Turbine vane and gas turbine including the same

Patent metadata

Field	Value
Publication number	US-2021003036-A1
Application number	US-202016889447-A
Country	US
Kind code	A1
Filing date	Jun 1, 2020
Priority date	Jul 1, 2019
Publication date	Jan 7, 2021
Grant date	—

Abstract

A turbine vane and a gas turbine including the same are provided. The turbine vane including an airfoil; an outer shroud formed at a top of the airfoil; and an inner shroud including a stress canceling part formed at a bottom of the airfoil and configured to cancel a stress applied to the airfoil by flowing combustion gas.

First claim

What is claimed is:

1 . An inner shroud of a turbine vane comprising:
a platform part configured to support an airfoil; a root part configured to be connected to a bottom surface of the platform part; and a stress canceling part formed at a bottom of the airfoil and configured to cancel a stress applied to the airfoil by flowing combustion gas.

2 . The inner shroud of the turbine vane of claim 1 ,
wherein the stress canceling part comprises a protrusion configured to protrude from a bottom of one surface of the root part and a recess configured to be recessed from a bottom of the other surface of the root part.

3 . The inner shroud of the turbine vane of claim 2 ,
wherein the protrusion and the recess include inclined surfaces at predetermined angles.

4 . The inner shroud of the turbine vane of claim 3 ,
wherein the angles of the inclined surfaces are 5° to 45°.

5 . The inner shroud of the turbine vane of claim 2 ,
wherein if a length of the root part is 100, lengths of the protrusion and the recess are 5 to 30.

6 . The inner shroud of the turbine vane of claim 2 ,
wherein if a height of the root part is 100, heights of the protrusion and the recess are 10 to 40.

7 . A turbine vane comprising:
an airfoil; an outer shroud formed at a top of the airfoil; and an inner shroud including a stress canceling part formed at a bottom of the airfoil and configured to cancel a stress applied to the airfoil by flowing combustion gas.

8 . The turbine vane of claim 7 ,
wherein the inner shroud comprises a platform part configured to support the airfoil and a root part configured to be connected to a bottom surface of the platform part, and wherein the stress canceling part comprises a protrusion configured to protrude from a bottom of one surface of the root part and a recess configured to be recessed from a bottom of the other surface of the root part.

9 . The turbine vane of claim 8 ,
wherein the protrusion and the recess include inclined surfaces at predetermined angles.

10 . The turbine vane of claim 9 ,
wherein the angles of the inclined surfaces are 5° to 45°.

11 . The turbine vane of claim 8 ,
wherein if a length of the root part is 100, lengths of the protrusion and the recess are 5 to 30.

12 . The turbine vane of claim 8 ,
wherein if a height of the root part is 100, heights of the protrusion and the recess are 10 to 40.

13 . The turbine vane of claim 8 ,
wherein the root part is inserted into an annular U ring having a U-shaped cross section in a non-fixed manner, and the root part is slid radially inside the U ring based on an operating state of a gas turbine.

14 . A gas turbine comprising:
a compressor configured to compress air drawn thereinto from an outside; a combustor configured to mix fuel with air compressed by the compressor and combust a mixture of the fuel and the compressed air; and a turbine including a turbine vane configured to generate power by combustion gas discharged from the combustor and to guide the combustion gas on a combustion gas path and a turbine blade configured to be rotated by the combustion gas on the combustion gas path, wherein the turbine vane comprises an airfoil; an outer shroud formed at a top of the airfoil; and an inner shroud including a stress canceling part formed at a bottom of the airfoil and configured to cancel a stress applied to the airfoil by flowing combustion gas.

15 . The gas turbine of claim 14 ,
wherein the inner shroud comprises a platform part configured to support the airfoil and a root part configured to be connected to a bottom surface of the platform part, and wherein the stress canceling part comprises a protrusion configured to protrude from a bottom of one surface of the root part and a recess configured to be recessed from a bottom of the other surface of the root part.

16 . The gas turbine of claim 15 ,
wherein the protrusion and the recess include inclined surfaces at predetermined angles.

17 . The gas turbine of claim 16 ,
wherein the angles of the inclined surfaces are 5° to 45°.

18 . The gas turbine of claim 15 ,
wherein if a length of the root part is 100, lengths of the protrusion and the recess are 5 to 30.

19 . The gas turbine of claim 15 ,
wherein if a height of the root part is 100, heights of the protrusion and the recess are 10 to 40.

20 . The gas turbine of claim 15 ,
wherein the root part is inserted into an annular U ring having a U-shaped cross section in a non-fixed manner, and the root part is slid radially inside the U ring based on an operating state of the gas turbine.

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Joo Hyun Woo
• Jung Sung Chul

Classifications

• F01D25/04

  Antivibration arrangements · CPC title

• F01D5/10 Primary

  Anti- vibration means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title