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Inter-Turbine Burners for Improved Part Power Performance of Turboshaft Engines.

Award Information
Agency: Department of Defense
Branch: Army
Contract: W911W6-04-C-0020
Agency Tracking Number: A032-4049
Amount: $70,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: A03-069
Solicitation Number: 2003.2
Solicitation Year: 2003
Award Year: 2004
Award Start Date (Proposal Award Date): 2003-12-10
Award End Date (Contract End Date): 2004-06-09
Small Business Information
1925 McKinley Avenue, Suite B
La Verne, CA 91750
United States
DUNS: 196694640
HUBZone Owned: No
Woman Owned: Yes
Socially and Economically Disadvantaged: No
Principal Investigator
 Thomas Sobota
 (909) 392-3155
Business Contact
 Jane Sobota
Title: Chief Financial Officer
Phone: (909) 392-3152
Research Institution

he use of an inter-turbine burner for improving the part power performance of small turboshaft engines in proposed. An inter-turbine burner is a second combustor placed between the gas generator exit and the power turbine to "reheat" the engine gas stream before it enters the power turbine. The inter-turbine burner is used to increase engine power at the maximum power setting permitting the core engine to be run closer to its design condition at part power settings. Cycle analysis shows significant improvement in engine power with an accompanying increase in specific fuel consumption at the full power condition. The part power specific fuel consumption improves by significant at power levels below half of the maximum power. This improve specific fuel consumption at part power settings will reduce fuel consumption during the cruise/loiter segments of the UAV mission. Thus there is a net benefit to time-on-station, provided that the cruise/loiter segment is long compared to the take-off and climb segments. The increased specific thrust of the turboshaft engine with an inter-turbine burner results in a lighter engine for the same maximum power.

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

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