Gas turbine engine with supersonic compressor
作者： William Byron Roberts , Shawn P. Lawlor
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摘要: A gas turbine engine having a compressor section using blades on rotor to deliver at supersonic conditions stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration the subsonic high pressure combustors. include structures changing effective contraction ratio enable starting even when designed ratios, boundary layer control. In an embodiment, are provided aspect two (2:1) more, viewed in cross-section orthogonal flow direction entrance duct.
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