TURBINE VANE, RING SEGMENT, AND GAS TURBINE INCLUDING THE SAME

• US 20200131914A1
• Filed: 08/16/2019
• Published: 04/30/2020
• Est. Priority Date: 10/29/2018
• Status: Active Grant

• Current Assignee: Doosan Heavy Industries and Construction Company Limited
• Original Assignee: Doosan Heavy Industries and Construction Company Limited
• Inventors: LEE, Chang Yong
• Granted Patent: US 11,149,557 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/2212 by creating turbulence

Abstract

A turbine vane is provided. The turbine vane may include a sidewall configured to form an airfoil including a leading edge and a trailing edge, an insert configured to be inserted inside the sidewall such that a gap is formed between the insert and an inner surface of the sidewall and include a plurality of insert holes, and a plurality of guides extending from the sidewall and configured to guide a flow of cooling fluid through the gap, wherein the plurality of guides guide cooling fluid drawn through the insert holes to prevent the cooling fluid from interfering with a flow of cooling fluid drawn through a subsequent insert hole.

Claims

1. A turbine vane comprising:

a sidewall configured to form an airfoil including a leading edge and a trailing edge;

an insert configured to be inserted inside the sidewall such that a gap is formed between the insert and an inner surface of the sidewall and include a plurality of insert holes; and

a plurality of guides extending from the sidewall and configured to guide a flow of cooling fluid through the gap,

wherein the plurality of guides guide cooling fluid drawn through the insert holes to prevent the cooling fluid from interfering with a flow of cooling fluid drawn through a subsequent insert hole.

2. The turbine vane according to claim 1, wherein the plurality of guides contact with a surface of the insert.

3. The turbine vane according to claim 2,

wherein the plurality of insert holes are arranged to form a plurality of rows and a plurality of columns, and

wherein insert holes of each of the columns are arranged to alternate with insert holes of a subsequent column.

4. The turbine vane according to claim 3, wherein each of the plurality of guides comprises:

an upstream end disposed at an upstream side of a gap flow;

a pair of sidewalls disposed to enclose an upstream side part of the insert hole; and

downstream ends disposed on respective sidewalls at left and right sides of the insert hole with respect to a gap flow direction.

5. The turbine vane according to claim 4, wherein the plurality of guides are arranged such that a distance between a downstream end of a guide on each of the rows and a downstream end of a guide on a subsequent row is ⅓

to 3 times a diameter of the insert hole.

6. The turbine vane according to claim 5, wherein the plurality of guides are arranged such that a distance between an upstream end of a guide on each of the columns and an upstream end of a guide on a subsequent column with respect to the gap flow direction is 3 to 10 times the diameter of the insert hole.

7. The turbine vane according to claim 4, wherein the guide further includes an impingement part integrally coupled to the upstream end and disposed perpendicular to the gap flow direction.

8. The turbine vane according to claim 3, wherein each of the plurality of guides comprises:

an upstream impingement part disposed at an upstream side of a gap flow so that cooling fluid impinges against the upstream impingement part;

a pair of sidewalls extending from upper and lower ends of the upstream impingement part in left and right diagonal directions relative to a gap flow direction of the insert hole and disposed to enclose an upstream side part of the insert hole; and

downstream ends disposed on respective sidewalls at left and right sides of the insert hole with respect to a gap flow direction.

9. The turbine vane according to claim 8, wherein the upstream impingement part has a planar shape.

10. The turbine vane according to claim 8, wherein the upstream impingement part has a convex or concave curved shape toward an upstream side of the gap flow.

11. The turbine vane according to claim 8, wherein a height of the upstream impingement part is 1.5 to 3 times a height of a pair of sidewalls.

12. A turbine vane comprising:

endwalls configured to be coupled to an inner end and an outer end of the turbine vane;

a concave part configured to be formed on a body part of the endwall at a side opposite to the turbine vane and include a plurality of cooling holes;

a thin plate configured to be coupled to the concave part such that a gap is formed between a thin plate and a bottom surface of the concave part; and

a plurality of guides extending from the bottom surface of the concave part and configured to guide a flow of cooling fluid through the gap,

wherein the plurality of guides guide cooling fluid drawn through the cooling holes to prevent the cooling fluid from interfering with a flow of cooling fluid drawn through a subsequent cooling hole,

wherein the plurality of cooling holes are arranged to form a plurality of rows and columns, and

wherein cooling holes of each of the columns are arrange to alternate cooling holes of a subsequent column.

13. The turbine vane according to claim 12, wherein each of the plurality of guides comprises:

an upstream impingement part disposed at an upstream side of the gap flow so that cooling fluid impinges against the upstream impingement part;

a pair of sidewalls extending from upper and lower ends of the upstream impingement part in left and right diagonal directions relative to a gap flow direction of the insert hole and disposed to enclose an upstream side part of the insert hole; and

downstream ends disposed on respective sidewalls at left and right sides of the insert hole with respect to the gap flow direction.

14. The turbine vane according to claim 13, wherein the plurality of guides are arranged such that a distance between a downstream end of a guide on each of the rows and a downstream end of a guide on a subsequent row is ⅓

to 3 times a diameter of the insert hole.

15. The turbine vane according to claim 14, wherein a height of the upstream impingement part is 1.5 to 3 times a height of a pair of sidewalls.

16. A ring segment comprising:

a ring segment body disposed to enclose a turbine blade and mounted to an inner circumferential surface of a turbine casing;

a concave part configured to be formed in the ring segment body at a side opposite to the turbine blade and include a plurality of cooling holes;

a thin plate configured to be coupled to a concave part such that a gap is formed between the thin plate and a bottom surface of the concave part; and

a plurality of guides extending from the bottom surface of the concave part and configured to guide a flow of cooling fluid through the gap,

wherein the plurality of guides guide cooling fluid drawn through the cooling holes to prevent the cooling fluid from interfering with a flow of cooling fluid drawn through a subsequent cooling hole.

17. The ring segment according to claim 16,

wherein the plurality of cooling holes are arranged to form a plurality of rows and columns, and

wherein cooling holes of each of the columns are arranged to alternate with cooling holes of a subsequent column.

18. The ring segment according to claim 17, wherein each of the plurality of guides comprises:

an upstream impingement part disposed at an upstream side of a gap flow so that cooling fluid impinges against the upstream impingement part;

a pair of sidewalls extending from upper and lower ends of the upstream impingement part in left and right diagonal directions relative to a gap flow direction of the insert hole and disposed to enclose an upstream side part of the insert hole; and

downstream ends disposed on respective sidewalls at left and right sides of the insert hole with respect to the gap flow direction.

19. The ring segment according to claim 18, wherein the plurality of guides are arranged such that a distance between a downstream end of a guide on each of the rows and a downstream end of a guide on a subsequent row is ⅓

to 3 times a diameter of the insert hole.

20. The ring segment according to claim 18, wherein a height of the upstream impingement part is 1.5 to 3 times a height of a pair of sidewalls.