Turbine vane with dust tolerant cooling system

Patent metadata

Field	Value
Publication number	US-11448093-B2
Application number	US-202117180035-A
Country	US
Kind code	B2
Filing date	Feb 19, 2021
Priority date	Jul 13, 2018
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

First claim

What is claimed is:

1. A turbine vane, comprising:
an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge;
an inner platform coupled to the airfoil at the inner diameter; and
a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge, the first conduit having an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform, the first conduit includes a plurality of cooling pins that extend between a first surface and a second surface of the first conduit, the second surface defined on a rib, the first surface of the first conduit opposite the leading edge, and the second conduit is defined within the airfoil to extend from a third surface of the rib to the trailing edge with a downstream boundary of the second conduit defined by a fourth surface that extends axially from the third surface, the second conduit including a fifth surface that defines an upper boundary of the second conduit, the fifth surface opposite the fourth surface, the third surface opposite the second surface and the fourth surface opposite an outlet of the first conduit,
wherein the outlet portion diverges within the airfoil into at least two flow paths that converge downstream to define the outlet of the first conduit at the trailing edge.

2. The turbine vane of claim 1 , wherein a first pair of the plurality of cooling pins extend substantially along a first longitudinal axis and have a first end coupled to the first surface and a second end coupled to the second surface, and a second pair of the plurality of cooling pins have a third end coupled to the first surface and a fourth end coupled to the second surface such that the fourth end is offset from an axis that extends through the third end of the second pair of the plurality of cooling pins.

3. The turbine vane of claim 1 , wherein each of the plurality of cooling pins includes a first end coupled to the first surface and a second end coupled to the second surface, and the outlet extends axially within the airfoil to the trailing edge.

4. The turbine vane of claim 3 , wherein each of the plurality of cooling pins includes a top surface opposite a bottom surface, the top surface includes a first fillet that extends from the first end toward the second end and the bottom surface includes a second fillet that extends from the first end toward the second end.

5. The turbine vane of claim 4 , wherein the first fillet has a first fillet arc that is different than a second fillet arc of the second fillet.

6. The turbine vane of claim 1 , further comprising at least one rib that extends from the first surface to the second surface to divide the first conduit into a plurality of flow passages.

7. The turbine vane of claim 1 , further comprising an outer platform coupled to the airfoil at the outer diameter, the outer platform in fluid communication with a source of the cooling fluid, the second conduit including a second inlet at the outer diameter, the second inlet defined proximate the fifth surface, the fifth surface extends from the second inlet to the trailing edge and the inlet and the second inlet are each fluidly coupled to outer platform to receive the cooling fluid.

8. The turbine vane of claim 1 , wherein the rib extends from the outer diameter to the inner diameter.

9. The turbine vane of claim 1 , wherein one of the at least two flow paths is defined at least partially within the inner platform.

10. A turbine vane, comprising:
an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge;
an inner platform coupled to the airfoil at the inner diameter;
an outer platform coupled to the airfoil at the outer diameter, the outer platform in fluid communication with a source of cooling fluid; and
a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge, the first conduit having an inlet at the outer diameter to receive the cooling fluid and an outlet portion that diverges within the airfoil into at least two flow paths that converge downstream within the airfoil to define an outlet for the first conduit at the trailing edge, the outlet extends axially within the airfoil to the trailing edge, with one of the at least two flow paths defined at least partially within the inner platform, the first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, with the first surface of the first conduit opposite the leading edge and the second surface defined on a rib, and the second conduit is defined within the airfoil to extend from a third surface of the rib to the trailing edge with a downstream boundary of the second conduit defined by a fourth surface that extends axially from the third surface, the third surface opposite the second surface and the fourth surface opposite the outlet of the first conduit, the second conduit including a fifth surface that defines an upper boundary of the second conduit, the fifth surface opposite the fourth surface.

11. The turbine vane of claim 10 , wherein the plurality of cooling features comprise a plurality of cooling pins, with a first pair of the plurality of cooling pins extending substantially along a first longitudinal axis and having a first end coupled to the first surface and a second end coupled to the second surface, and a second pair of the plurality of cooling pins having a third end coupled to the first surface and a fourth end coupled to the second surface such that the fourth end is offset from an axis that extends through the third end of the second pair of the plurality of cooling pins.

12. The turbine vane of claim 10 , wherein the plurality of cooling features comprise a plurality of cooling pins, which extend from the first surface to the second surface and from the outer diameter to the inner diameter to divide the first conduit into a plurality of flow passages.

13. The turbine vane of claim 10 , wherein the plurality of cooling features comprise a plurality of cooling pins, and each of the plurality of cooling pins includes a first end coupled to the first surface and a second end coupled to the second surface.

14. The turbine vane of claim 13 , wherein each of the plurality of cooling pins includes a top surface opposite a bottom surface, the top surface includes a first fillet that extends from the first end toward the second end and the bottom surface includes a second fillet that extends from the first end toward the second end.

15. The turbine vane of claim 14 , wherein the first fillet has a first fillet arc that is different than a second fillet arc of the second fillet.

16. The turbine vane of claim 10 , wherein the second conduit includes a second inlet at the outer diameter proximate the fifth surface, the fifth surface extends from the second inlet to the trailing edge, and the inlet and the second inlet are each fluidly coupled to outer platform to receive the cooling fluid.

17. The turbine vane of claim 10 , wherein the rib extends from the outer diameter to the inner diameter.

Assignees

• Honeywell Int Inc

Inventors

• Whitaker Steven
• Crites Daniel C
• Morris Mark C
• Riahi Ardeshir

Classifications

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title