Plate for metering flow

Patent metadata

Field	Value
Publication number	US-10436113-B2
Application number	US-201514816125-A
Country	US
Kind code	B2
Filing date	Aug 3, 2015
Priority date	Sep 19, 2014
Publication date	Oct 8, 2019
Grant date	Oct 8, 2019

Abstract

A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

First claim

The invention claimed is:

1. A cooling device for a gas turbine engine component comprising:
a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path, and wherein the gas turbine engine component includes a platform with an opening to the downstream channel;
a meter feature including a meter plate associated with the opening and having at least one hole to meter flow from the upstream channel to the downstream channel, the meter plate having an upstream side and a downstream side, and wherein the at least one hole defines a center axis; and
an exit diffuser extending outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel, wherein the exit diffuser comprises a ring-shaped structure with an open center defined by an inner peripheral surface surrounding the center axis, and wherein the ring-shaped structure extends from the meter plate to a distal edge that opens into the downstream channel, and wherein the inner peripheral surface comprises a curved surface that curves from the meter plate to the distal edge, and wherein the curved surface curves radially outward from the meter plate until the distal edge.

2. The cooling device according to claim 1 , wherein the distal edge is spaced outwardly from the downstream side of the meter plate by a distance, and wherein the distance remains generally constant about the hole.

3. The cooling device according to claim 1 , wherein the distal edge is spaced outwardly from the downstream side of the meter plate by a distance, and wherein the distance varies about the hole.

4. The cooling device according to claim 1 , wherein the ring-shaped structure has a downstream diameter at the distal edge and an upstream diameter at the meter plate that is less than the downstream diameter.

5. The cooling device according to claim 1 , including at least one turbulator on the inner peripheral surface.

6. The cooling device according to claim 1 , wherein the exit diffuser is non-symmetrical about the hole.

7. The cooling device according to claim 1 , wherein the exit diffuser is symmetrical about the hole.

8. The cooling device according to claim 1 , including an inlet bellmouth extending outwardly from the upstream side of the meter plate.

9. The cooling device according to claim 8 , wherein the inlet bellmouth is non-symmetrical about the hole.

10. The cooling device according to claim 1 , wherein the center axis defines a first flow axis, and wherein the downstream channel defines a second flow axis that is obliquely orientated to the first flow axis.

11. The cooling device according to claim 1 , wherein the gas turbine engine component comprises an airfoil.

12. The cooling device according to claim 11 , wherein the airfoil includes the platform with the downstream channel comprising a cooling channel in the airfoil, and wherein the meter plate is mounted within the platform.

13. 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 an upstream channel and a downstream channel that define a cooling flow path, and wherein the component includes a platform with an opening to the downstream channel;
a meter feature including a meter plate associated with the opening and having at least one hole to meter flow from the upstream channel to the downstream channel, the meter plate having an upstream side and a downstream side, and wherein the at least one hole defines a center axis; and
an exit diffuser extending outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel, wherein the exit diffuser comprises a ring-shaped structure with an open center defined by an inner peripheral surface surrounding the center axis, and wherein the ring-shaped structure extends from the meter plate to a distal edge that opens into the downstream channel, and wherein the inner peripheral surface comprises a curved surface that curves from the meter plate to the distal edge, and wherein the curved surface curves radially outward from the meter plate until the distal edge.

14. The gas turbine engine according to claim 13 , wherein the exit diffuser is non-symmetrical about the hole.

15. The gas turbine engine according to claim 13 , wherein the exit diffuser is symmetrical about the hole.

16. The gas turbine engine according to claim 13 , including an inlet bellmouth extending outwardly from the upstream side of the meter plate.

17. The gas turbine engine according to claim 13 , wherein the ring-shaped structure has a downstream diameter at the distal edge and an upstream diameter at the meter plate that is less than the downstream diameter.

18. The gas turbine engine according to claim 13 , wherein the center axis defines a first flow axis, and wherein the downstream channel defines a second flow axis that is obliquely orientated to the first flow axis.

19. The gas turbine engine according to claim 13 , wherein the meter plate and exit diffuser comprise a single-piece structure.

20. The cooling device according to claim 1 , wherein the meter plate and exit diffuser comprise a single-piece structure.

21. A cooling device for a gas turbine engine component comprising:
a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path, and wherein the gas turbine engine component includes a platform with an opening to the downstream channel; and
a meter feature comprising a single-piece structure that comprises a meter plate and an exit diffuser, the meter plate associated with the opening and having at least one hole to meter flow from the upstream channel to the downstream channel, the meter plate having an upstream side and a downstream side, and the exit diffuser extending outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel, wherein the exit diffuser comprises a ring-shaped structure with an open center defined by an inner peripheral surface surrounding a center axis, and wherein the ring-shaped structure extends from the meter plate to a distal edge that opens into the downstream channel, and wherein the inner peripheral surface comprises a curved surface that curves from the meter plate to the distal edge, and wherein the curved surface curves radially outward from the meter plate until the distal edge.

22. The cooling device according to claim 21 , wherein the single-piece structure includes an inlet bellmouth extending outwardly from the upstream side of the meter plate.

23. The cooling device according to claim 21 , wherein the at least one hole defines the center axis.

24. The cooling device according to claim 23 , wherein the ring-shaped structure has a downstream diameter at the distal edge and an upstream diameter at the meter plate that is less than the downstream diameter.

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Mongillo Dominic J
• Gautschi Steven Bruce
• Ghigliotty Jaime G

Classifications

• F02C9/16

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title

• F05D2250/71

  curved · CPC title

• F05D2250/51

  Inlet · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D5/18

  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 title