Gas turbine engine component cooling cavity with vortex promoting features

Patent metadata

Field	Value
Publication number	US-10465530-B2
Application number	US-201415102335-A
Country	US
Kind code	B2
Filing date	Nov 17, 2014
Priority date	Dec 20, 2013
Publication date	Nov 5, 2019
Grant date	Nov 5, 2019

Abstract

A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features arranged in a helical pattern along the wall.

First claim

What is claimed is:

1. A component, comprising:
a body;
a wall extending inside of said body and circumscribing a cavity formed through said body; and
a plurality of vortex promoting features extending from said wall inward into said cavity and arranged in a dually helical pattern along said wall, wherein said plurality of vortex promoting features include at least one of pedestals and hemispherical protrusions, and said dually helical pattern includes a first helix formed by a first group of the plurality of vortex promoting features that extends in parallel with a second helix formed by a second group of the plurality of vortex promoting features wherein said helical pattern extends along a direction of flow through the cavity and has a varying pitch.

2. The component as recited in claim 1 , wherein said component is one of a blade, a vane, a blade outer air seal (BOAS), a combustor liner and a turbine exhaust case liner.

3. The component as recited in claim 1 , wherein said cavity includes one of a bowed, serpentine, helical, conical or contoured shape.

4. The component as recited in claim 1 , wherein said cavity includes a bowed shape.

5. The component as recited in claim 1 , wherein said cavity includes a serpentine shape.

6. The component as recited in claim 1 , wherein said cavity includes a helical shape.

7. The component as recited in claim 1 , wherein said plurality of vortex promoting features are implemented circumferentially in said cavity and vary in location relative to one another along a direction of flow within said cavity.

8. A gas turbine engine, comprising:
a component that defines a cavity configured to channel a cooling fluid to cool said component, said component including:
a wall that at least partially circumscribes said cavity; and
a plurality of vortex promoting features extending from said wall inward into said cavity and arranged in a dually helical pattern along said wall and configured to induce a vortexing flow of said cooling fluid through said cavity, wherein said plurality of vortex promoting features include at least one of pedestals and hemispherical protrusions, and said dually helical patterns includes a first helix formed by a first group of the plurality of vortex promoting features that extends in parallel with a second helix formed by a second group of the plurality of vortex promoting features wherein said helical pattern extends along a direction of flow through the cavity and has a varying pitch.

9. The gas turbine engine as recited in claim 8 , wherein said cavity includes one of a bowed, serpentine, helical, conical or contoured shape.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F01D5/187

  Convection cooling · CPC title

• F05D2260/2214

  by increasing the heat transfer surface · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F01D5/189 Primary

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