Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Hisato Tagawa

Yasuhiro Horiuchi

Shinichi Higuchi

Tetsuro Morisaki

Manabu Yagi

Kenji Shingai

Takemitsu Miura

In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

Gas turbine transition seal with hole through seal plate in groove of nozzle

The invention provides a gas turbine blade that is capable of reducing the temperature difference between the pressure side and the suction side even if the trailing-edge cooling channel is narrow, thereby lessening thermal stress as well. A gas turbine bladecomprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surfaceand a pressure-side cooling target surfacethat face each other; and multiple vortex-generator-shaped finsdisposed between the two cooling target surfacesandsuch that the finsconnect the two cooling target surfacesand. Each of the vortex-generator-shaped finsincludes an oblique surfacelocated on the downstream side of the flow direction of a cooling medium. A normal lineto the oblique surfaceintersects with one of the two cooling target surfacesand

Gas turbine blade

A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction. Cooling holes are disposed in the leading edge side hook portion of the end wall portion. The plurality of cooling holes are arranged at different distance of intervals in the circumferential direction of the gas turbine. Cooling air that has flowed in the cooling passage is configured to flow from the cooling holes toward the leading edge of the end wall portion.

Gas turbine airfoil

A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.

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Yokohama, Japan

Hisato Tagawa