Advanced High Temperature Capable Materials and Coatings Integration with 200 lbt Low-Cost Turbojet for Increased Performance

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-19-P-2032
Agency Tracking Number: F182-059-0968
Amount: $150,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF182-059
Solicitation Number: 2018.2
Solicitation Year: 2018
Award Year: 2019
Award Start Date (Proposal Award Date): 2018-11-30
Award End Date (Contract End Date): 2019-11-30
Small Business Information
450 Frontier Way, Unit D, Bensenville, IL, 60106
DUNS: 615345329
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Christopher Spytek
 (630) 595-9133
Business Contact
 Elizabeth Spytek
Phone: (630) 595-9133
Research Institution
The role of class III UAVs is becoming prevalent for high altitude DOD operations.Turbine engine concepts, capable of long lives and reliability, with minimal maintenance, high fuel efficiency, altitude capability, low noise, operating in austere environments, produced at low cost are required.Spytek proposes to use its newly developed J302-GMX-2 200 lbt turbojet developed under a SOSSEC/LCMC contract, modifying it with advanced ceramics in the hot section for improved performance. The J302 engine leverages low cost engine build technologies to produce a low cost turbo-jet engine. The focus of the SOSSEC engine development is producibility and low cost manufacture with maximized performance.Target unit costs are $16,800.The project objective for this Phase I SBIR is a study/manufacture/test effort to apply advanced materials and coatings to improve the engine efficiency, boosting temperature capability, and durability of the engine. This includes low cost and high performance, design concepts and technologies such as ceramics and TBCs in the engine combustor/turbine and possibly TBCs in the compressor, creating an innovative 200+ lbt turbine engine propulsion system for class III Unmanned Aerial Vehicles (UAVs) taking advantage of higher turbine inlet temperatures and possibly higher overall pressure ratio (OPR) for maximum efficiency.

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

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