Mixing and Combustion of Gelled Propellants

Award Information
Agency: Department of Defense
Branch: Army
Contract: DAAH01-02-C-R020
Agency Tracking Number: A002-2814
Amount: $730,000.00
Phase: Phase II
Program: SBIR
Awards Year: 2002
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Space Center,, 1212 Fourier Drive, Madison, WI, 53717
DUNS: 196894869
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Martin Chiaverini
 Project Manager
 (608) 827-5000
Business Contact
 Eric Rice
Title: President/CEO
Phone: (608) 827-5000
Email: ricee@orbitec.com
Research Institution
ORBITEC proposes to continue to empirically develop and analytically model the mixing and combustion of gel propellants in the rocket combustion chamber flow field generated by innovative vortex injection schemes. The gels are injected circumferentiallytangent to the chamber wall. Streaming the propellants on the wall provides required shear to keep the non-Newtonian fluids liquefied to allow mixing and dispersion on the wall. The thin liquid film of propellants is vaporized and brought to ignitiontemperature by the adjacent swirling combustion process. CFD codes are being used to model the injection and mixing of the non-Newtonian fluids. Propellant vaporization and combustion in the flow field are included in the model. Customized subroutineswill be used to treat geometry variations, and propellant alternatives, and to link codes. In Phase II, proposed herein, chamber hot-fire testing in the form of statistical test matrices will validate and refine the model. Test results will also provideempirical evidence of performance, as well as engine durability and cooling requirements data as functions of operating conditions and geometry variables.

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

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