US 12,305,532 B2
Cooling method and structure of vane of gas turbine
Satoshi Mizukami, Houston, TX (US); David Allen Flodman, Houston, TX (US); and Satoshi Hada, Houston, TX (US)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed on Nov. 16, 2022, as Appl. No. 17/988,336.
Prior Publication US 2024/0159152 A1, May 16, 2024
Int. Cl. F01D 5/18 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/187 (2013.01) [F01D 9/041 (2013.01); F05D 2240/81 (2013.01); F05D 2250/291 (2013.01); F05D 2260/201 (2013.01); F05D 2260/232 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A shroud of a vane of a turbine 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, the shroud edge passage is disposed along the circumference of the shroud main body,
wherein 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,
wherein 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, each of the sub-passages is entirely disposed in the shroud edge along the circumference of the shroud main body to surround the shroud main body,
wherein the shroud edge comprises:
a leading-side shroud edge positioned at an upstream end portion of the shroud edge with respect to a flow of hot gas in the turbine,
a trailing-side shroud edge positioned at a downstream end portion of the shroud edge with respect to the flow of hot gas in the turbine,
a suction-side shroud edge positioned on a suction side of the shroud edge with respect to the flow of hot gas in the turbine, and
a pressure-side shroud edge positioned on a pressure side of the shroud edge with respect to the flow of hot gas in the turbine,
wherein one of the three or more sub-passages includes a cooling air inlet thereof located at a longitudinal middle of one of the leading-side shroud edge, the trailing-side shroud edge, the suction-side shroud edge and the pressure-side shroud edge, and includes a cooling air outlet thereof located at a longitudinal middle of another one of the leading-side shroud edge, the trailing-side shroud edge, the suction-side shroud edge and the pressure-side shroud edge,
wherein the shroud edge passage is divided into four sub-passages by the plurality of cooling air inlets and the plurality of cooling air outlets,
wherein the plurality of cooling air inlets include a first cooling air inlet disposed at a middle portion of the leading-side shroud edge and a second cooling air inlet disposed at a middle portion of the trailing-side shroud edge, and the plurality of cooling air outlets include a first cooling air outlet disposed at a middle portion of the suction-side shroud edge and a second cooling air outlet disposed at a middle portion of the pressure-side shroud edge,
wherein the sub-passages comprise:
a first sub-passage bordered by the first cooling air inlet and the first cooling air outlet,
a second sub-passage bordered by the first cooling air inlet and the second cooling air outlet,
a third sub-passage bordered by the second cooling air inlet and the first cooling air outlet, and
a fourth sub-passage bordered by the second cooling air inlet and the second cooling air outlet.