Cooling method and structure of vane of gas turbine
AssigneeMitsubishi Heavy Industries, Ltd.
InventorsSatoshi Mizukami, David Allen Flodman, Satoshi Hada
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Abstract
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.
Claims20
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,
- wherein the shroud comprises:
- a shroud main body comprising a first wall facing a hot gas passage of the turbine, a second wall disposed on an opposite side of the first wall with respect to the hot gas passage, 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,
- wherein the shroud edge comprises a cooling air inlet to introduce a cooling air into the shroud edge passage and a cooling air outlet to cause the cooling air to flow out of the shroud edge passage,
- wherein the shroud main body comprises a hollow space inside thereof between the first wall and the second wall, the hollow space being connected with the shroud edge passage through the cooling air outlet.
A method of cooling a vane of a turbine, the turbine comprising 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,
- wherein the method comprising steps of:
- (i) causing a cooling air to flow inside the shroud edge passage to cool the shroud edge;
- and
- (ii) after cooling the shroud edge, cooling the shroud main body by using the cooling air which has flowed inside the shroud edge passage.
A method of cooling a vane of a turbine, the turbine comprising 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,
- wherein the method comprising steps of:
- (i) causing a cooling air to flow inside the airfoil to cool the airfoil;
- (ii) after cooling the airfoil, cooling either one of the shroud main body or the shroud edge by using the cooling air which has flowed inside airfoil;
- and
- (iii) after cooling either one of the shroud main body or the shroud edge, cooling the other one of the shroud main body or the shroud edge by using the cooling air which has cooled either one of the shroud body or the shroud edge.
Dependencies are inferred from the claim text.