Interface for double-skin combustor liner

Patent metadata

Field	Value
Publication number	US-11054136-B2
Application number	US-201816205933-A
Country	US
Kind code	B2
Filing date	Nov 30, 2018
Priority date	Nov 30, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

An interface for double-skin combustor liner comprises an annular ceramic matrix composite (CMC) body. The annular body extends from a first side to a second side, the first and second sides each having an annular inner joint groove configured to receive a CMC combustor skin and an annular outer joint groove configured to receive a metal combustor skin. The outer joint groove is radially outward of the inner joint groove. A combustor and an gas turbine engine with the interface are also provided.

First claim

The invention claimed is:

1. An interface for a double-skin combustor liner, the interface comprising an annular ceramic matrix composite (CMC) body formed about a center axis, the annular both extending from a first side on a first axial end of the annular body to a second side on a second axial end of the annular both spaced axially apart from the first axial end, the first and second sides each having an annular inner joint groove extending axially from each of the first and second axial ends into the annular body toward the other of the first and second axial ends, each annular inner joint groove configured to receive a respective CMC combustor skin, and the first and second sides each having an annular outer joint groove extending axially from each of the first and second axial ends into the annular body toward the other of the first and second axial ends, each annular outer joint groove configured to receive a respective metal combustor skin, each annular outer joint groove being radially outward of each annular inner joint groove.

2. The interface according to claim 1 , wherein at least one of the annular inner joint grooves defines a respective sliding surface for the respective CMC combustor skin, the respective sliding surface oriented with a radial component and an axial component relative to the center axis of the annular CMC body.

3. The interface according to claim 1 , wherein a plurality of holes extend from an outer circumferential face of the annular CMC body to an inner circumferential face of the annular CMC body, the holes being circumferentially distributed in the annular CMC body.

4. The interface according to claim 3 , wherein the holes are quench jet holes.

5. The interface according to claim 3 , further comprising fluid passages extending from one of the first side and the second side and distributed circumferentially.

6. The interface according to claim 3 , further comprising necks projecting from the outer circumferential face around the holes.

7. The interface according to claim 1 , wherein the annular CMC body is a CMC monoblock.

8. The interface according to claim 1 , wherein the annular CMC body is CMC arcuate segments joined end to end to form the annular CMC body.

9. A combustor for a gas turbine engine comprising:
a combustor chamber having a dome portion and a duct portion, the dome and duct portions each having an inner ceramic matrix composite (CMC) skin and an outer skin radially spaced from the inner CMC skin, each inner CMC skin defining a part of an inner surface of the combustor chamber; and
an annular CMC interface formed about a center axis and disposed between the dome and duct portions, the interface extending from a first side at a first axial end of the annular CMC interface to a second side at a second axial end of the annular CMC interface and having an inner circumferential face providing a portion of the inner surface of the combustor chamber, the first and second sides each having an inner annular joint groove extending from each of the first and second axial ends into the annular CMC interface toward the other of the first and second axial ends, each inner joint groove receiving a respective one of the inner CMC skins of the dome and duct portions to form a continuous CMC surface with the inner circumferential face and an outer annular joint groove extending axially from each of the first and second axial ends into the annular CMC interface toward the other of the first and second axial ends, each outer joint groove receiving a respective one of the outer skin of the dome and duct portions, each outer joint groove being radially outward of each inner joint groove.

10. The combustor according to claim 9 , wherein each of the dome and duct portions has a double-skin construction on opposite sides of the interface.

11. The combustor according to claim 10 , wherein the outer skins of the dome and duct portions on opposite sides of the interface are connected by an annular cap covering the interface.

12. The combustor according to claim 10 , comprising springs biasing the interface against the outer skins.

13. The combustor according to claim 9 , wherein at least one of the inner joint grooves defines a respective sliding surface for the respective inner CMC skin, the respective sliding surface oriented with a radial component and an axial component relative to the center axis of the annular CMC interface.

14. The combustor according to claim 9 , wherein a plurality of holes extend from an outer circumferential face of the annular CMC interface to the inner circumferential face of the annular CMC interface, the holes being circumferentially distributed in the annular CMC interface.

15. The combustor according to claim 14 , further comprising fluid passages extending from one of the first side and the second side to the holes, the fluid passages being in fluid communication with an annular space.

16. The combustor according to claim 14 , further comprising necks projecting from the outer circumferential face around the holes.

17. A gas turbine engine comprising:
a combustor defined by a combustor Chamber having a dome portion and a duct portion, the dome and duct portions each having an inner ceramic matrix composite (CMC) skin and an outer skin radially spaced from the inner CMC skin with respect to a center axis of the gas turbine engine, each inner CMC skin defining a part of an inner surface of the combustor chamber; and
an annular CMC interface formed about the center axis and disposed between the dome and duct portions, the interface extending from a first side at a first axial end of the interface to a second side at a second axial end of the interface and having an inner circumferential face providing a portion of the inner surface of the combustor chamber, the first and second sides each having an inner annular joint groove extending axially from each of the first and second axial ends into the interface toward the other of the first and second axial ends, each inner joint groove receiving a respective one of the inner CMC skins to form a continuous CMC surface with the inner circumferential face, and an outer annular joint groove extending axially from each of the first and second axial ends into the interface toward the other of the first and second axial ends, each outer joint groove receiving a respective one of the outer skins, each outer joint groove being radially outward of each inner joint groove.

Assignees

• Pratt & Whitney Canada

Inventors

• Hu Tin-Cheung John
• Sze Robert

Classifications

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title