Baffle insert for a gas turbine engine component and method of cooling

Patent metadata

Field	Value
Publication number	US-10280841-B2
Application number	US-201514961694-A
Country	US
Kind code	B2
Filing date	Dec 7, 2015
Priority date	Dec 7, 2015
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine. The method including the steps of: directing a cooling fluid between an interior surface of an internal cooling cavity of the component and an exterior surface of a baffle insert located in the internal cooling cavity; and creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity, wherein the internal cooling cavity is elliptical in shape.

First claim

What is claimed is:

1. A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine, comprising:
directing a cooling fluid between an interior surface of an internal cooling cavity of the component and an exterior surface of a baffle insert located in the internal cooling cavity; and
creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity, wherein the internal cooling cavity is elliptical in shape.

2. The method as in claim 1 , wherein the plurality of vortices are created by a plurality of trip strips extending upwardly from at least one of the exterior surface of the baffle insert and the interior surface of the internal cooling cavity; and
wherein at least one of the exterior surface of the baffle insert and the interior surface of the internal cooling cavity has at least one separating feature located between a pair of ends of a pair of the plurality of trip strips.

3. The method as in claim 2 , wherein the at least one separating feature is at least one of a rib and a gap.

4. The method as in claim 2 , wherein the plurality of trip strips are arranged around the entire perimeter of at least one of the exterior surface of the baffle insert and the interior surface of the internal cooling cavity.

5. The method as in claim 2 , wherein the plurality of trip strips on at least one of the baffle insert and the interior surface of the internal cooling cavity are arranged in at least one of the following configurations: a corkscrew configuration; an offset corkscrew configuration; a chevron configuration; an offset chevron configuration; a spiral corkscrew configuration; an offset spiral corkscrew configuration; a multi-length corkscrew configuration; and a crosshatch configuration.

6. The method as in claim 2 , wherein a plurality of trip strips and at least one separating feature are located on the exterior surface of the baffle insert; and
wherein a plurality of trip strips and at least one separating feature are located on the interior surface of the internal cooling cavity.

7. The method as in claim 6 , wherein the plurality of trip strips of the baffle insert are arranged in a co-flowing configuration with respect to the plurality of trip strips of the interior surface of the internal cooling cavity.

8. The method as in claim 6 , wherein the plurality of trip strips of the baffle insert are arranged in a counter-flowing configuration with respect to the plurality of trip strips of the interior surface of the internal cooling cavity.

9. The method as in claim 1 , wherein the component is one of a vane, a blade, a blade outer air seal, and a combustor panel.

10. A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine, comprising:
directing a cooling fluid between an interior surface of an internal cooling cavity of the component and an exterior surface of a baffle insert located in the internal cooling cavity, wherein the exterior surface of the baffle insert is elliptical in shape; and
creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity.

11. The method as in claim 10 , wherein the internal cooling cavity is elliptical in shape.

12. The method as in claim 10 , wherein the vortices are created by a plurality of trip strips extending upwardly from at least one of the exterior surface of the baffle insert and the interior surface of the internal cooling cavity; and
wherein at least one of the exterior surface of the baffle insert and the interior surface of the internal cooling cavity contains at least one separating feature located between a pair of ends of a pair of the plurality of trip strips.

13. The method as in claim 12 , wherein the at least one separating feature is at least one of a rib and a gap.

14. The method as in claim 12 , wherein the plurality of trip strips are arranged around the entire perimeter of at least one of the baffle insert and the interior surface of the internal cooling cavity.

15. The method as in claim 12 , wherein the plurality of trip strips on at least one of the baffle insert and the interior surface of the internal cooling cavity are arranged in at least one of the following configurations: a corkscrew configuration; an offset corkscrew configuration; a chevron configuration; an offset chevron configuration; a spiral corkscrew configuration; an offset spiral corkscrew configuration; a multi-length corkscrew configuration; and a crosshatch configuration.

16. The method as in claim 12 , wherein a portion of the plurality of trip strips and at least one separating feature are located on the exterior surface of the baffle insert; and
wherein the portion of the plurality of trip strips and at least one separating feature are located on the interior surface of the internal cooling cavity.

17. The method as in claim 16 , wherein the portion of the plurality of trip strips of the baffle insert are arranged in a co-flowing configuration with respect to the portion of the plurality of trip strips of the interior surface of the internal cooling cavity.

18. The method as in claim 16 , wherein the portion of the plurality of trip strips of the baffle insert are arranged in a counter-flowing configuration with respect to the portion of the plurality of trip strips of the interior surface of the internal cooling cavity.

19. The method as in claim 10 , wherein the component is one of a vane, a blade, a blade outer air seal, and a combustor panel.

20. The method as in claim 1 , wherein the plurality of vortices create a swirling flow field that enhances heat transfer from the interior surface of the internal cooling cavity to the cooling fluid.

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W
• Kohli Atul

Classifications

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F05D2240/126

  Baffles or ribs · CPC title

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F01D5/189

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title