Turbine vane equipped with insert support

Patent metadata

Field	Value
Publication number	US-11098602-B2
Application number	US-201916294947-A
Country	US
Kind code	B2
Filing date	Mar 7, 2019
Priority date	Apr 17, 2018
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

Disclosed is a turbine vane having a turbine vane airfoil extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side that extend from the leading edge to the trailing edge, wherein a plurality of cavities defined by a plurality of ribs extending from the pressure side to the suction side is formed in the turbine vane airfoil, at least one of the cavities is provided with a plurality of insert supports protruding inward from an inner surface of the turbine vane airfoil, and the insert supports are arranged in a circumferential direction of the cavity and arranged in a plurality of rows arranged in a radial direction.

First claim

What is claimed is:

1. A turbine vane comprising:
a turbine vane airfoil extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein a plurality of cavities defined by a plurality of ribs extending from the pressure side to the suction side is formed in the turbine vane airfoil, at least one of the cavities is provided with a plurality of insert supports formed to protrude from an inner surface of the turbine vane airfoil, and the plurality of insert supports is arranged separately inside the cavity at intervals in a circumferential direction of the cavity and is arranged in a plurality of rows that is arranged at intervals in a radial direction,
wherein the plurality of insert supports in the rows arranged in the radial direction of the cavity is arranged such that heights of the plurality of insert supports show a linear change in the radial direction in which the rows of the insert supports are arranged.

2. The turbine vane according to claim 1 , wherein a number of the insert supports arranged at intervals in the circumferential direction of the cavity is three or four.

3. The turbine vane according to claim 1 , wherein the plurality of insert supports are disposed on the pressure side and the suction side of the inner surface of the turbine vane airfoil and at a border between the pressure side and a rib of the plurality of ribs or a border between the suction side and a rib of the plurality of ribs.

4. The turbine vane according to claim 3 , wherein the plurality of insert supports formed on the pressure side and the suction side of the inner surface of the turbine vane airfoil have a rectangular-shaped cross section and the insert support of the plurality of insert supports formed at the border between the pressure side and the rib or the border between the suction side and the rib has a triangular-shaped cross section.

5. The turbine vane according to claim 3 , wherein one insert support of the plurality of insert supports is disposed on each of the pressure side and the suction side of the inner surface of the turbine vane airfoil and one insert support of the plurality of insert supports is disposed at the border between the pressure side and the rib or the border between the suction side and the rib, so that a three-point structure is configured.

6. The turbine vane according to claim 3 , wherein one insert support of the plurality of insert supports is disposed on each of the pressure side and the suction side of the inner surface of the turbine vane airfoil and one insert support of the plurality of insert supports is disposed at each of the border between the pressure side and the rib and the border between the suction side and the rib, so that a four-point structure is configured.

7. The turbine vane according to claim 1 , wherein two insert supports of the plurality of insert supports are disposed respectively on the pressure side and the suction side of the inner surface of the turbine vane airfoil and one insert support of the plurality of insert supports is disposed at the border between the pressure side and the rib or the border between the suction side and the rib, so that a three-point structure in which three supporting points are disposed in two consecutive rows is formed.

8. The turbine vane according to claim 1 , wherein two insert supports of the plurality of insert supports are disposed respectively on the pressure side and the suction side of the inner surface of the turbine vane airfoil and two insert supports of the plurality of insert supports are disposed at the border between the pressure side and the rib and the border between the suction side and the rib, so that a four-point structure in which four supporting points are disposed in two consecutive rows is formed.

9. A turbine vane assembly comprising:
a turbine vane having a turbine vane airfoil extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side that extend from the leading edge to the trailing edge, wherein a plurality of cavities defined by a plurality of ribs extending from the pressure side to the suction side is formed in the turbine vane airfoil, at least one of the cavities is provided with a plurality of insert supports protruding inward from an inner surface of the turbine vane airfoil, the plurality of insert supports are arranged separately inside the cavity in a circumferential direction of the cavity and arranged in a plurality of rows arranged in a radial direction; and
a pipe-shape insert inserted in the cavity, supported by the plurality of insert supports, and provided with a plurality of through holes formed in a surface thereof,
wherein the plurality of insert supports in the rows arranged in the radial direction of the cavity is arranged such that heights of the plurality of insert supports show a linear change starting from an insert inlet through which the insert is inserted into the cavity of the turbine vane airfoil.

10. The turbine vane assembly according to claim 9 , wherein the insert has a cross-sectional shape similar to a cross-sectional shape of the cavity, resulting in a structure in which an annular space formed between the inner surface of the turbine vane airfoil and the cavity has a uniform width.

11. The turbine vane assembly according to claim 9 , wherein a number of the insert supports arranged at intervals in the circumferential direction of the cavity is three or four.

12. The turbine vane assembly according to claim 9 , wherein the plurality of insert supports are disposed on the pressure side and the suction side of the inner surface of the turbine vane airfoil and at a border between the pressure side and a rib of the plurality of ribs or a border between the suction side and a rib of the plurality of ribs.

13. The turbine vane assembly according to claim 12 , wherein the plurality of insert supports formed on the pressure side and the suction side of the inner surface of the turbine vane airfoil have a rectangular-shaped cross section and the insert support of the plurality of insert supports formed at the border between the pressure side and the rib or the border between the suction side and the rib has a triangular-shaped cross section.

14. The turbine vane assembly according to claim 12 , wherein one insert support of the plurality of insert supports is disposed on each of the pressure side and the suction side of the inner surface of the turbine vane airfoil and one insert support of the plurality of insert supports is disposed at the border between the pressure side and the rib or the border between the suction side and the rib, so that a three-point structure is configured.

15. The turbine vane assembly according to claim 12 , wherein one insert support of the plurality of insert supports is disposed on each of the pressure side and the suction side of the inner surface of the turbine vane airfoil and one insert support of the plurality of insert supports is disposed at each of the border between the pressure side and the rib and the border between the suction side and the rib, so that a four-point structure is configured.

16. The turbine vane assembly according to claim 9 , wherein two insert supports of the plurality of insert supports are disposed respectively on the pressure side and the suction side of the inner surf ace of the turbine vane airfoil and one insert support of the plurality o

Assignees

• Doosan Heavy Ind & Construction Co Ltd

Inventors

• Lee Hyuk Hee
• Jung Sung Chul

Classifications

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F05D2240/126

  Baffles or ribs · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/06

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title