Gas turbine engine component with film cooling hole with accumulator

Patent metadata

Field	Value
Publication number	US-9957814-B2
Application number	US-201514827453-A
Country	US
Kind code	B2
Filing date	Aug 17, 2015
Priority date	Sep 4, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.

First claim

What is claimed is:

1. A gas turbine engine component comprising:
a wall providing an exterior surface and an interior flow path surface extending in a longitudinal direction;
a film cooling hole extending through the wall and configured to fluidly connect the interior flow path surface to the exterior surface, the film cooling hole having a pocket facing the interior flow path and extending substantially in the longitudinal direction, the film cooling hole having a portion downstream from the pocket and arranged at an angle relative to the longitudinal direction and extending to the exterior surface, the portion having an inlet at the pocket and extending to the exterior surface, wherein the pocket provides an opening in the interior flow path surface that is larger than the inlet, the pocket extends substantially in the longitudinal direction, extending in the longitudinal direction a greater amount than in a direction normal to the longitudinal direction, and the portion extends lateral at an angle in a range of 70°-179° relative to the longitudinal direction.

2. The gas turbine engine component according to claim 1 , wherein the gas turbine engine component is a turbine airfoil, and the exterior surface is an exterior airfoil surface.

3. The gas turbine engine component according to claim 1 , wherein the portion includes a metering hole providing an inlet at the pocket, and the portion has a diffuser providing the exit arranged downstream from the metering hole at the exterior surface.

4. The gas turbine engine component according to claim 3 , wherein the portion extends along a centerline, and the diffuser has a second diffuser surface at an obtuse angle relative to adjacent exterior surface, the centerline and the second diffuser surface at a second angle relative to one another in a range of 0°-15°.

5. The gas turbine engine component according to claim 1 , wherein the interior flow path surface faces a cooling passage that extends in the longitudinal direction.

6. The gas turbine engine component according to claim 1 , wherein the portion is configured to extend is a direction corresponding to a core gas flow over the exterior surface.

7. A gas turbine engine component comprising:
a wall providing an exterior surface and an interior flow path surface;
a film cooling hole extending through the wall and configured to fluidly connect the interior flow path surface to the exterior surface, the film cooling hole having a pocket facing the interior flow path and extending substantially in a longitudinal direction, the film cooling hole having a portion downstream from the pocket and arranged at an angle relative to the longitudinal direction and extending to the exterior surface, wherein the portion includes a metering hole providing an inlet at the pocket, and the portion has a diffuser providing the exit arranged downstream from the metering hole at the exterior surface, wherein the pocket has a pocket surface, and the diffuser has a first diffuser surface, the pocket surface and first diffuser surface on a same side of the wall, the pocket surface and the first diffuser surface at a first angle relative to one another in a range of 165°-180°.

8. A gas turbine engine comprising:
a compressor section;
a turbine section; and
a component arranged in one of the compressor and turbine sections, the component including:
a wall providing an exterior surface and an interior flow path surface extending in a longitudinal direction;
a film cooling hole extending through the wall and configured to fluidly connect the interior flow path surface to the exterior surface, the film cooling hole having a pocket facing the interior flow path and extending in the longitudinal direction, the film cooling hole having a portion downstream from the pocket and arranged at an angle relative to the longitudinal direction and extending to the exterior surface, the portion having an inlet at the pocket and extending to the exterior surface, wherein the pocket provides an opening in the interior flow path surface that is larger than the inlet, the pocket extends substantially in the longitudinal direction, extending in the longitudinal direction a greater amount than in a direction normal to the longitudinal direction, and the portion extends lateral at an angle in a range of 70°-179° relative to the longitudinal direction.

9. The gas turbine engine according to claim 8 , wherein the component is arranged in the turbine section.

10. The gas turbine engine according to claim 9 , wherein the exterior surface is an exterior airfoil surface.

11. The gas turbine engine according to claim 8 , wherein the portion includes a metering hole providing an inlet at the pocket, and the portion has a diffuser providing the exit arranged downstream from the metering hole at the exterior surface.

12. The gas turbine engine according to claim 11 , wherein the portion extends along a centerline, and the diffuser has a second diffuser surface at an obtuse angle relative to adjacent exterior surface, the centerline and the second diffuser surface at a second angle relative to one another in a range of 0°-15°.

13. The gas turbine engine according to claim 8 , wherein the interior flow path surface faces a cooling passage that extends in the longitudinal direction.

14. The gas turbine engine according to claim 8 , wherein the portion is configured to extend is a direction corresponding to a core gas flow over the exterior surface.

15. A gas turbine engine comprising:
a compressor section;
a turbine section; and
a component arranged in one of the compressor and turbine sections, the component including:
a wall providing an exterior surface and an interior flow path surface;
a film cooling hole extending through the wall and configured to fluidly connect the interior flow path surface to the exterior surface, the film cooling hole having a pocket facing the interior flow path and extending in a longitudinal direction, the film cooling hole having a portion downstream from the pocket and arranged at an angle relative to the longitudinal direction and extending to the exterior surface, wherein the portion includes a metering hole providing an inlet at the pocket, and the portion has a diffuser providing the exit arranged downstream from the metering hole at the exterior surface, wherein the pocket has a pocket surface, and the diffuser has a first diffuser surface, the pocket surface and first diffuser surface on a same side of the wall, the pocket surface and the first diffuser surface at a first angle relative to one another in a range of 165°-180°.

Assignees

• United Technologies Corp

Inventors

• Musto Clifford J
• Moore Sasha M
• Slavens Thomas N
• Quach San
• Loricco Nicholas M
• Jennings Timothy J
• Mcbrien John

Classifications

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F01D5/186 Primary

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

• F05D2220/32

  in gas turbines · CPC title

• F04D29/582

  specially adapted for elastic fluid pumps · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic