Engine component for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016201507-A1
Application number	US-201514881188-A
Country	US
Kind code	A1
Filing date	Oct 13, 2015
Priority date	Oct 31, 2014
Publication date	Jul 14, 2016
Grant date	—

Abstract

An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. A film hole in the wall has an inlet, an outlet, and a passage connecting the inlet and outlet that defines an inflection point.

First claim

What is claimed is:

1 . An engine component for a gas turbine engine, the gas turbine engine generating hot combustion gas, comprising:
a wall separating the hot combustion gas from a cooling fluid flow and having a hot surface facing the hot combustion gas and a cooling surface facing the cooling fluid flow; and a film hole having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet; wherein the passage is formed by a wall having at least one localized curvilinear portion transitioning between concave and convex to define an inflection point.

2 . The engine component of claim 1 wherein the cross-sectional area immediately downstream of the inflection point is greater than, and the cross-sectional area immediately upstream of the inflection point is less than, the cross-sectional area at the inflection point.

3 . The engine component of claim 1 wherein the cross-sectional area immediately upstream of the inflection point is greater than, and the cross-sectional area immediately downstream of the inflection point is less than, the cross-sectional area at the inflection point.

4 . The engine component of claim 1 wherein the cross-sectional area of the passage from the inlet to the inflection point is constant.

5 . The engine component of claim 1 wherein the cross-sectional area of the passage from the inflection point to the outlet is constant.

6 . The engine component of claim 5 wherein the cross-sectional area of the passage from the inlet to the inflection point is constant.

7 . The engine component of claim 1 wherein the inflection point lies along an inflection transition line that extends at least partially about the circumference of the passage, wherein the inflection transition line is an imaginary line at which the localized curvilinear portion of the passage transitions between a concave surface and a convex surface.

8 . The engine component of claim 7 wherein the inflection transition line extends completely about the circumference of the passage.

9 . The engine component of claim 1 wherein the passage defines a centerline formed by a line passing through the center of the cross-sectional area for each point along the passage, wherein the centerline is linear.

10 . The engine component of claim 9 wherein the passage defines a centerline formed by a line passing through the center of the cross-sectional area for each point along the passage, wherein the centerline is curvilinear.

11 . The engine component of claim 1 wherein the inlet comprises a flared portion flaring inwardly from the cooling surface.

12 . The engine component of claim 11 wherein the flared portion has a smaller cross-sectional area inwardly from the cooling surface than the cross-sectional area at the cooling surface.

13 . The engine component of claim 1 wherein the outlet comprises a flared portion flaring inwardly from the hot surface.

14 . The engine component of claim 13 wherein the flared portion has a smaller cross-sectional area inwardly from the hot surface than the cross-sectional area at the hot surface.

15 . The engine component of claim 13 wherein the flared portion defines a diffusing section of the film hole.

16 . The engine component of claim 1 wherein at least one of the inlet, the outlet or the passage define a metering section.

17 . The engine component of claim 16 wherein the passage defines the metering section.

18 . The engine component of claim 17 wherein the metering section is adjacent the at least one localized curvilinear portion.

Assignees

• Gen Electric

Inventors

• Bunker Ronald Scott

Classifications

• F01D25/12 Primary

  Cooling · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D5/186 Primary

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

• F05D2250/184

  sinusoidal · CPC title