Engine component with cooling hole

Patent metadata

Field	Value
Publication number	US-10975704-B2
Application number	US-201815898703-A
Country	US
Kind code	B2
Filing date	Feb 19, 2018
Priority date	Feb 19, 2018
Publication date	Apr 13, 2021
Grant date	Apr 13, 2021

Abstract

An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

First claim

What is claimed is:

1. An airfoil for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising:
a wall separating the hot gas flow from the cooling fluid flow and having a heated surface along which the hot gas flows and a cooled surface facing the cooling fluid flow; and
at least one cooling hole comprising at least one inlet at the cooled surface and at least one outlet at the heated surface, at least one connecting passage extending between the at least one inlet and the at least one outlet, with a disc-shaped impingement cavity formed in the at least one connecting passage, the at least one connecting passage including a first portion upstream of the disc-shaped impingement cavity and a second portion downstream of the disc-shaped impingement cavity, the disc-shaped impingement cavity defining a turn between the first portion and the second portion;
wherein the disc-shaped impingement cavity comprises one a biconcave disc shape with a depressed portion formed to decrease a cross-sectional area of the disc-shaped impingement cavity.

2. The airfoil of claim 1 , wherein the second portion is the at least one outlet.

3. The airfoil of claim 1 , wherein at least one of the first or second portions define multiple branches of the connecting passage.

4. The airfoil of claim 1 , wherein the turn further defines a stagnation zone.

5. The airfoil of claim 1 , wherein the first portion has a first cross-sectional area defining a first centerline and the second portion has a second cross-sectional area defining a second centerline and the turn is an angle greater than 70 degrees formed between the first and second centerline.

6. The airfoil of claim 5 wherein at least one of the first or second centerlines is a curvilinear centerline.

7. The airfoil of claim 1 wherein the first portion of the at least one connecting passage intersects the disc-shape impingement cavity beyond a diameter of the depressed portion.

8. The airfoil of claim 1 , wherein the first portion has a first cross-sectional area defining a first centerline and the second portion has a second cross-sectional area defining a second centerline.

9. The airfoil of claim 8 , wherein at least one of the first or second centerlines is a curvilinear centerline.

10. The airfoil of claim 8 , wherein the at least one connecting passage further comprises at least one diffusing section.

11. The airfoil of claim 8 , wherein the second portion comprises a secondary diffusing section located downstream of the impingement cavity.

12. The airfoil of claim 11 wherein the secondary diffusing section is divided by a tear drop shaped wall.

13. The airfoil of claim 11 wherein the secondary diffusing section defines the at least one outlet.

14. The airfoil of claim 1 , wherein at least one of the at least one outlet or the at least one inlet is multiple outlets or multiple inlets.

15. The airfoil of claim 1 , wherein the wall further comprises a thickened wall portion through which the connecting passage extends.

16. The airfoil of claim 1 , wherein the second portion comprises an inverse diffusing section located downstream of the impingement cavity wherein the second cross-sectional area decreases toward the outlet.

17. A component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising:
a wall separating the hot gas flow from the cooling fluid flow and having a heated surface along which the hot gas flows and a cooled surface facing the cooling fluid flow; and
at least one cooling hole comprising at least one inlet at the cooled surface and at least one outlet at the heated surface, at least one connecting passage extending between the at least one inlet and the at least one outlet, with an impingement cavity, the at least one connecting passage extending in a first direction between the inlet and the impingement cavity to define a first portion, the at least one connecting passage defining a first cross-sectional area increasing only in the first direction to define at least one diffusing section located upstream of the impingement cavity and formed within the first portion of the connecting passage;
wherein the impingement cavity is a disc-shaped impingement cavity with a biconcave disc shape having a depressed portion.

18. The component of claim 17 wherein the connecting passage further includes a second portion downstream of the impingement cavity.

19. The component of claim 18 wherein the impingement cavity defines a turn between the first portion and the second portion.

20. The component of claim 19 wherein at least one of the first or second portions define multiple branches of the connecting passage.

21. The component of claim 19 wherein the turn further defines a stagnation zone.

22. The component of claim 19 wherein the impingement cavity is a disc-shaped impingement cavity.

23. The component of claim 17 wherein the at least one of the outlet or inlet is multiple outlets or multiple inlets.

24. The component of claim 17 , wherein the first portion of the connecting passage intersects the disc-shape impingement cavity beyond a diameter of the depressed portion.

25. A method of cooling an engine component with at least one cooling hole extending through a wall of the engine component between an inlet along a cooled surface facing a cooling fluid flow and an outlet along a heated surface along which hot gas flows, the method comprising:
flowing the cooling fluid flow through at least one connecting passage in a first direction;
diffusing the cooling fluid in the first direction to form a first diffused airflow;
impinging the first diffused airflow of the cooling fluid flow on an impingement surface of a disc-shaped impingement cavity with a biconcave disc shape having a depressed portion and located between the cooled surface and the heated surface within the at least one cooling hole;
turning the cooling fluid flow from the first direction to a second direction; and
emitting the cooling fluid flow in the second direction onto the heated surface.

26. The method of claim 25 further comprising diffusing the cooling fluid to form a second diffused airflow in the second direction after turning the cooling fluid flow.

27. The method of claim 26 wherein emitting the diffused airflow onto the heated surface comprises emitting the second diffused airflow onto the heated surface.

28. The method of claim 25 further including splitting the diffused airflow into multiple branches.

29. The method of claim 25 further including turning the cooling fluid through an angle greater than or equal to 90 degrees.

30. The method of claim 25 further including slowing the cooling fluid flow to a velocity of zero.

Assignees

• Gen Electric

Inventors

• Webster Zachary Daniel
• Garay Gregory Terrence
• Brassfield Steven Robert

Classifications

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2250/324

  divergent · CPC title