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