Coated cooling passage

Patent metadata

Field	Value
Publication number	US-2016273391-A1
Application number	US-201415029525-A
Country	US
Kind code	A1
Filing date	Sep 4, 2014
Priority date	Nov 4, 2013
Publication date	Sep 22, 2016
Grant date	—

Abstract

A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.

First claim

What is claimed is:

1 . A component for a gas turbine engine, comprising:
a substrate with a substrate aperture; and a coating on the substrate that extends a length of the substrate aperture.

2 . The component as recited in claim 1 , wherein the coating is thicker than a thickness of the substrate.

3 . The component as recited in claim 1 , wherein a thickness of the coating is between 10%-100% of a characteristic diameter of the substrate aperture.

4 . The component as recited in claim 1 , wherein the coating is a thermal barrier coating.

5 . The component as recited in claim 1 , wherein the coating is a signature reduction coating.

6 . The component as recited in claim 1 , wherein the coating is between about 0.010-0.1 inches (0.254-2.54 mm) thick.

7 . The component as recited in claim 1 , wherein the substrate defines a raised area toward a backside of the substrate.

8 . The component as recited in claim 1 , wherein the coating defines a coating inner periphery at least partially within a substrate inner periphery, and the coating inner periphery is smaller than the substrate inner periphery.

9 . The component as recited in claim 8 , wherein the coating inner periphery defines an angle with respect to an axis of the substrate aperture.

10 . A liner assembly for a gas turbine engine, the liner assembly comprising:
a hot sheet with a multiple of apertures; and a coating on the hot sheet that extends a length of each of the multiple of apertures.

11 . The liner assembly as recited in claim 10 , further comprising a cold sheet spaced from the hot sheet, wherein the cold sheet and the hot sheet are within an exhaust duct of a gas turbine engine.

12 . The liner assembly as recited in claim 10 , wherein the coating defines a coating inner periphery at least partially within a substrate inner periphery of each of the multiple of apertures, and the coating inner periphery is smaller than the substrate inner periphery.

13 . The liner assembly as recited in claim 12 , wherein the coating inner periphery defines an angle with respect to an axis of the substrate aperture.

14 . The liner assembly as recited in claim 12 , wherein the coating defines an unequal thickness within the substrate inner periphery.

15 . A method of forming an aperture to provide film cooling in a component of a gas turbine engine, the method comprising:
forming a multiple of substrate apertures in a substrate; and applying a coating on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures.

16 . The method as recited in claim 15 , further comprising applying the coating at a non-perpendicular angle to the substrate.

17 . The method as recited in claim 15 , further comprising punching the multiple of substrate apertures in the substrate from a front side to form a raised region on a backside of the substrate.

18 . The method as recited in claim 15 , further comprising laser drilling the multiple of substrate apertures in the substrate.

19 . The method as recited in claim 15 , wherein the coating inner periphery defines an angle with respect to an axis of the substrate aperture.

20 . The method as recited in claim 15 , wherein the coating defines an unequal thickness around the substrate inner periphery.

Assignees

• United Technologies Corp

Inventors

• Burd Steven W
• Brdar Christopher R
• Philippona Derk S

Classifications

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title