Cooling method and structure of vane of gas turbine

Patent metadata

Field	Value
Publication number	US-12305532-B2
Application number	US-202217988336-A
Country	US
Kind code	B2
Filing date	Nov 16, 2022
Priority date	Nov 16, 2022
Publication date	May 20, 2025
Grant date	May 20, 2025

Abstract

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.

First claim

What is claimed is:

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.

2. The shroud of the vane of the turbine according to claim 1 , wherein each of the sub-passages has one of the plurality of cooling air inlets at one end thereof and one of the plurality of cooling air outlets at an opposite end thereof so as to have an airtight passage from the one end thereof through the opposite end thereof.

3. The shroud of the vane of the turbine according to claim 1 , wherein at least one of the plurality of the cooling air inlets is positioned at a downstream end portion of the shroud edge with respect to a flow of hot gas in the turbine.

4. The shroud of the vane of the turbine according to claim 1 ,
wherein the plurality of the cooling air inlets include a first cooling air inlet disposed to the leading-side shroud edge and a second cooling air inlet disposed to the trailing-side shroud edge.

5. The shroud of the vane of the turbine according to claim 1 , wherein the plurality of cooling air outlets are connected to the shroud main body to cause the cooling air to flow out of the shroud edge passage into the shroud main body.

6. The shroud of the vane of the turbine according to claim 5 , wherein the shroud main body includes a hollow space inside thereof, and the cooling air is caused to flow out of the shroud edge passage into the hollow space.

7. The shroud of the vane of the turbine according to claim 1 , wherein the shroud edge surrounds the shroud main body entirely.

8. The shroud of the vane of the turbine according to claim 1 ,
wherein the suction-side shroud edge comprises a suction-side shroud edge passage therein, and the pressure-side shroud edge comprises a pressure-side shroud edge passage therein, and
the suction-side shroud edge passage or the pressure-side shroud edge passage is divided by a partition wall.

9. The shroud of the vane of the turbine according to claim 1 , wherein the first cooling air outlet is partitioned by a partition wall into a leading-side first cooling air outlet bordering the first sub-passage and a trailing-side first cooling air outlet bordering the third sub-passage,
the second cooling air outlet is partitioned by a partition wall into a leading-side second cooling air outlet bordering the second sub-passage and a trailing-side second cooling air outlet bordering the fourth sub-passage.

10. The shroud of the vane of the turbine according to claim 1 , wherein the shroud main body comprises a hollow space inside thereof, the hollow space being connected with the shroud edge passage through the plurality of cooling air outlets to cause the cooling air to flow out of the shroud edge passage through the plurality of cooling air outlets into the hollow space.

11. The shroud of the vane of the turbine according to claim 1 , wherein each of the sub-passages has a cooling air inlet at one end thereof and a cooling air outlet at an opposite end thereof so as to have an airtight passage from the one end thereof through the opposite end thereof.

12. 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

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Mizukami Satoshi
• Flodman David Allen
• Hada Satoshi

Classifications

• F05D2240/81

  Cooled platforms · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/232

  characterized by the cooling medium · CPC title

• F05D2250/291

  hollowed · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title