Gas turbine engine component with compound cusp cooling configuration

Patent metadata

Field	Value
Publication number	US-9869186-B2
Application number	US-201615243220-A
Country	US
Kind code	B2
Filing date	Aug 22, 2016
Priority date	Feb 15, 2012
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition.

First claim

The invention claimed is:

1. A component for a gas turbine engine, the component comprising:
a gas path wall having a first surface and a second surface;
a cooling hole extending through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface, wherein a first cross sectional area of the cooling hole does not increase from the inlet to the transition, and wherein a second cross sectional area of the cooling hole increases from the transition to the outlet; and
cusps formed on the transition, wherein only one cusp extends from the transition along a ridge, the ridge extending from the transition toward a trailing edge of the outlet.

2. The component of claim 1 , wherein the cusps extend from the inlet along the cooling hole toward the outlet.

3. The component of claim 2 , wherein the cusps terminate between the inlet and the outlet.

4. The component of claim 1 , wherein the ridge divides the cooling hole into two lobes.

5. The component of claim 4 , further comprising:
a transition region extending along a trailing edge of the outlet.

6. The component of claim 1 , wherein the cooling hole has a bicuspid cross section taken perpendicular to an axis of the cooling hole at a location between the inlet and the outlet, the bicuspid cross section having a ratio of semi-major to semi-minor axes, the ratio being 3 or less.

7. The component of claim 1 , wherein the cooling hole has a bicuspid cross section taken perpendicular to an axis of the cooling hole at a location between the inlet and the outlet, the bicuspid cross section having a concave upstream surface, the concave upstream surface extending toward an axis of the cooling hole between opposing side surfaces.

8. The component of claim 1 , wherein the cooling hole has a cross section taken perpendicular to an axis of the cooling hole at a location between the inlet and the outlet, the cross section having a single cusp.

9. A gas turbine engine comprising the component of claim 1 .

10. A cooling system for a gas turbine engine component, the cooling system comprising:
a flow path wall having a first surface exposed to cooling fluid and a second surface exposed to working fluid flow;
a cooling hole extending through the flow path wall from an inlet in the first surface through a transition to an outlet in the second surface;
a metering section extending from the inlet to the transition;
at least two longitudinal cusps extending along the metering section from the inlet toward the transition, wherein the longitudinal cusps divide the metering section into lobes; and
a diffusing section extending from the transition to the outlet, wherein only longitudinal cusp extends from the transition along a longitudinal ridge, the longitudinal ridge dividing the diffusing section into lobes.

11. The cooling system of claim 10 , further comprising:
a transition region extending from the longitudinal ridge to a trailing edge of the outlet, the transition region extending along substantially all of a transverse width of the trailing edge.

12. The cooling system of claim 10 , wherein the transition has a cross section with a single cusp.

13. The cooling system of claim 10 , wherein the inlet has an uncusped cross section with a continuously convex perimeter.

14. A component for a gas turbine engine, the component comprising:
a gas path wall having a first surface and a second surface;
a cooling hole extending through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface; and
cusps formed on the transition, wherein the cooling hole has a cross section taken perpendicular to an axis of the cooling hole at a location between the inlet and the transition, the cross section having a single cusp.

Assignees

• United Technologies Corp

Inventors

• Xu Jinquan

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F04D29/582

  specially adapted for elastic fluid pumps · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title