Gas turbine engine component with increased cooling capacity

Patent metadata

Field	Value
Publication number	US-10247011-B2
Application number	US-201514923553-A
Country	US
Kind code	B2
Filing date	Oct 27, 2015
Priority date	Dec 15, 2014
Publication date	Apr 2, 2019
Grant date	Apr 2, 2019

Abstract

A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

First claim

The invention claimed is:

1. A cooling circuit for a gas turbine engine comprising:
a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall, wherein the internal cavity is defined by a height and a width that is greater than the height, and wherein the height is within the range of 0.100-0.300 inches (2.54-7.62 mm); and
a plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole, and wherein the minimum allowable ligament distance is at least 0.003 inches (0.076 mm) and not more than 0.050 inches (1.27 mm), and wherein each cooling hole as a diameter within a range of 0.010-0.030 inches (0.254-0.762 mm).

2. The cooling circuit according to claim 1 wherein each cooling hole has a uniform shape.

3. The cooling circuit according to claim 2 wherein the uniform shape comprises a cylindrical shape.

4. The cooling circuit according to claim 2 wherein each cooling hole defines a hole center axis and wherein the center axes are parallel to each other.

5. The cooling circuit according to claim 1 wherein each hole has a non-uniform shape.

6. The cooling circuit according to claim 5 wherein the non-uniform shape comprises a first portion at the cooling hole inlet that is defined by a first cross-sectional area and a second portion at the cooling hole outlet that is defined by a second cross-sectional area greater than the first cross-sectional area.

7. The cooling circuit according to claim 6 wherein each cooling hole defines a center axis, and wherein at least one center axis of one cooling hole is non-parallel to at least one center axis of another cooling hole.

8. The cooling circuit according to claim 6 wherein the cooling hole inlet of at least one cooling hole is axially aligned with the cooling hole outlet of the at least one cooling hole.

9. The cooling circuit according to claim 1 wherein the plurality of cooling holes includes at least a first row of cooling holes and a second row of cooling holes spaced from the first row of cooling holes.

10. The cooling circuit according to claim 9 wherein at least one cooling hole in the first row of cooling holes is oriented to extend in a first direction and at least one cooling hole in the second row of cooling holes is orientated to extend in a second direction different than the first direction.

11. The cooling circuit according to claim 1 wherein the gas turbine engine component comprises one of an airfoil, a blade, a vane, a BOAS, or a combustor panel.

12. A gas turbine engine comprising:
a compressor section;
a combustor section downstream of the compressor section; and
a turbine section downstream of the combustor section, and wherein at least one of the combustor section and the turbine section include a component having a body with at least one internal cavity defined by a cavity wall, and a plurality of cooling holes formed within the cavity wall, wherein the internal cavity is defined by a height and a width that is greater than the height, and wherein the height is within the range of 0.100-0.300 inches (2.54-7.62 mm), and wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole, and wherein the minimum allowable ligament distance is at least 0.003 inches (0.076 mm) and not more than 0.050 inches (1.27 mm), and wherein each cooling hole as a diameter within a range of 0.010-0.030 inches (0.254-0.762 mm).

13. The gas turbine engine according to claim 12 wherein the component comprises an airfoil, a combustor panel, or BOAS.

14. The gas turbine engine according to claim 12 wherein the plurality of cooling holes includes at least a first row of cooling holes and a second row of cooling holes spaced from the first row of cooling holes, and wherein at least one cooling hole in the first row of cooling holes is oriented to extend in a first direction and at least one cooling hole in the second row of cooling holes is orientated to extend in a second direction different than the first direction.

15. The gas turbine engine according to claim 12 wherein each cooling hole comprises a first portion at the cooling hole inlet that is defined by a first cross-sectional area and a second portion at the cooling hole outlet that is defined by a second cross-sectional area greater than the first cross-sectional area.

16. A method of forming a cooling circuit for a gas turbine engine comprising the steps of:
(a) providing a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall, wherein the internal cavity is defined by a height and a width that is greater than the height, and wherein the height is within the range of 0.100-0.300 inches (2.54-0.762 mm); and
(b) forming a plurality of cooling holes within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet; and
(c) forming the cooling holes relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole, wherein the minimum allowable ligament distance is at least 0.003 inches (0.076 mm) and not more than 0.050 inches (1.27 mm), and wherein each cooling hole has a diameter within a range of 0.010-0.030 inches (0.254-0.762 mm).

17. The method according to claim 16 including forming at least two rows of cooling holes in the cavity wall.

18. The gas turbine engine according to claim 12 wherein each cooling hole has a variable cross-section.

19. The gas turbine engine according to claim 12 wherein the plurality of cooling holes includes at least a first row of cooling holes and a second row of cooling holes spaced from the first row of cooling holes.

20. The cooling circuit according to claim 1 wherein each cooling hole has a variable cross-section.

Assignees

• United Technologies Corp

Inventors

• Quach San
• King Christopher
• Slavens Thomas N

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F01D5/186 Primary

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

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title