HIGHLY EFFICIENT TURBOFAN ENGINE AERO DESIGN FOR LONGER RANGE MUNITIONS

Award Information
Agency: Department of Defense
Branch: Army
Contract: W31P4Q-05-C-R106
Agency Tracking Number: A043-173-0681
Amount: $113,965.00
Phase: Phase I
Program: SBIR
Awards Year: 2005
Solitcitation Year: 2004
Solitcitation Topic Code: A04-172
Solitcitation Number: 2004.3
Small Business Information
FLORIDA TURBINE TECHNOLOGIES, INC.
6210 Keller's Church Road, Pipersville, PA, 18947
Duns: 929950012
Hubzone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 P. Dean Johnson
 President & Chief Scientis
 (561) 746-3317
 djohnson@fttinc.com
Business Contact
 Sanford Dash
Title: President & Chief Scientist
Phone: (561) 746-3317
Email: sbrostmeyer@fttinc.com
Research Institution
N/A
Abstract
Small expendable gas turbine engines historically suffer from poor specific fuel consumption (SFC) and high costs for military applications. These engines are single-shaft turbojets and their use in the propulsion system of future advanced munitions such as the Army's Non-Line of Sight Launch System Loitering Attack Munition (NLOS-LS LAM) will greatly limit the munition's operational capability. Florida Turbine Technologies, Inc. (FTT) has developed an improved design concept for an expendable gas turbine engine for use in military applications. The new concept addresses key challenges that limit the effective use of small turbojets, and provides an alternative highly efficient affordable turbofan engine. FTT focuses the current effort on the development of an optimized aerodynamic design of fan, compressor and turbine airfoils using 3D steady and unsteady advanced computational fluid dynamics (CFD). The resulting aero design can be used in subsequent mechanical design of a small engine with half the fuel consumption and significantly lower cost than today's turbojet baseline. Analytical validation of the improvement in fuel consumption over today's turbojet baseline will be provided.

* information listed above is at the time of submission.

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