This Phase I SBIR proposal will evaluate an innovative method for obtaining a more uniform dispersion of smaller fuel droplets and prevent droplet coalescing in order to reduce flame hot spots by several hundred degrees. If successful, this SBIR program has the potential to ease stage I turbine nozzle design and reduce Nox formation during high power engine operation.The basic Air Assist Fuel Atomization system operating principle is to (1) extract a small amount of compressor discharge air, (2) further compress it by approximately 25% in a engine mounted turbocompressor, and then (3) insert the compressed air into the fuel nozzle upstream of the exit orifice in an innovative mixing chamber.The test apparatus to be used in the Phase I test program will be fabricated to Grey Fox Technologies' specifications. The proposed Phase I work plan will be centered on two test segments. The first test segment will be comprised of simple, understandable tests using different air/water ratios and mechanical mixing configurations. The second test segment will consist of a more precise measurement of the actual droplet sizes for the most promising air/fuel ratios and mechanical mixing configuration. The Air Assisted Fuel Atomization system has a significant world wide commercial and military market potential for advanced high compressor pressure ratio and turbine inlet temperature aircraft engine applications. This innovative system also has a substantial marine and industrial gas turbine market potential.o Advanced Subsonic Transportso Advanced Supersonic Transportso Marine and Industrial Gas Turbine Applications
Keywords: Phase_I, NASA, Abstract, FY94
