Trailing edge configuration with cast slots and drilled filmholes

• US 10,641,103 B2
• Filed: 01/19/2017
• Issued: 05/05/2020
• Est. Priority Date: 01/19/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Spangler, Brandon W.
• Primary Examiner(s): Lee, Jr., Woody A
• Assistant Examiner(s): Sehn, Michael L
• Application Number:
  US15/409,613
• Publication Number:
  US 20180202294A1
• Time in Patent Office: 1,202 Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine component comprises a body having a leading edge and a trailing edge. At least one internal channel is formed within the body, wherein the channel includes an inlet to direct cooling flow into the body. At least one cast slot is formed in the trailing edge. At least one drilled filmhole is formed in the trailing edge, wherein the cast slot and drilled filmhole direct flow from the internal channel to an external location from the body. A gas turbine engine, a method of manufacturing a gas turbine engine component, and a method of controlling flow in a gas turbine engine component.

Claims

1. A gas turbine engine component comprising:

a body having a leading edge, a trailing edge, and an external side surface extending from the leading edge to the trailing edge and from a radially inner end to a radially outer end, and wherein an axial direction is defined in a direction extending from the leading edge to the trailing edge, and a radial direction is defined as a direction that is perpendicular to the axial direction;

at least one internal channel formed within the body, wherein the channel includes an inlet to direct cooling flow into the body;

a plurality of cast slots formed in the external side surface along the trailing edge and having slot outlets spaced apart from each other in the radial direction; and

a plurality of drilled filmholes formed in the external side surface along the trailing edge and having hole outlets spaced apart from each other in the radial direction, wherein the slot outlets and hole outlets are spaced apart from each other along the external side surface in the radial direction such that the cast slots and drilled filmholes direct flow from the internal channel to an external location from the body, and wherein the plurality of drilled filmholes and the plurality of cast slots are both aligned and spaced apart from each other in the radial direction along a common radial path that extends from the radially inner end to the radially outer end.

2. The gas turbine engine component according to claim 1 wherein the plurality of drilled filmholes include at least some drilled filmholes that are more closely spaced to each other in the radial direction than other drilled filmholes.

3. The gas turbine engine component according to claim 1 wherein

the plurality of cast slots are all positioned radially outward of the plurality of drilled filmholes along the common radial path or the plurality of cast slots are all radially inboard of the plurality of drilled filmholes along the common radial path, or

the plurality of cast slots are interspersed with the plurality of drilled filmholes in an alternating pattern along the common radial path such that one or more cast slots are directly between adjacent drilled filmholes and/or one or more drilled filmholes are directly between adjacent cast slots.

4. The gas turbine engine component according to claim 1 wherein the cast slots extend in the axial direction and the drilled filmholes extend at an obtuse angle relative to the cast slots.

5. The gas turbine engine component according to claim 1 wherein the body extends from a radially inner end to a radially outer end, and wherein all of the cast slots are positioned radially inward of the drilled filmholes or all of the cast slots are positioned radially outward of the drilled filmholes.

6. The gas turbine engine component according to claim 1 wherein each drilled filmhole has a hole inlet in communication with the internal channel and extends to the hole outlet to the external side surface, and wherein each cast slot has a slot inlet in communication with the internal channel and extends to the slot outlet to the external side surface, and wherein the cast slots are interspersed with the drilled filmholes in a radial direction along the trailing edge such that the hole outlets and the slot outlets are separate from each other in the radial direction and such that the hole outlets are spaced apart from the cast slots in the radial direction.

7. The gas turbine engine component according to claim 6 wherein the cast slots extend in the axial direction and the drilled filmholes extend at an obtuse angle relative to the cast slots.

8. The gas turbine engine component according to claim 1 wherein the body comprises a vane, blade or blade outer air seal.

9. The gas turbine engine component according to claim 1 wherein the body comprises a turbine component.

10. The gas turbine engine component according to claim 1 wherein each cast slot is spaced apart from each drilled filmhole along the common radial path.

11. A gas turbine engine comprising:

a compressor section defining an engine center axis;

a combustor section downstream of the compressor section; and

a turbine section downstream of the combustor section, wherein the turbine section includes a turbine component having

a leading edge extending to a trailing edge to define an axial direction along the engine center axis,

an external side surface extending from the leading edge to the trailing edge,

a radially inner end extending to a radially outer end to define a radial direction,

at least one internal channel formed within the turbine component, wherein the channel includes an inlet to direct cooling flow into the turbine component,

a plurality of cast slots formed in the external side surface along the trailing edge and having slot outlets spaced apart from each other in the radial direction, and

a plurality of drilled filmholes formed in the external side surface along the trailing edge and having hole outlets spaced apart from each other in the radial direction, wherein the slot outlets and hole outlets are spaced apart from each other along the external side surface in the radial direction such that the cast slots and drilled filmholes direct flow from the internal channel to an external location from the turbine component, and wherein the plurality of drilled filmholes and the plurality of cast slots are both aligned and spaced apart from each other in the radial direction along a common radial path that extends from the radially inner end to the radially outer end.

12. The gas turbine engine according to claim 11 wherein the turbine component comprises a vane, blade or blade outer air seal, and wherein

the plurality of cast slots are all positioned radially outward of the plurality of drilled filmholes along the common radial path or the plurality of cast slots are all radially inboard of the plurality of drilled filmholes along the common radial path, or

the plurality of cast slots are interspersed with the plurality of drilled filmholes in an alternating pattern along the common radial path such that one or more cast slots are directly between adjacent drilled filmholes and/or one or more drilled filmholes are directly between adjacent cast slots.

13. The gas turbine engine according to claim 11 wherein the cast slots have a length greater than a width, and wherein the length extends in the axial direction and the drilled filmholes extend along an obtuse angle relative to the cast slots.

14. The gas turbine engine according to claim 11 wherein the cast slots are configured to position a core during a casting process for the turbine component.

15. The gas turbine engine according to claim 11 wherein each cast slot is spaced apart from each filmhole along the common radial path.

16. A method of manufacturing a gas turbine engine component comprising:

using a core to form at least one internal cooling channel in a body, wherein the body extends along an external side surface from a leading edge to a trailing edge and from a radially inner end to a radially outer end, and wherein an axial direction is defined in a direction extending from the leading edge to the trailing edge, and a radial direction is defined as a direction that is perpendicular to the axial direction;

providing a plurality of slots with the core to be located at the trailing edge, wherein the slots position the core during a casting process and form cast slots in the trailing edge that have slot outlets spaced apart from each other in the radial direction; and

drilling a plurality of filmholes in the external side surface along the trailing edge subsequent to the casting process, the filmholes having hole outlets spaced apart from each other in the radial direction, and spacing the slot outlets and hole outlets apart from each other along the external side surface in the radial direction such that the cast slots and filmholes are configured to direct flow from the internal cooling channel to an external location from the body, and wherein the plurality of filmholes and the plurality of slots are both aligned and spaced apart from each other in the radial direction along a common radial path that extends from the radially inner end to the radially outer end.

17. The method according to claim 16 including casting the cast slots to extend in the axial direction and drilling the filmholes to extend at an obtuse angle relative to the cast slots.

18. The method according to claim 16 including interspersing the cast slots with the filmholes in the radial direction along the trailing edge such that

the plurality of slots are all positioned radially outward of the plurality of filmholes along the common radial path or the plurality of slots are all radially inboard of the plurality of filmholes along the common radial path, or

the plurality of slots are interspersed with the plurality of filmholes in an alternating pattern along the common radial path such that one or more slots are directly between adjacent filmholes and/or one or more filmholes are directly between adjacent slots.

19. The method according to claim 16 including tailoring filmhole sizes and spacing the filmholes relative to the cast slots to meet cooling flow requirements for a specified engine configuration.

20. The method according to claim 16 wherein each cast slot is spaced apart from each filmhole along the common radial path.

21. A method of controlling flow in a gas turbine engine component, the method comprising:

a body having a leading edge, a trailing edge, and an external side surface extending from the leading edge to the trailing edge and from a radially inner end to a radially outer end, and wherein an axial direction is defined in a direction extending from the leading edge to the trailing edge, and a radial direction is defined as a direction that is perpendicular to the axial direction;

at least one internal channel formed within the body, wherein the channel includes an inlet to direct cooling flow into the body; and

arranging a plurality of flow exit features along the trailing edge to tailor cooling flow to a predetermined amount at each desired location along an entire radial span of the trailing edge by providing one portion of trailing edge flow with cast slots that are spaced apart from each other in the radial direction and providing another portion of trailing edge flow with drilled film holes that are spaced apart from each other in the radial direction such that outlets from the drilled filmholes are in the external side surface and spaced apart from the cast slots in the radial direction, and wherein the drilled filmholes and the cast slots are both aligned and spaced apart from each other in the radial direction along a common radial path that extends from the radially inner end to the radially outer end.

22. The method according to claim 21 wherein each cast slot is spaced apart from each drilled hole along the common radial path such that

the cast slots are all positioned radially outward of the drilled filmholes along the common radial path or the cast slots are all radially inboard of the drilled filmholes along the common radial path, or

the cast slots are interspersed with the drilled filmholes in an alternating pattern along the common radial path such that one or more cast slots are directly between adjacent drilled filmholes and/or one or more drilled filmholes are directly between adjacent cast slots.