTLE HAS BEEN ACHIEVED TO UNDERSTAND NONLINEAR COMBUSTION INSTABILITIES PRIMARILY BECAUSE OF LACK OF ACCURATE COMPUTATIONAL FLUID DYNAMICS (CFD) METHODOLOGY. PROPOSED EFFERT WILL CONCENTRATE ON DEVELOPING FAST AND TIME- AND SPACE-ACCURATE CFD METHODS FOR EXACT ANALYSIS OF THE NONLINEAR COMBUSTION INSTABILITIES. PROPOSED INNOVATIVE TIME- ACCURATE METHOD WILL BE COMPARED WITH BEST EXISTING NUMERICAL MODELS. THE TECHNIQUES WILL BE EVALUATED ON 1-D ACOUSTIC AND COMBUSTION INSTABILITY PROBLEMS. RESULTS WILL BE COMPARED WITH ANALYTICAL SOLUTIONS AND AVAILABLE EXPERIMENTAL DATA. IN PHASE II, THE BEST TECHNIQUE WILL BE INCORPORATED IN A CFD COMPUTER CODE TO BE USED AS A BASE FORINCORPORATING PHYSICAL MODELS OF TWO-PHASE SPRAY COMBUSTION MODELS.

* information listed above is at the time of submission.

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