You are here

Gas Turbine Pre-Compressor Cooling Using Water and Oxidizer Injection for Small Access to Space Vehicles

Award Information
Agency: Department of Defense
Branch: Defense Advanced Research Projects Agency
Contract: MDA972-03-C-0002
Agency Tracking Number: 01SB2-0161
Amount: $593,991.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Solicitation Year: N/A
Award Year: 2002
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
1925 McKinley Avenue
La Verne, CA 91750
United States
DUNS: 196694640
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Thomas Sobota
 (909) 392-3155
Business Contact
 Thomas Sobota
Title: President
Phone: (909) 392-3155
Research Institution

"The development of a pre-compressor mass injection system for extending the flight Mach number and altitude of conventional military afterburning turbo jet and turbofan engines is proposed. The injection of water and liquid oxidizer such as liquid oxygencan be used to enhance the performance of these engines so that they may power the reusable air-breathing first stage of a space access vehicle. The fluid injected into the inlet may serve three purposes. First, it can cool the air entering thecompressor so that the engine may be operated to higher flight Mach number. Second, it can increase the net mass flow through the inlet so that the engine can generate more thrust. Third, it can provide additional oxidizer so that additional fuel can beadded in the engine afterburner further augmenting the engine thrust. It is anticipated that the coolant injected upstream of the compressor may be vaporized before entering the compressor face. This minimizes the effect of the coolant injection systemon the engine operation thereby simplifying the development effort."

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

US Flag An Official Website of the United States Government