Turbomachine cooling trench

Patent metadata

Field	Value
Publication number	US-11879356-B2
Application number	US-202217852875-A
Country	US
Kind code	B2
Filing date	Jun 29, 2022
Priority date	Aug 6, 2018
Publication date	Jan 23, 2024
Grant date	Jan 23, 2024

Abstract

A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section in axial flow arrangement;
a combustion flowpath extending through the combustion section and the turbine section for a flow of combustion gas therethrough; and
a component, comprising:
a body with an exterior surface abutting the combustion flowpath;
a trench on the exterior surface comprising a curved portion defining a projecting tip with the exterior surface, the projecting tip extending at least partially downstream from the curved portion in the direction of the combustion flowpath;
a cooling passage defined within the body and supplying cooling air to the component; and
at least one outlet on the trench fluidly coupled to the cooling passage.

2. The gas turbine engine of claim 1 , wherein the trench comprises a first curved sidewall having a first radius of curvature, and a second curved sidewall having a second radius of curvature smaller than the first radius of curvature.

3. The gas turbine engine of claim 1 , wherein the trench comprises a first curved sidewall having a convex curvature with respect to the outlet, and a second curved sidewall having a concave curvature with respect to the outlet.

4. The gas turbine engine of claim 1 , wherein the projecting tip at least partially overlies the outlet for impingement by the cooling air from the outlet.

5. The gas turbine engine of claim 1 , wherein the projecting tip defines a knife edge between the curved portion and the exterior surface.

6. A component for a turbine engine, comprising:
a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine;
a trench on the exterior surface comprising a curved portion defining a projecting tip with the exterior surface, the projecting tip extending at least partially downstream from the curved portion in the direction of the combustion flowpath;
a cooling passage defined within the body and supplying cooling air to the component; and
at least one outlet on the trench fluidly coupled to the cooling passage.

7. The component of claim 6 , wherein the trench comprises a first curved sidewall having a first portion tangent to the outlet and a second portion tangent to the exterior surface for directing the cooling air from the trench onto the exterior surface.

8. The component of claim 7 , wherein the trench comprises a first curved sidewall having a first radius of curvature, and a second curved sidewall having a second radius of curvature smaller than the first radius of curvature.

9. The component of claim 8 , wherein the first portion comprises the first radius of curvature, and the second portion comprises a third radius of curvature larger than the first radius of curvature.

10. The component of claim 8 , wherein at least one of the first radius of curvature or the second radius of curvature is defined by a continuous curvature.

11. The component of claim 6 , wherein the trench comprises a first curved sidewall having a convex curvature with respect to the outlet, and a second curved sidewall having a concave curvature with respect to the outlet.

12. The component of claim 6 , wherein the body is an airfoil, and the exterior surface is an airfoil surface comprising a pressure side and suction side extending between a leading edge and a trailing edge.

13. The component of claim 6 , wherein the component is a turbine rotor blade, wherein the body comprises a first band and an airfoil extending radially from the first band, wherein the exterior surface comprises a first band surface and an airfoil surface, and wherein the trench is positioned on at least one of the first band surface or the airfoil surface.

14. The component of claim 6 , wherein the component is a turbine nozzle, wherein the body comprises a first band, a second band positioned radially outward from the first band, and an airfoil extending therebetween, wherein the exterior surface comprises a first band surface, an airfoil surface, and a second band surface, and wherein the trench is positioned on at least one of the first band surface, the airfoil surface, or the second band surface.

15. The component of claim 6 , wherein the projecting tip at least partially overlies the outlet for impingement by the cooling air from the outlet.

16. The component of claim 6 , wherein the projecting tip defines a knife edge between the curved portion and the exterior surface.

17. A component for a turbine engine, comprising:
a body with an exterior surface having a leading edge and a trailing edge and abutting a combustion flowpath for a combustion gas flow through the turbine engine;
a trench on the exterior surface having a curved wall and defining a trench outlet, the curved wall defining a projecting tip with the exterior surface and extending at least partially extends over the trench with a proximal end of the projecting tip closer to the leading edge of the component and a distal tip end of the projecting tip closer to the trailing edge of the component;
a cooling passage defined within the body and supplying cooling air to the component; and
at least one outlet on the trench fluidly coupled to the cooling passage and defining a cooling axis, with the cooling axis extending at least partially downstream with respect to the combustion flowpath;
wherein the curved wall comprises a first portion tangent to the at least one outlet and a second portion tangent to the exterior surface at the trench outlet for directing the cooling air from the trench downstream onto the exterior surface.

18. The component of claim 17 , wherein the first portion comprises a first radius of curvature, and the second portion comprises a second radius of curvature larger than the first radius of curvature.

Assignees

• Gen Electric

Inventors

• Osgood Daniel Endecott
• Webster Zachary Daniel
• Garay Gregory Terrence
• Feldmann Kevin Robert

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2300/514

  Porosity · CPC title

• F05D2230/311

  by torch or flame spraying · CPC title

• F01D11/14

  Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing (rotors with blades adjustable in operation F01D7/00) · CPC title

• F01D11/12

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title