The overall objective of this SBIR project is the development of a novel concept for low emissions: a lean fully premixed (LFP) combustor for high overall pressure ratio small core engines. In order to achieve this major objective, a three-unit fully premixed injector has been conceptualized and proposed. Phase I scope includes design and demonstration of this injector, which will be composed of three units. The first component will execute complete fuel vaporization by heating from the hot compressed air while the second component ensures rapid and efficient premixing and the third component generates robust stability associated with a fully premixed flame. The issues of auto-ignition, flashback, static and dynamic combustion instabilities will be addressed during the design of the LFP injector. Theoretical, computational, and reduced-order modeling analyses will be utilized to design the LFP injector during Phase I. Phase II will focus on the rigorous testing of this technology as well as design refinement and optimization to be integrated with a relevant gas-turbine engine.
NASA is leading effort in Aeronautics to minimize the impact of aircraft transportation on pollutants emissions and to satisfy future FAA regulations on emissions. In this context, this technology will have significant NASA potential applications. Implementation within any engine is anticipated to reduce emissions and enhance combustion stability without compromising cold ignition, durability or cost of ownership.
Non-NASA commercial applications of a LFP injector/combustor are significant as it can be retrofit within commercial/military aircraft/rotorcraft gas turbine engines to lower emissions. Other applications include electricity generation land-based gas turbines manufacturers.