Title:
TIP SHROUD FOR GAS TURBINE COOLING BLADE
Document Type and Number:
Japanese Patent JPH1113402
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To increase the cooling efficiency of a moving blade tip shroud, thin- walled and lightweight, for use in a gas turbine rear stage by smoothing the flow of cooling air. SOLUTION: Cooling air holes 13-16, having long hole shapes, are provided in the inside of the tip shroud 11 of a moving blade 10, and are opened in both side surface to flow out cooling air from the moving blade 10 inside. Cooling air holes 20, for communicating the moving blade 10 inside with a high pressure side in a combustion gas flow direction R, are provided on the upper surface of the tip shroud 11 to flow out the cooling air, and the cooling air flows to a low-pressure side from the high pressure side to cool a high stress part Y. A high stress part X is similarly cooled by cooling air from an adjoining moving blade. The cooling air flows widely by the long hole shapes of the cooling air holes 13-16 to cool the surface of the tip shroud 11, and moreover the high-stress parts X and Y too are resultantly cooled by the cooling air holes 20.
Inventors:
FUKUNO HIROKI
TOMITA YASUO
ITO EISAKU
TOMITA YASUO
ITO EISAKU
Application Number:
JP16591797A
Publication Date:
January 19, 1999
Filing Date:
June 23, 1997
Export Citation:
Assignee:
MITSUBISHI HEAVY IND LTD
International Classes:
F01D5/08; F01D5/18; F01D5/20; F01D5/22; F01D11/10; F02C7/18; (IPC1-7): F01D5/18; F01D5/08; F01D5/20; F01D5/22; F02C7/18
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