Mitsubishi Heavy Industries Limited

Yasumasa Kunisada

Satoshi Hada

Saki Matsuo

Masamitsu Kuwabara

Satoshi Mizukami

Yoshitaka Uemura

Ryozo Tamura

Ryo Tanaka

Takuro Kameda

Hiroyuki Otomo

David Allen Flodman

Hiroki Kitada

Yusuke Akada

A shroud of a vane of a turbine is provided. The shroud includes a shroud main body comprising a first wall having a gas-passage face facing a hot gas passage of the turbine and a cooling face facing opposite to the hot gas passage, a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein, and an impingement box disposed to face the cooling face of the first wall so as to be spaced apart from the cooling face of the first wall. The impingement box comprises a cooling air inlet to introduce a cooling air from the shroud edge passage into an inside of the impingement box, and an impingement air hole configured to jet the introduced cooling air to the cooling face of the first wall to cool the cooling face of the first wall.

Structure of cooling turbine vane shroud and manufacturing method thereof

A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Turbine blade

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

Turbine blade and method for manufacturing the turbine blade

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

Yasumasa Kunisada