Turbine Burner for Near-Constant Temperature Cycle Gas Turbine Engine

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: F33615-01-C-2133
Agency Tracking Number: 001PR-1735
Amount: $0.00
Phase: Phase I
Program: SBIR
Awards Year: 2001
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
2766 Indian Ripple Rd, Dayton, OH, 45440
DUNS: 884812025
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Geoffrey Sturgess
 Senior Combustion Enginee
 (937) 252-2706
Business Contact
 Larry Goss
Title: President
Phone: (937) 429-4980
Email: gosslp@innssi.com
Research Institution
The proposed Phase II SBIR addresses the question of how the potential performance benefits demonstrated for the constant-temperature cycle aircraft gas turbine may actually be realized in an engine. The approach used is to take the engine design choicesand cycle performance for a constant-temperature cycle high bypass ratio, high thrust turbofan from the Phase I results, and layout the engine using a mean-line design process for component sizing and configuration. The proposal includes an enablingtechnology assessment, combustion component concept definition, sizing and performance evaluation, and an overall engine viability and risk assessment. The overall objective is to demonstrate that the constant-temperature cycle gas turbine engine concepthas the potential to be turned into a viable piece of turbo-machinery while achieving its performance benefits.

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

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