Mitsubishi Heavy Industries Limited

David Allen Flodman

Satoshi Mizukami

Satoshi Hada

Ryo Tanaka

Takuro Kameda

Saki Matsuo

Yasumasa Kunisada

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 shroud of a vane of a turbine is provided. The shroud comprises a shroud main body; and 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, the shroud edge passage is disposed along the circumference of the shroud main body. The shroud edge comprises a plurality of cooling air inlets configured to introduce a cooling air into the shroud edge passage from outside of the shroud edge, and a plurality of cooling air outlets configured to cause the cooling air to flow out of the shroud edge passage to the outside of the shroud edge. The shroud edge passage is divided into three or more sub-passages by the plurality of cooling air inlets and the plurality of cooling air outlets.

Cooling method and structure of vane of gas turbine

A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, an outer shroud disposed at an outer radial end of the airfoil and an inner shroud, the airfoil including a plurality of air channels extending along the radial direction of the turbine, the air channels comprising a first air channel and a second air channel. A cooling air is caused to flow inside the first air channel to cool the first air channel, then cool one of the outer shroud and the inner shroud. A cooling air is caused to flow inside the second air channel to cool the second air channel, then cool the other one of the outer shroud and the inner shroud.

A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, a shroud disposed at an end of the airfoil, the end being a radial end along a radial direction of the turbine, the shroud comprising a shroud main body and 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. A cooling air is caused to flow inside the shroud edge passage to cool the shroud edge, and after cooling the shroud edge, the shroud main body is cooled by using the cooling air which has flowed inside the shroud edge passage.

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Houston, TX, United States of America

David Allen Flodman