Cooling method and structure of vane of gas turbine

Patent metadata

Field	Value
Publication number	US-11536149-B1
Application number	US-202217692667-A
Country	US
Kind code	B1
Filing date	Mar 11, 2022
Priority date	Mar 11, 2022
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

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.

First claim

What is claimed is:

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,
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.

2. The vane of the turbine according to claim 1 , wherein the shroud main body comprises:
an impingement plate disposed between the first wall and the second wall to partition the hollow space into an first region on the first wall side of the impingement plate and an second region on the second wall side of the impingement plate, the second region of the hollow space being connected with the shroud edge passage through the cooling air outlet, and the impingement plate including a plurality of air holes therethrough in the radial direction, and
a passage connecting the first region of the hollow space and an outside space on the opposite side of the second wall with respect to the hollow space, and the passage being isolated from the second region of the hollow space.

3. The vane of the turbine according to claim 2 , wherein the passage is configured to penetrate through the second wall and the impingement plate.

4. The vane of the turbine according to claim 2 , wherein the passage is configured to bypass the second wall.

5. The vane of the turbine according to claim 2 , wherein the shroud main body includes:
an exit conduit extending in the radial direction,
wherein the exit conduit includes the passage inside thereof.

6. The vane of the turbine according to claim 1 , wherein the shroud edge comprises:
a leading-side shroud edge including a leading-side shroud edge passage inside thereof,
a trailing-side shroud edge including a trailing-side shroud edge passage inside thereof,
a suction-side shroud edge including a suction-side shroud edge passage inside thereof, and,
a pressure-side shroud edge including a pressure-side shroud edge passage inside thereof,
wherein the cooling air inlet is disposed on one of the leading-side shroud edge and the trailing-side shroud edge, and the cooling air outlet is disposed on either one of the suction-side shroud edge, the pressure-side shroud edge, or the other one of the leading-side shroud edge and the trailing-side shroud edge.

7. The vane of the turbine according to claim 6 , wherein the cooling air outlet is disposed on the other one of the leading-side shroud edge and the trailing-side shroud edge.

8. The vane of the turbine according to claim 1 , wherein the shroud edge passage includes:
a turbulator disposed on an inner surface of the shroud edge passage.

9. The vane of the turbine according to claim 8 , wherein the turbulator is disposed on a bottom surface of the shroud edge passage which is the closest surface to the hot gas passage of the turbine among a plurality of inner surfaces defining the shroud edge passage.

10. The vane of the turbine according to claim 1 , wherein the cooling air inlet is communicated with an inside of the airfoil, and is configured to introduce the cooling air from the airfoil to the shroud edge passage.

11. The vane of the turbine according to claim 10 , wherein the airfoil includes:
a radially extending insert comprising a radially extending air channel inside thereof and an aperture penetrating through a side wall of the insert from an inner side surface thereof to an outer side surface thereof, and
an outer air channel between an inner side surface of the airfoil and the outer side surface of the insert,
wherein the outer air channel is connected to the cooling air inlet such that a cooling air is introduced to the air channel and is jetted through the aperture from the air channel toward the inner side surface of the airfoil and guided by the outer air channel toward the cooling air inlet.

12. The vane of the turbine according to claim 2 , wherein the cooling air inlet of the shroud edge is configured to receive a cooling air extracted from an inside of a combustor casing and compressed by an external compressor, and the passage is configured to discharge the cooling air to the inside of the combustor casing.

13. The vane of the turbine according to claim 1 , wherein the shroud edge surrounds the shroud main body entirely, and
the cooling air flows along entirety of the shroud edge.

14. 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.

15. The method of cooling the vane of the turbine according to claim 14 , further comprising:
causing the cooling air to flow inside the airfoil to cool the airfoil, and
wherein the step (i) further comprises causing the cooling air to flow inside the shroud edge passage to cool the shroud edge by using the cooling air which has flowed inside the airfoil after cooling the airfoil.

16. The method of cooling the vane of the turbine according to claim 15 , wherein the airfoil includes:
a radially extending insert comprising a radially extending air channel inside thereof,
wherein the cooling air is introduced to the air channel to cool the airfoil, and then, is guided by the airfoil toward the shroud edge passage.

17. The method of cooling the vane of the turbine according to claim 15 , wherein the airfoil includes:
a radially extending insert comprising a radially extending air channel inside thereof and an aperture penetrating through a side wall of the insert from an inner side surface thereof to an outer side surface thereof, and
an outer air channel between an inner side surface of the airfoil and the outer side surface of the insert,
wherein the cooling air is introduced to the air channel and is jetted through the aperture from the air channel toward the inner side surface of the airfoil and guided by the outer air channel toward the shroud edge passage.

18. The method of cooling the vane of the turbine according to claim 16 , wherein the radially extending air channel of the insert is configured to receive a cooling air extracted from an inside of a combustor casing and compressed by an external compressor, and the method further comprises, after cooling the shroud main body, discharging the cooling air to the inside of the combustor casing.

19. The method of cooling the vane of the turbine according to claim 14 , wherein the shr

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Mizukami Satoshi
• Flodman David Allen
• Hada Satoshi

Classifications

• F01D9/041

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

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title