Title:
TIP SHROUD FOR GAS TURBINE MOVING BLADE
Document Type and Number:
Japanese Patent JPH1113403
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To effectively flow out cooling air to a tip shroud to prolong a creep life, in a moving blade tip shroud used in the rear stage in a gas turbine. SOLUTION: Clearance parts 12 and 13; passed by high-temperature combustion gas, and receiving influence of thermal stress; are provided on a tip shroud 11, and are portions apt to cause creep; and grooves 31, 32, 33, and 34 and cooling guide lids 21 and 22 are provided respectively on the shroud surface. The cooling guide lids 21 and 22 are closed at one side by members 21a and 22a, and are opened at another side to cover air holes 17; and lets flow cooling air to each of the clearance parts 12 and 13 to flow out the cooling air so as to cool these clearance parts 12 and 13. The metal temperature rise in the clearance parts 12 and 13, receiving the influence of the high temperature combustion gas, can be restrained to prolong the creep life of the tip shroud 11.
Inventors:
AI TOSHISHIGE
Application Number:
JP17018297A
Publication Date:
January 19, 1999
Filing Date:
June 26, 1997
Export Citation:
Assignee:
MITSUBISHI HEAVY IND LTD
International Classes:
F01D5/08; F01D5/18; F01D5/20; F01D5/22; F02C7/18; (IPC1-7): F01D5/18; F01D5/08; F01D5/22; F02C7/18
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