Invention Grant
US07870742B2 Interstage cooled turbine engine 有权
级间冷却涡轮发动机

Interstage cooled turbine engine
Abstract:
A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.
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