Gas turbine engine component with a cooling circuit having a flared base

Patent metadata

Field	Value
Publication number	US-10815792-B2
Application number	US-201916239949-A
Country	US
Kind code	B2
Filing date	Jan 4, 2019
Priority date	Jan 4, 2019
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

A component for a gas turbine engine includes a body portion that extends between a leading edge and a trailing edge of the component. The trailing edge includes a flared region and a non-flared region. At least one discharge slot is disposed at least partially within the flared region of the component.

First claim

What is claimed is:

1. A component for a gas turbine engine, comprising:
a body portion that extends between a leading edge and a trailing edge, wherein said trailing edge includes a cooling circuit having a flared region and a non-flared region, the flared region having a first thickness that increases to the trailing edge as the trailing edge is approached at a consistent span and the non-flared region have a second thickness that remains constant or decreases as the trailing edge is approached at a consistent span;
the trailing edge further including at least one discharge slot, and a first discharge slot of the at least one discharge slot is disposed partially within the flared region of the cooling circuit;
and wherein the cooling circuit defines a first width in the flared region and a second width in the non-flared region, the first width being larger than the second width, and wherein the flared region is disposed partially in a filleted region of the body and partially outside of the filleted region of the body.

2. The component as recited in claim 1 , wherein the at least one discharge slot has a first portion that includes an oval geometry.

3. The component as recited in claim 1 , wherein said component is one of a vane and a blade.

4. The component as recited in claim 1 , wherein said at least one discharge slot includes a plurality of second discharge slots.

5. The component as recited in claim 1 , further comprising at least a second discharge slot disposed radially outward of the first discharge slot.

6. The component as recited in claim 1 , further comprising at least a second discharge slot disposed radially inward of the first discharge slot.

7. The component as recited in claim 1 , wherein said at least one discharge slot is positioned at a position that is immediately adjacent to a platform of said component.

8. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section along a core flow path;
a turbine section in fluid communication with said combustor section along said core flow path;
a component that extends into said core flow path within at least one of said compressor section and said turbine section, wherein said component includes a body portion that extends between a leading edge and a trailing edge;
wherein the body portion includes an internal cooling circuit having flared region having a first thickness that increases to the trailing edge as the trailing edge is approached at a consistent span and a non-flared region having a second thickness that remains constant or decreases as the trailing edge is approached at a consistent span, and wherein a widest portion of the first thickness is larger than a widest portion of the second thickness; and
wherein the component further includes at least one internal cooling circuit discharge slot is disposed partially within the flared region, and wherein the flared region is disposed partially in a filleted region of the body portion and partially outside of the filleted region of the body portion.

9. The gas turbine engine as recited in claim 8 , wherein said component is one of a vane and a blade.

10. The gas turbine engine as recited in claim 8 , wherein the flared region is disposed at a radially innermost edge of the component, relative to a radius of the gas turbine engine.

11. The gas turbine engine as recited in claim 8 , wherein the flared region extends less than 100% of the distance from the leading edge to the trailing edge.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Auxier James Tilsley
• Morton Jeffrey T
• Gleiner Matthew S
• Jariwala Parth
• Thistle Charles
• Kwolek Megan J

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · 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

• F05D2240/81

  Cooled platforms · CPC title

• F05D2240/125

  related to the tip of a stator vane · CPC title