Robust Cryogenic Cavitation Modeling for Propulsion Systems Ground Test Facilities

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX16CS14P
Agency Tracking Number: 156333
Amount: $125,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: H10.02
Solicitation Number: N/A
Solicitation Year: 2016
Award Year: 2016
Award Start Date (Proposal Award Date): 2016-06-10
Award End Date (Contract End Date): 2016-12-09
Small Business Information
420 Park Avenue West, Princeton, IL, 61356-1934
DUNS: 000000000
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Rex Chamberlain
 Principal Investigator
 (815) 872-0702
Business Contact
 Rex Chamberlain
Title: Business Official
Phone: (815) 872-0702
Research Institution
Rigorous ground testing mitigates space propulsion system risk by enabling advanced component and system level rocket propulsion development and by demonstrating that designs reliably meet the specified requirements over the operational envelope before the first flight. The development of advanced ground test technology components and systems that are capable of enhancing environment simulation, minimizing program test time, cost and risk and meeting environmental and safety regulations is focused on near-term products that augment existing state-of-the-art propulsion system test facilities. Thus improved capabilities to model and predict component behavior in harsh ground test environments are needed for enhanced facility design. In particular, components such as valves, check valves and chokes that are subjected to high pressure, high flow rate cryogenic environments will experience potentially damaging two phase flow effects such as cavitation. Robust cryogenic cavitation models for real fluids equations of state in the presence of mixed supersonic/subsonic flows are demonstrated to deal with poor solution convergence and numerical instabilities. The proposed innovation leverages modifications to the local preconditioning formulation of the Roe flux with a barotropic equation of state and uses a representative component flow problem to demonstrate the effectiveness of enhanced modifications to the cryogenic liquid tabular equation of state. Instabilities arising from the single temperature assumption in the two phase mixture equation of state, which must often be evaluated by extrapolating data too far from the saturation curve, are eliminated with a nonlinear temperature limiter that precludes non-physical behavior, such as imaginary mixture sound speeds. The result is an efficient, robust cryogenic cavitation model suitable for application to propulsion systems ground test facility component design and analysis efforts.

* Information listed above is at the time of submission. *

US Flag An Official Website of the United States Government