Simulations of Unsteady Effects and Dynamic Responses in Complex Valve Systems

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNS05AA36C
Agency Tracking Number: 040884
Amount: $69,996.00
Phase: Phase I
Program: SBIR
Awards Year: 2005
Solitcitation Year: N/A
Solitcitation Topic Code: N/A
Solitcitation Number: N/A
Small Business Information
Combustion Research and Flow Technology
6210 Kellers Church Road, Pipersville, PA, 18947
Duns: 929950012
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Vineet Ahuja
 (215) 766-1520
 vineet@craft-tech.com
Business Contact
 Paula Schachter
Title: Business Official
Phone: (215) 766-1520
Email: schachte@craft-tech.com
Research Institution
N/A
Abstract
CFD based analyses are playing an increasingly important role in supporting experimental testing of rocket propulsion systems. The focus of this proposal is towards identifying and characterizing flow induced instabilities in the experimental test facility. Computational simulations will be carried out with advanced turbulence modeling extensions to the hybrid unstructured framework that has been previously shown to accurately and efficiently predict steady flowfields in complex valve configurations used at SSC. The computational framework will be comprehensive to include instabilities ranging from turbulent pressure fluctuations due to vortex shedding in bends and elbows of the piping system to large scale fluctuations due to collapse of vapor cavities in flow control elements such as venturis. Furthermore, the development in this proposal will include prediction of system response such as amplification and attenuation of dominant instability modes from coupling between components. In Phase II of the proposal development will focus on fluid structure interaction, structural vibrations and resonance. This will greatly enhance the current CFD technology utilized for performance analyses of valve and feed based systems and improve the ability to exert flow control, gauge system response, regulate pressure and suppress instabilities in rocket propulsion test facilities.

* information listed above is at the time of submission.

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