Turbopump Cavitation Tools

Award Information
Agency:
Department of Defense
Amount:
$99,989.00
Program:
SBIR
Contract:
FA9300-07-M-3003
Solitcitation Year:
2007
Solicitation Number:
2007.1
Branch:
Air Force
Award Year:
2007
Phase:
Phase I
Agency Tracking Number:
F071-204-0275
Solicitation Topic Code:
AF071-204
Small Business Information
COMBUSTION RESEARCH & FLOW TECHNOLOGY, I
6210 Keller's Church Road, Pipersville, PA, 18947
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
929950012
Principal Investigator
 Ashvin Hosangadi
 Principal Scientist
 (215) 766-1520
 hosangad@craft-tech.com
Business Contact
 Brian York
Title: Principal Scientist & Treasurer
Phone: (215) 766-1520
Email: york@craft-tech.com
Research Institution
N/A
Abstract
The next generation liquid rocket systems envision novel designs for turbopumps that can operate at high suction speeds (i.e. low inlet pressures), and can be throttled over a wide range of low, off-design flow conditions. This is an extremely demanding flow regime where performance loss and damage from cavitation instabilities can be catastrophic since they can generate large amplitude pressure fluctuations. However, the ability of current analytical or CFD tools to reliably predict unsteady cavitation dynamics is not mature particularly for cryogens where temperature fluctuations can couple with the pressure variations.. The innovation proposed here is to extend current capabilities to analyze mean solutions and head drop-off, to an unsteady framework that can predict amplitudes and frequencies of dynamic pressure loads within a cryogenic fluid environment with temperature fluctuations. A key aspect of this proposal is an extensive testing program that will be conducted in the Phase II effort to provide dynamic load magnitudes in a regime where thermal effects are important Hence, the resulting product will be a well-validated and reliable analysis tool, CRUNCH CFD®, that can be used predict unsteady, off-design performance of liquid rocket turbopumps.

* information listed above is at the time of submission.

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