US 11,982,206 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 Mar. 11, 2022, as Appl. No. 17/692,572.
Prior Publication US 2023/0287796 A1, Sep. 14, 2023
Int. Cl. F01D 5/18 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/189 (2013.01) [F01D 5/18 (2013.01); F01D 5/187 (2013.01); F01D 5/188 (2013.01); F01D 9/041 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2260/232 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A vane for a turbine comprising:
an airfoil; and
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 an outer shroud disposed at a radially outer end of the airfoil in the radial direction of the turbine and an inner shroud disposed at a radially inner end of the airfoil in the radial direction of the turbine,
wherein the airfoil comprises a plurality of air channels extending along the radial direction of the turbine, the air channels comprising a one air channel and an another air channel,
the airfoil comprises an air inlet configured to introduce cooling air from outside of the vane to the one air channel and the another air channel,
the one air channel is communicated with one of the outer shroud and the inner shroud to cause the cooling air introduced to the one air channel to flow toward the one of the outer shroud and the inner shroud to cool the one of the outer shroud and the inner shroud,
the another air channel is communicated with the other one of the outer shroud and the inner shroud to cause the cooling air introduced to the another air channel to flow toward the other one of the outer shroud and the inner shroud to cool the other one of the outer shroud and the inner shroud, and
the outer shroud comprises an outer shroud main body and an outer shroud edge disposed on a circumference of the outer shroud main body to surround the outer shroud main body, the outer shroud edge comprising an outer shroud edge passage therein,
the inner shroud comprises an inner shroud main body and an inner shroud edge disposed on a circumference of the inner shroud main body to surround the inner shroud main body, the inner shroud edge comprising an inner shroud edge passage therein,
the one air channel is communicated with the outer shroud edge passage, and
the another air channel is communicated with the inner shroud edge passage,
wherein the one air channel is a leading end air channel positioned at an upstream end of the airfoil with respect to a flow of hot gas in the turbine, and
wherein the another air channel is an air channel positioned on a downstream side of the leading end air channel.