Turbine vane with dust tolerant cooling system

Patent metadata

Field	Value
Publication number	US-11713693-B2
Application number	US-202117181113-A
Country	US
Kind code	B2
Filing date	Feb 22, 2021
Priority date	Jul 13, 2018
Publication date	Aug 1, 2023
Grant date	Aug 1, 2023

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 from a first 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, extends from a leading edge to a trailing edge, and includes a rib that extends from the inner diameter to the outer diameter;
a second airfoil spaced apart from the first airfoil;
an inner platform coupled to the airfoil at the inner diameter and coupled to the second airfoil, the inner platform having a first platform surface opposite a second platform surface and a first platform end opposite a second platform end, the first platform end defined proximate the leading edge of the airfoil, the second platform end defined at the trailing edge of the airfoil, and the airfoil and the second airfoil are coupled to the first platform surface; 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, the first conduit extending from the inlet at the outer diameter to an outlet portion defined in the inner platform, the outlet portion defined through the first platform surface of the inner platform to extend within the inner platform below the second conduit and between the first platform surface and the second platform surface toward the second platform end, the outlet portion defines a plurality of film cooling holes through a portion of the first platform surface of the inner platform that spans between the airfoil and the second airfoil, the first conduit includes a plurality of cooling features that extend from a first surface of the first conduit toward an opposite second surface, the first surface of the first conduit opposite the leading edge, the rib separates the first conduit from the second conduit, the second surface of the first conduit is defined on the rib, the second conduit is defined between the inner diameter and the outer diameter from a third surface of the rib to the trailing edge, and the third surface of the rib is opposite the second surface.

2. The turbine vane of claim 1 , wherein the plurality of cooling features comprise a plurality of cooling pins that extend into the first conduit and are spaced apart from the second surface of the first conduit.

3. The turbine vane of claim 1 , 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 of the first conduit, 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.

4. 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, and the inlet and the second inlet are each fluidly coupled to outer platform to receive the cooling fluid.

5. The turbine vane of claim 1 , wherein the plurality of cooling features comprise a plurality of cooling pins that extend from the first surface of the first conduit to the second surface of the first conduit.

6. The turbine vane of claim 1 , wherein the second conduit includes a second outlet portion defined through the trailing edge, and the second outlet portion defines a single outlet.

7. The turbine vane of claim 1 , wherein a fourth surface is defined along the airfoil from the third surface to the trailing edge proximate the inner diameter, and the fourth surface forms a downstream boundary of the second conduit.

8. A turbine vane, comprising:
an airfoil that extends from an inner diameter to an outer diameter, extends from a leading edge to a trailing edge, and includes a rib that extends from the inner diameter to the outer diameter;
a second airfoil spaced apart from the airfoil;
an inner platform coupled to the airfoil at the inner diameter and coupled to the second airfoil, the inner platform having a first platform surface opposite a second platform surface and a first platform end opposite a second platform end, the first platform end defined proximate the leading edge of the airfoil, the second platform end defined at the trailing edge of the airfoil, and the airfoil and the second airfoil are coupled to the first platform surface;
an outer platform coupled to the airfoil at the outer diameter and coupled to the second airfoil, 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 extending from an inlet at the outer diameter that is configured to receive the cooling fluid to an outlet portion defined in the inner platform, the outlet portion is defined through the first platform surface of the inner platform and extends within the inner platform below the second conduit and between the first platform surface and the second platform surface toward the second platform end, the outlet portion includes a plurality of film cooling holes defined through a portion of the first platform surface of the inner platform that spans between the airfoil and the second airfoil, the plurality of film cooling holes spaced a distance apart from the second platform end, the first conduit includes a plurality of cooling pins that at least extend from a first surface of the first conduit toward a second surface of the first conduit, with the first surface of the first conduit opposite the leading edge, the rib separates the first conduit from the second conduit, the second surface of the first conduit is defined on the rib, the second conduit is defined between the inner diameter and the outer diameter from a third surface of the rib to the trailing edge, and the third surface of the rib is opposite the second surface.

9. The turbine vane of claim 8 , wherein the plurality of cooling pins include 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.

10. The turbine vane of claim 8 , wherein the plurality of cooling pins 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.

11. The turbine vane of claim 8 , wherein the plurality of cooling pins extend into the first conduit and are spaced apart from the second surface of the first conduit.

Assignees

• Honeywell Int Inc

Inventors

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

Classifications

• F01D25/12 Primary

  Cooling · CPC title

• F01D9/041

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2240/121

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

• F05D2240/122

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