Trailing Edge Configuration with Cast Slots and Drilled Filmholes

• US 20180202294A1
• Filed: 01/19/2017
• Published: 07/19/2018
• Est. Priority Date: 01/19/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Spangler, Brandon W.
• Granted Patent: US 10,641,103 B2
• Time in Patent Office: 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 and a trailing edge;

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

at least one cast slot formed in the trailing edge; and

at least one drilled filmhole 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.

2. The gas turbine engine component according to claim 1 wherein the at least one cast slot comprises a plurality of cast slots.

3. The gas turbine engine component according to claim 1 wherein the at least one drilled filmhole comprises a plurality of drilled filmholes.

4. The gas turbine engine component according to claim 1 wherein the at least one cast slot comprises a plurality of cast slots, and wherein the at least one drilled filmhole comprises a plurality of drilled filmholes.

5. The gas turbine engine component according to claim 4 wherein the body extends from a radially inner end to a radially outer end, and wherein the cast slots are positioned radially outward of the drilled filmholes.

6. The gas turbine engine component according to claim 4 wherein an axial direction is defined in a direction extending from the leading edge to the trailing edge, and wherein a radial direction is defined as a direction that is perpendicular to the axial direction, and wherein the cast slots extend in a generally axial direction and the drilled filmholes extend at an obtuse angle relative to the cast slots.

7. The gas turbine engine component according to claim 4 wherein the body extends from a radially inner end to a radially outer end, and wherein the cast slots are positioned radially inward of the drilled filmholes.

8. The gas turbine engine component according to claim 4 wherein an axial direction is defined in a direction extending from the leading edge to the trailing edge, and wherein a radial direction is defined as a direction that is perpendicular to the axial direction, and wherein the cast slots are interspersed with the drilled filmholes in a radial direction along the trailing edge.

9. The gas turbine engine component according to claim 8 wherein the cast slots extend in the axial direction and the drilled filmholes extend at an obtuse angle relative to the cast slots.

10. The gas turbine engine component according to claim 4 wherein the body comprises a vane, blade or BOAS.

11. The gas turbine engine component according to claim 4 wherein the body comprises a turbine component.

12. 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,

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 trailing edge, and

a plurality of drilled filmholes formed in the trailing edge, wherein the cast slots and drilled filmholes direct flow from the internal channel to an external location from the turbine component.

13. The gas turbine engine according to claim 12 wherein the turbine component comprises a vane, blade or BOAS.

14. The gas turbine engine according to claim 12 wherein the cast slots having 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.

15. The gas turbine engine according to claim 12 wherein the cast slots are configured to position a core during a casting process for the turbine component.

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 from a leading edge to a trailing edge;

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; and

drilling a plurality of filmholes in the trailing edge subsequent to the casting process, wherein the cast slots and filmholes are configured to direct flow from the internal cooling channel to an external location from the body.

17. The method according to claim 16 including forming the cast slots to extend in a generally axial direction and forming the drilled 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 a radial direction along the trailing edge.

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

20. A method of controlling flow in a gas turbine engine component comprising:

a body having a leading edge and a trailing edge;

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

forming 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 and providing another portion of trailing edge flow with drilled holes.