High-Fidelity Multiphysics Simulations of Nozzle Erosion

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0006-10-C-7390
Agency Tracking Number: B09B-009-0003
Amount: $99,999.00
Phase: Phase I
Program: STTR
Awards Year: 2010
Solicitation Year: 2009
Solicitation Topic Code: MDA09-T009
Solicitation Number: 2009.B
Small Business Information
P. O. Box 3001, Champaign, IL, 61826
DUNS: 792045713
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Mark Brandyberry
 Chief Operating Officer
 (217) 766-2567
Business Contact
 William Dick
Title: Chief Executive Officer
Phone: (217) 417-0885
Email: wdick@illinoisrocstar.com
Research Institution
 University of Illinois
 Kathy Young
 OSPRA, 1901 S. First
Champaign, IL, 61820
 (217) 333-2187
 Nonprofit college or university
A collaborative effort is proposed between IllinoisRocstar LLC and the University of Illinois to develop and commercialize a computational framework to investigate nozzle erosion in solid-propellant rocket motors (SRM) and tangential instability modes in liquid rocket engines (LRE). For SRM, highly resolved simulations will be performed to understand the effects of turbulent inlet conditions, as well as nozzle vectoring, on nozzle erosion. The thermal boundary layer is captured along the nozzle walls to compute the heat flux and erosion rates. To optimize the computational resources, the SRM nozzle configuration is studied by itself and appropriate inflow conditions are imposed. Two complementary formulations to apply these inlet conditions are described: the first is based on extracting the flow field from the full motor configuration for turbulent flows; while the second invokes a multiscale asymptotic analysis of turbulent flows inside rocket motor. Preliminary results suggest that specifying turbulent, rather than uniform, inlet conditions has a significant effect on nozzle erosion. For LRE, a full three-dimensional configuration is proposed to investigate tangential instabilities.

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

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