Vortex Universal Stoichiometric Preburner (VUSP) for Liquid Rocket Engines

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NAS8-02021
Agency Tracking Number: 012879
Amount: $70,000.00
Phase: Phase I
Program: SBIR
Awards Year: 2002
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Orbital Technologies Corporation
Space Center, 1212 Fourier Drive, Madison, WI, 53717
DUNS: N/A
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 William Knuth
 Chief Engineer
 (608) 827-5000
 knuthw@orbitec.com
Business Contact
 Eric Rice
Title: President/CEO
Phone: (608) 827-5000
Email: ricee@orbitec.com
Research Institution
N/A
Abstract
ORBITEC proposes a universal preburner as the gas generator on liquid rocket and combined cycle engine applications. The stoichiometric preburner, fitted with the appropriate downstream mixers, produces either or both fuel-rich or oxidizer-rich gas for turbine drive or tank pressurization. The preburner uses a unique vortex combustion that prevents combustion products from contacting the wall, keeping it cool. The mixer also uses the vortex flow to mix either propellant with the combustion products to quench the temperature for the turbine drive or tank pressurant use. The advantage of this innovation is that a single technology development effort will result in a new combustion device having unique performance and operational benefits for a wide range of engine cycles and propulsion systems. It avoids problems commonly encountered with conventional gas generators and preburners. It enhances engine performance. It potentially minimizes sooting problems, temperature stratification, combustion instability, and chamber/injector overheating. In Phase I, the combustor will be hot-fired with LOX/RP-1 and fuel quenching will be demonstrated. In Phase II the work will demonstrate oxidizer quenching as well as parametrically characterizing the device over a range of operating conditions and sizes. In Phase III, a universal preburner will be developed for application in an existing engine

* information listed above is at the time of submission.

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