Engine components with cooling holes having tailored metering and diffuser portions

Patent metadata

Field	Value
Publication number	US-11286791-B2
Application number	US-202017030017-A
Country	US
Kind code	B2
Filing date	Sep 23, 2020
Priority date	May 19, 2016
Publication date	Mar 29, 2022
Grant date	Mar 29, 2022

Abstract

An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion and a diffuser portion extending from the metering portion to the external surface of the body.

First claim

What is claimed is:

1. An engine component, comprising:
a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit; and
a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body, the plurality of cooling holes including a first cooling hole configured to receive a cooling fluid flow, the first cooling hole comprising:
a metering portion extending from an inlet on the internal surface to a diffuser portion, the inlet configured to receive the cooling fluid flow and the metering portion to define a center flow zone, the metering portion extending along a longitudinal centerline; and
the diffuser portion extending from the metering portion to the external surface of the body and defining an outlet at the external surface, the diffuser portion to receive the cooling fluid flow from the metering portion, the diffuser portion having a diffuser portion top surface, a diffuser portion bottom surface, and diffuser portion sides that join the diffuser portion top surface to the diffuser portion bottom surface, the diffuser portion extends along an axis oblique to the longitudinal centerline, and the diffuser portion top surface is inclined at a forward angle relative to the metering portion such that a diffuser central concave section of the diffuser portion top surface extends into the center flow zone to direct the cooling fluid flow from the center flow zone toward the diffuser portion sides, with a diffuser central convex section connected to a diffuser third convex section and a diffuser fourth convex section by a respective concave section, a diffuser first convex section connected to the diffuser third convex section by one of the diffuser portion sides and a diffuser second convex section connected to the diffuser fourth convex section by another of the diffuser portion sides, the diffuser portion includes a second maximum height defined between the diffuser first convex section and the diffuser third convex section, a central height defined between the diffuser central concave section and the diffuser central convex section, the central height less than the second maximum height, and the second maximum height is offset from the axis.

2. The engine component of claim 1 , wherein the diffuser portion top surface includes the diffuser central concave section downstream from the diffuser first convex section and the diffuser second convex section at the outlet.

3. The engine component of claim 1 , wherein the diffuser portion bottom surface includes the diffuser third convex section and the diffuser fourth convex section downstream from the diffuser central convex section at the outlet.

4. The engine component of claim 1 , wherein the metering portion is inclined relative to the external surface of the body at an angle of 20°-45° to define the cross-sectional shape.

5. The engine component of claim 1 , wherein the metering portion has a metering portion top surface, a metering portion bottom surface, and metering portion sides that join the metering portion top surface to the metering portion bottom surface, and the metering portion top surface includes a central concave section relative to the first cooling hole that cooperates with the metering portion bottom surface to define the center flow zone through the metering portion.

6. The engine component of claim 5 , wherein the metering portion bottom surface includes a concave section relative to the first cooling hole or a flat section.

7. The engine component of claim 1 , wherein the cross-sectional shape of the metering portion has a center height on the longitudinal centerline, a first offset diameter that corresponds to the maximum height, and a second offset diameter that corresponds to the maximum height.

8. The engine component of claim 7 , wherein a ratio of the center height to the maximum height is less than 0.9 to 1.

9. The engine component of claim 1 , wherein the metering portion intersects with the diffuser portion within the middle half of the first cooling hole.

10. The engine component of claim 1 , wherein the diffuser portion is inclined relative to the external surface of the body at an angle of 20°-45° to define a cross-sectional shape,
wherein the diffuser portion sides are splayed relative to one another from the diffuser portion top surface to the diffuser portion bottom surface.

11. The engine component of claim 10 , wherein the diffuser portion sides are splayed relative to one another from the diffuser portion top surface to the diffuser portion bottom surface at an angle of 20°-24°.

12. A turbine section of a gas turbine engine, comprising:
a housing defining a hot gas flow path;
a plurality of circumferential rows of airfoils disposed in the hot gas flow path, each airfoil defining an inner surface and an outer surface; and
a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils and configured to receive a cooling fluid flow, wherein a first cooling hole of the plurality of cooling holes is defined by:
a metering portion extending from an inlet on the internal surface to a diffuser portion, the inlet configured to receive the cooling fluid flow and the metering portion to define a center flow zone, the metering portion extending along a longitudinal centerline; and
the diffuser portion extending from the metering portion to the outer surface of the airfoil and defining an outlet at the outer surface, the diffuser portion to receive the cooling fluid flow from the metering portion, the diffuser portion having a diffuser portion top surface, a diffuser portion bottom surface, and diffuser portion sides that join the diffuser portion top surface to the diffuser portion bottom surface, the diffuser portion top surface including a diffuser central concave section downstream from a diffuser first convex section and a diffuser second convex section at the outlet, the diffuser portion bottom surface including a diffuser third convex section and a diffuser fourth convex section downstream from a diffuser central convex section at the outlet, the diffuser first convex section connected to the diffuser third convex section by one of the diffuser portion sides and the diffuser second convex section connected to the diffuser fourth convex section by another of the diffuser portion sides, the diffuser portion including a second maximum height defined between the diffuser first convex section and the diffuser third convex section, a central height defined between the diffuser central concave section and the diffuser central convex section, the central height less than the second maximum height, the diffuser portion extends along an axis oblique to the longitudinal centerline and the second maximum height is offset from the axis, and the diffuser portion top surface is inclined at a forward angle relative to the metering portion such that the diffuser central concave section of the diffuser portion top surface extends into the center flow zone to direct the cooling fluid flow from the center flow zone toward the diffuser portion sides.

13. The turbine section of claim 12 , wherein the diffuser central convex section is connected to the diffuser third convex section and the diffuser fourth convex section by a respective concave section.

14. The turbine section of claim 12 , wherein the metering portion has a constant cross-sectional area and a cross-sectional shape having a maximum height that is offset relative to the longitudinal centerline.

15. The turbine s

Assignees

• Honeywell Int Inc

Inventors

• Crites Daniel C
• Morris Mark C
• Waldman David R
• Riahi Ardeshir

Classifications

• F05D2240/81

  Cooled platforms · CPC title

• F01D5/186 Primary

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

• F05D2260/202

  by film cooling · CPC title

• F05D2250/712

  concave · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title