Cavitation Model for Turbopumps in Liquid Rocket Systems

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$69,999.00
Award Year:
2002
Program:
SBIR
Phase:
Phase I
Contract:
NAS8-02098
Award Id:
56450
Agency Tracking Number:
012459
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
174 North Main Street, POB 1150, Dublin, PA, 18917
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
AshvinHosangadi
Principal Investigator
(215) 249-9780
hosangad@craft-tech.com
Business Contact:
SanfordDash
President & Chief Scientist
(215) 249-9780
dash@craft-tech.com
Research Institute:
n/a
Abstract
An innovative model for simulating cavitation in liquid rocket turbopumps using cryogenic working fluids is proposed. The formulation is based on a compressible gas-liquid framework that accurately models the acoustics in a multi-phase mixture. This methodology was successfully applied, in our Phase I effort, to simulate cavitating inducer performance in water. Our Phase II effort will extend this formulation to cavitation in cryogenic fluids which exhibit, relative to water, far more complex physics; cryogenic pumps operate at temperatures closer to the critical temperature of the working fluid making thermodynamic effects important. The model will account for the variation in the properties of the fluid as a function of the local fluid temperature that may vary due to energy requirements of vaporization/condensation. It will be incorporated within the commercially marketed code CRUNCH CFD that has a multi-element unstructured framework and is ideally suited for complex turbomachine configurations. This framework will be used as a design support tool to analyze inducer designs and in particular determine the suction specific speed at which head breakdown occurs. The limited reliability of current design tools in cavitating flow regimes makes this innovation a useful tool for turbomachine designers.

* information listed above is at the time of submission.

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