GAS TURBINE STATIONARY BLADE AND GAS TURBINE

WIPO Patent Application WO/2024/048211

A1

Provided is a gas turbine stationary blade. When a plane including a thickness direction and a blade height direction of a leading edge part at the center of an inlet of a first film cooling hole is defined as a first plane, the center of an outlet of the first film cooling hole is positioned on the downstream side in a flow of combustion gas of a position at which the first plane and an outer surface of the leading edge part intersect each other. When a plane including the thickness direction and the blade height direction of the leading edge part at the center of an inlet of a second film cooling hole is defined as a second plane, an outlet of the second film cooling hole is positioned at a place at which the second plane and the outer surface of the leading edge part intersect each other. When a plane including the thickness direction and the blade height direction of the leading edge part at the center of an inlet of a third film cooling hole is defined as a third plane, the center of an outlet of the third film cooling hole is positioned on the downstream side in the flow of combustion gas of a position at which the third plane and the outer surface of the leading edge part intersect each other.

MIYAHISA YASUO (JP)
MATSUO SAKI (JP)
TORII SHUNSUKE (JP)

PCT/JP2023/028722

March 07, 2024

August 07, 2023

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MITSUBISHI HEAVY IND LTD (JP)
MITSUBISHI POWER LTD (JP)

F01D9/02; F02C7/18

US20140093379A1	2014-04-03
JPH05163959A	1993-06-29
JP2000230402A	2000-08-22
JP2008051107A	2008-03-06
JP2001507773A	2001-06-12
JP2009144724A	2009-07-02

SSIP PATENT ATTORNEY CORPORATION (JP)

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