发明名称 IMPINGEMENT COOLING OF GAS TURBINE SHROUD
摘要 PROBLEM TO BE SOLVED: To maximize the impingement cooling efficiency by eliminating a leakage path to a cooling current flowing to an inner shroud segment inlet, and minimizing a distance of the collision current between the opening of a baffle plate and a surface of a wall to be cooled. SOLUTION: An inner shroud 22 is connected to an outer shroud 20, and the outer shroud 20 receives the cooling air through an inlet 54 to make the cooling air flow to the inner shroud. The inner shroud has a wall 42 for partially defining a heat gas path 16, and plural cavities 44 at a side opposite to the heat gas path of the wall. The inner shroud includes a cover 40, partition chambers 52 are suspended from the cover, and opening 56 are formed through floors of the partition chambers 52. When the cover is placed on the inner shroud body, the partition chambers are accommodated in the cavities, the cooling air from the inlet flows into the partition chambers, passes through the openings, and impinges on the wall of the inner shroud for cooling the same. The used cooling air is discharged from the inner shroud through a path 45 penetrating through a sidewall circumferentially or axially faced to the inner shroud and/or the wall of the inner shroud defining the heat gas path.
申请公布号 JP2001221065(A) 申请公布日期 2001.08.17
申请号 JP20000032592 申请日期 2000.02.10
申请人 GENERAL ELECTRIC CO <GE> 发明人 STEVEN SEBASTIAN BURDICK
分类号 F01D11/08;F02C7/18;(IPC1-7):F02C7/18 主分类号 F01D11/08
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