Small gas turbine engine having enhanced fuel economy

摘要: A gas turbine engine ducted to have the air pass sequentially through a single stage axial-flow compressor, single-stage hybrid axial-radial centrifugal burner, an inward flow radial turbine, axial-flow, high-pressure and then exit nozzles. The axial compressor are on common core shaft. porous hub form integral, modular unit in which forces blades drive compressor. permits transpire from serving cool turbine. Fuel is burned annular, "folded-comma" shaped burners with multiple fuel-injection ignition zones (two combustion). path has outer annular duct, first inner duct second burner. shares walls ducts. located between burner duct. portion of section.