A COMPUTER MODEL FOR LIQUID JET ATOMIZATION IN ROCKET THRUSTCHAMBERS.

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$497,977.00
Award Year:
1989
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Award Id:
6836
Agency Tracking Number:
6836
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
3325d Triana Blvd, Huntsville, AL, 35805
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Andrzej J Przekwas
() -
Business Contact:
() -
Research Institution:
n/a
Abstract
LIQUID PROPELLANT ATOMIZATION PLAYS A DOMINANT ROLE IN STABLE AND EFFICIENT OPERATION OF ROCKET THRUST CHAMBERS. DESPITE THE RECENT PROGRESS IN COMPUTATIONAL FLUID DYNAMICS (CFD) AND SPRAY COMBUSTION MODELLING TECHNIQUES, NOSATISFACTORY APPROACH HAS YET BEEN DEVELOPED FOR PROPELLANT ATOMIZATION MODELLING. THE MAJOR INNOVATIVE ELEMENT OF THIS PROPOSAL IS TO PREDICT THE DROPLET BREAKUP RATE AND AVERAGE DROPLET DIAMETER AFTER PRIMARY ATOMIZATION. THE APPROACH IS TO PREDICT THE WAVE FORMATION ON THE JET SURFACE AND ITS TRANSPORT. THESE MODELS WILL BE COUPLED WITH THE JET EMBEDDING (JE) TECHNIQUE OF PREDICTING THE ATOMIZATION PROCESS. THE PROPOSED IMPROVEMENTS WILL BE INCORPORATED INTO NASA'S MULTI-DIMENSIONAL REACTIVE FLOW CODE, REFLAN, AND TESTED ON THE SSME THRUST CHAMBER GEOMETRY. THE PHASE I WORK WILL ESTABLISH THE FEASIBILITY OF THE PROPOSED MODIFICATIONS. IN PHASE II, EMPHASIS WILL BE ON CODE VERIFICATION, AND ON EXTENSIONS, E.G. FOR NON-AXISYMMETRI JETS AND IMPINGING ELEMENTS.

* information listed above is at the time of submission.

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