Mitsubishi Heavy Industries Limited

Hiroki Kitada

Hiroyuki Otomo

Satoshi Hada

Shunsuke Torii

Naoya Tatsumi

Yasumasa Kunisada

Ryo Murata

Yuji Komagome

A platform of a gas turbine rotor blade according to one embodiment includes a groove portion recessed from an end surface on a trailing edge side toward a leading edge side. A bottom portion of the groove portion overlaps at least a blade-shaped portion when viewed from a radial direction. When a pressure-side end portion of the platform with respect to the bottom portion is defined as a first point, a tangent line that is a tangent line with respect to the bottom portion, extending along a plane intersecting the radial direction at the first point is defined as a first tangent line, when an intersection between a line segment connecting the bottom portion and an end portion on the trailing edge side of a serpentine cooling flow path provided inside the blade-shaped portion when viewed from the radial direction and an end portion on the trailing edge side of the blade-shaped portion is defined as a second point, a tangent line that is a tangent line with respect to the bottom portion, extending along the plane at the second point is defined as a second tangent line, and when an intersection between the first tangent line and the second tangent line when viewed from the radial direction is defined as a third point. As viewed from the radial direction, the third point exists on a side opposite to the end portion on the trailing edge side of the blade-shaped portion across a straight line connecting the first point and the second point.

Gas turbine rotor blade and gas turbine

A turbine rotor blade includes a leading edge portion having a plurality of cooling holes. The plurality of cooling holes includes: m cooling holes arranged in a first range in the blade height direction, where m is an integer of 2 or more; and n cooling holes arranged in a second range on the blade tip side of the first range in the blade height direction, where n is an integer of 2 or more, and n/b<m/a is satisfied, where a is the dimension of the first range in the blade height direction, and b is the dimension of the second range in the blade height direction.

Turbine rotor blade and gas turbine

A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.

Turbine rotor blade, turbine, and tip clearance measurement method

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Yokohama, Japan

Hiroki Kitada