GAS TURBINE ROTOR BLADE AND GAS TURBINE - MITSUBISHI HEAVY IND LTD

Title:

GAS TURBINE ROTOR BLADE AND GAS TURBINE

Document Type and Number:

WIPO Patent Application WO/2012/140806

Kind Code:

A1

Abstract:

Provided is a cooling structure of a gas turbine rotor blade, wherein cooling air which has convection cooled a fillet part is ejected from branch pipes open on the surface of a platform having small thermal stress without drilling holes in the fillet part, a blade surface, and the surface of the platform that have large thermal stress. A gas turbine rotor blade is formed from a base part which is affixed to a rotor, a platform which is affixed to the base part and provided with a cooling flow path therein, an airfoil part which extends radially outward from the platform, and a fillet part which is disposed on a surface connecting the airfoil part and the platform, and is characterized by being formed from a header pipe which branches from the cooling flow path and is open at the side end of the platform, and branch pipes which branch from the header pipe, are close to the inner side in the radial direction of the fillet part along the fillet part, and are each provided with a film hole open on the surface of the platform.

Inventors:

HADA SATOSHI (JP)

Application Number:

PCT/JP2011/077466

Publication Date:

October 18, 2012

Filing Date:

November 29, 2011

Export Citation:

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Assignee:

MITSUBISHI HEAVY IND LTD (JP)
HADA SATOSHI (JP)

International Classes:

F01D5/18

Foreign References:

JP2008202547A	2008-09-04
JPH09280002A	1997-10-28
JP2006170198A	2006-06-29
JP2009503331A	2009-01-29
JP2006170198A	2006-06-29
JP2008202547A	2008-09-04

Other References: