Interstage cooled turbine engine

Interstage cooled turbine engine

  • CN 101,178,029 A
  • Filed: 11/09/2007
  • Published: 05/14/2008
  • Est. Priority Date: 11/10/2006
  • Status: Active Grant
First Claim
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1. a gas turbine engine (10) comprising:

  • Multistage axial compressor (18), it comprises that in a row being used to makes the compressor blade (1-7) of air (34) pressurization;

    Be arranged to the annular burner (20) with described compressor (18) circulation, it is used to make fuel (36) to mix with described pressurized air (34) and produces combustion gas (38);

    High pressure (HP) turbine (22), it comprises that a row has the HP turbine blade (44) of dovetail joint, described dovetail joint is installed in the corresponding dovetail groove (52) of the periphery that supports HP rotor disk (46), and described rotor disk is connected on the described compressor blade (1-7) by axle (30);

    Described HP dish (46) comprises from described periphery and extends internally out, and make forward surface (50) end at web (60) in the broad hub portion (62), and preceding sealing plate (56), sealing plate (56) radially extends along described forward surface (50) before described, thereby limits the annular manifold (58) that circulates with described dovetail groove (52);

    WithBe connected to the inter-stage cooling circuit (48) of described dish forward surface (50) from the intergrade (3,5) of described compressor (18), it is used for that inter-stage is discharged cooling air (34b) and guides to described dish forward surface (50) flow type.

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