Engine component

Patent metadata

Field	Value
Publication number	US-2016251966-A1
Application number	US-201514633167-A
Country	US
Kind code	A1
Filing date	Feb 27, 2015
Priority date	Feb 27, 2015
Publication date	Sep 1, 2016
Grant date	—

Abstract

An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.

First claim

What is claimed is:

1 . An engine component for a gas turbine engine, the gas turbine engine generating hot combustion gas flow, comprising:
a substrate having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow, the hot combustion gas flow generally defining an upstream direction and a downstream direction relative to the hot surface; a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet; and a flow conditioning structure provided upstream of the outlet on the hot surface, wherein the flow conditioning structure is configured to divert at least a portion of the hot combustion gas flow around the cooling fluid flow emerging from the outlet.

2 . The engine component of claim 1 , wherein the flow conditioning structure comprises a planform that tapers in the upstream direction away from the outlet.

3 . The engine component of claim 2 , wherein the flow conditioning structure comprises a cross-section that increases toward the outlet.

4 . The engine component of claim 1 , wherein the flow conditioning structure comprises a recess in the hot surface.

5 . The engine component of claim 4 , wherein the recess is immediately adjacent to the outlet.

6 . The engine component of claim 4 , wherein the recess is tapered in the upstream direction away from the outlet.

7 . The engine component of claim 1 , wherein the flow conditioning structure comprises a projection from the hot surface.

8 . The engine component of claim 7 , wherein the projection is immediately adjacent to the outlet.

9 . The engine component of claim 7 , wherein the projection is tapered in the upstream direction away from the outlet.

10 . The engine component of claim 1 , wherein the passage comprises a metering section defining the inlet and a diffusing section defining the outlet.

11 . The engine component of claim 10 , wherein a portion of the perimeter of the outlet defined by the diffusing section is contiguous with a portion of the flow conditioning structure.

12 . The engine component of claim 1 , wherein the passage defines a centerline that is inclined in the downstream direction such that the centerline is non-orthogonal to the cooling surface and the hot surface.

13 . The engine component of claim 1 , wherein the engine component comprises one of a blade, a vane, a shroud, or a combustor liner.

14 . The engine component of claim 1 wherein the substrate comprises an exterior wall of the engine component which defines an interior to which the cooling fluid flow is supplied.

15 . An engine component for a gas turbine engine, the gas turbine engine generating hot combustion gas flow, comprising:
a substrate having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow, the hot combustion gas flow generally defining an upstream direction and a downstream direction relative to the hot surface; a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet; and a flow conditioning structure comprising a recess in the hot surface provided upstream of the outlet on the hot surface, wherein the recess is configured to divert at least a portion of the hot combustion gas flow around the cooling fluid flow emerging from the outlet.

16 . The engine component of claim 15 , wherein the recess is tapered in the upstream direction away from the outlet.

17 . The engine component of claim 16 , wherein the recess is immediately adjacent to the outlet.

18 . An engine component for a gas turbine engine, the gas turbine engine generating hot combustion gas flow, comprising:
a substrate having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow, the hot combustion gas flow generally defining an upstream direction and a downstream direction relative to the hot surface; a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet; and a flow conditioning structure comprising a projection from the hot surface provided upstream of the outlet on the hot surface, wherein the projection is configured to divert at least a portion of the hot combustion gas flow around the cooling fluid flow emerging from the outlet.

19 . The engine component of claim 18 , wherein the projection is tapered in the upstream direction away from the outlet.

20 . The engine component of claim 19 , wherein the projection is immediately adjacent to the outlet.

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott
• Briggs Robert David

Classifications

• F01D5/186 Primary

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

• F05D2260/202

  by film cooling · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title