Gas turbine engines with plug resistant effusion cooling holes

Patent metadata

Field	Value
Publication number	US-10101030-B2
Application number	US-201414475106-A
Country	US
Kind code	B2
Filing date	Sep 2, 2014
Priority date	Sep 2, 2014
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.

First claim

What is claimed is:

1. A gas turbine engine comprising a component, the component comprising:
a body having a first surface and a second surface, the first surface being exposed to cooling air and the second surface being exposed to combustion gases in the gas turbine engine; and
a plurality of angled cooling holes formed in the body and direct the cooling air from the first surface to the second surface to form a film of cooling air on the second surface of the body, the plurality of angled cooling holes including a first angled cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, the metering portion having a substantially constant diameter, and an outlet portion fluidly coupled to the metering portion and extending to the second surface, the inlet portion being larger than the metering portion,
wherein the inlet portion has a first section that forms a curved edge from the first surface to a location along the inlet portion within the first angled cooling hole, the first section of the inlet portion being arranged on an acute side of the inlet portion relative to the first surface,
wherein the inlet portion has at least one second section disposed between the first surface and the second surface, the at least one second section forming a first non-zero angle with respect to the first surface and forming a second non-zero angle with respect to the metering portion, and
wherein, during operation of the gas turbine engine, cooling air flows from the inlet portion to the outlet portion.

2. The component of claim 1 , wherein the inlet portion includes a protrusion extending from a plane defined by the first surface.

3. The component of claim 1 , wherein the inlet portion includes a protrusion extending from a plane defined by the first surface, and wherein the protrusion forms a continuously curved edge between the first surface and the metering portion.

4. A combustor for a turbine engine, comprising:
a first liner having a first surface and a second surface; and
a second liner forming a combustion chamber with the second surface of the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein;
the first liner defining a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner, the plurality of effusion cooling holes including a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, the metering portion having a substantially constant diameter, and an outlet portion fluidly coupled to the metering portion and extending to the second surface, the inlet portion being larger than the metering portion,
wherein the inlet portion has a first section that forms a curved edge from the first surface to a location along the inlet portion within the first effusion cooling hole,
wherein the first section of the inlet portion is on an acute side of the inlet portion relative to the first surface,
wherein the inlet portion has at least one second section disposed between the first surface and the second surface, the at least one second section forming a first non-zero angle with respect to the first surface and forming a second non-zero angle with respect to the metering portion, and
wherein, during operation of the combustor, cooling air flows from the inlet portion to the outlet portion.

5. The combustor of claim 4 , wherein the second section of the inlet portion is on an obtuse side of the inlet portion relative to the first surface.

6. The combustor of claim 4 , wherein the inlet portion defines a first cross-sectional area and the metering portion defines a second cross-sectional area such that the first cross-sectional area is larger than the second cross-sectional area.

7. The combustor of claim 4 , wherein the inlet portion diverges in cross-sectional area from the metering portion to the first surface.

8. The combustor of claim 4 , wherein the inlet portion includes a protrusion extending from a plane defined by the first surface.

9. The combustor of claim 8 , wherein the protrusion forms a continuously curved edge between the first surface and the metering portion.

10. The combustor of claim 4 , wherein the outlet portion is larger than the metering portion.

11. The combustor of claim 10 , wherein the outlet portion diverges in cross-sectional area from the metering section to the second surface.

12. The combustor of claim 4 , wherein the metering portion is substantially cylindrical.

13. The combustor of claim 4 , wherein the curved edge is convex from the first surface into the metering portion of the first effusion cooling hole.

14. A gas turbine engine, comprising:
a compressor section configured to compress air;
a combustor section fluidly coupled to the compressor section and including a combustor liner forming a combustion chamber in which the compressed air is mixed with fuel and combusted to generate combustion gases,
wherein the combustor liner has an inner surface and an outer surface, the combustor liner defining a plurality of effusion cooling holes, each extending between the outer surface and the inner surface, the plurality of effusion cooling holes including a first effusion cooling hole with an inlet portion extending from the outer surface, a metering portion fluidly coupled to the inlet portion, the metering portion having a substantially constant diameter, and an outlet portion fluidly coupled to the metering portion and extending to the inner surface, the inlet portion being larger than the metering portion; and
a turbine section fluidly coupled to the combustor section to receive the combustion gases and extract energy from the combustion gases,
wherein the inlet portion has a first section that forms a curved edge connected with the outer surface,
wherein the first section of the inlet portion is on an acute side of the inlet portion relative to the outer surface,
wherein the inlet portion has at least one second section disposed between the outer surface and the inner surface, the at least one second section forming a first non-zero angle with respect to the outer surface and forming a second non-zero angle with respect to the metering portion, and
wherein, during operation of the gas turbine engine, cooling air flows from the inlet portion to the outlet portion.

15. The gas turbine engine of claim 14 , wherein the second section of the inlet portion is on an obtuse side of the inlet portion relative to the outer surface.

16. The gas turbine engine of claim 14 , wherein the inlet portion diverges in cross-sectional area from the metering portion to the outer surface.

17. The gas turbine engine of claim 14 , wherein the inlet portion includes a protrusion extending from a plane defined by the outer surface.

18. The gas turbine engine of claim 14 , wherein the inlet portion includes a protrusion extending from a plane defined by the outer surface, and wherein the protrusion forms a continuously curved edge between the outer surface and the metering portion.

Assignees

• Honeywell Int Inc

Inventors

• Dudebout Rodolphe
• Blumer Eric

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · 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

• F05D2260/202

  by film cooling · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/04

  Air inlet arrangements · CPC title