Gas turbine engine component cooling passage turbulator

Patent metadata

Field	Value
Publication number	US-10364683-B2
Application number	US-201415036833-A
Country	US
Kind code	B2
Filing date	Nov 5, 2014
Priority date	Nov 25, 2013
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.

First claim

What is claimed is:

1. A gas turbine engine component comprising:
opposing walls providing an interior cooling passage, one of the walls has a turbulator with a hook provided as a cross-section of the turbulator that is enclosed within the walls, wherein the hook includes a first portion extending from a surface of the one wall, and a second portion extends from the first portion longitudinally within the interior cooling passage to a terminal end providing an overhang that is unattached with respect to the surface, wherein the interior flow passage is configured to provide a flow direction, and the second portion faces away from the flow direction, and wherein the first and second portions and the surface provide a pocket, the pocket configured to provide a cavitation zone.

2. A gas turbine engine component comprising:
opposing walls providing an interior cooling passage, one of the walls has a turbulator with a hook provided as a cross-section of the turbulator that is enclosed within the walls, wherein the hook includes a first portion extending from a surface of the one wall, and a second portion extends from the first portion longitudinally within the interior cooling passage to a terminal end providing an overhang that is unattached with respect to the surface, wherein the interior flow passage is configured to provide a flow direction, and the second portion faces into the flow direction, and wherein the first and second portions and the surface provide a pocket, the pocket configured to provide a cavitation zone.

3. The gas turbine engine component according to claim 1 , wherein the first portion has a height, and the second portion has a width, the aspect ratio of height to width in the range of 0.1-10.

4. The gas turbine engine component according to claim 1 , wherein the hook provides a chevron.

5. The gas turbine engine component according to claim 1 , wherein the hook provides a curved saw-tooth shaped structure.

6. The gas turbine engine component according to claim 1 , wherein the second portion is parallel to the surface.

7. The gas turbine engine component according to claim 1 , wherein gas turbine engine component is one of a blade, a vane, a combustor liner, an exhaust liner, and a blade outer air seal.

8. The gas turbine engine component according to claim 1 , wherein the turbulator provides a surface protrusion with a stream-wise cross-sectional shape providing at least one secondary surface near parallel with the wall to which the protrusion is affixed.

9. A method of cooling a gas turbine engine component including walls providing an interior cooling passage configured to provide a flow direction, one of the walls has a turbulator with a hook that is enclosed within the walls, the method comprising the step of:
providing the hook as a cross-section of the turbulator, wherein the hook includes a first portion extending from a surface of the one wall, and a second portion extends from the first portion longitudinally within the interior cooling passage to a terminal end providing an overhang that is unattached with respect to the surface to provide a pocket;
passing a fluid flow through the interior cooling passage; and
cavitating the fluid flow through the interior cooling passage in the pocket provided by the hook.

10. The method according to claim 9 , wherein the hook provides at least one of a curved saw-tooth shaped structure and the second portion is parallel to the surface.

11. The method according to claim 9 , wherein the first portion has a height, and the second portion has a width, the aspect ratio of height to width in the range of 0.1-10.

Assignees

• United Technologies Corp

Inventors

• Snyder Brooks E
• Slavens Thomas N
• Loricco Nicholas M
• Auxier James T

Classifications

• F05D2260/2212

  by creating turbulence · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/182

  Transpiration cooling · CPC title

• F01D5/181

  Blades having a closed internal cavity containing a cooling medium, e.g. sodium · CPC title

• F05D2240/127

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