Seals for a gas turbine engine assembly

Patent metadata

Field	Value
Publication number	US-10704404-B2
Application number	US-201615076127-A
Country	US
Kind code	B2
Filing date	Mar 21, 2016
Priority date	Apr 30, 2015
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

Abstract

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a pressure-activated seal. The pressure-activated seal is arranged in a channel formed between a first component and a second component that opens toward the high pressure zone.

First claim

What is claimed is:

1. A gas turbine engine assembly comprising
a first component comprising ceramic matrix materials, the first component including a panel arranged to separate a high pressure zone from a low pressure zone and a plurality of hangers that extend radially outward from the panel and are configured to couple the panel of the first component to a surrounding structure, the panel formed to include a first chamfer surface that extends from a radially-outwardly facing surface of the first component facing the high pressure zone to a first circumferentially-facing side surface of the first component,
a second component comprising ceramic matrix materials, the second component including a panel arranged to separate the high pressure zone from the low pressure zone and a plurality of hangers that extend radially outward from the panel and are configured to couple the panel of the second component to the surrounding structure, the panel formed to include a second chamfer surface that extends from a radially-outwardly facing surface of the second component facing the high pressure zone to a second circumferentially-facing side surface of the second component, and
a seal arranged in a channel formed by the first chamfer surface and the second chamfer surface when the first circumferentially-facing side surface of the first component is arranged in confronting relation to the second circumferentially-facing side surface of the second component, the seal having a first seal surface that contacts the first chamfer surface and a second seal surface that contacts the second chamfer surface, and the seal shaped to be pushed into contact with the first chamfer surface and the second chamfer surface by pressure in the high pressure zone so that the seal resists gasses from moving through a gap between the first circumferentially-facing side surface of the first component and the second circumferentially-facing side surface of the second component,
wherein the first chamfer surface extends only partway along the first side surface of the panel included in the first component, the first chamfer surface having a first end that is spaced apart from a forward side surface of the panel included in the first component and a second end spaced part from an aft side surface of the panel included in the first component, and the plurality of hangers of the first component are arranged axially between the first end and the second end of the first chamfer surface,
wherein the second chamfer surface extends only partway along the second side surface of the panel included in the second component, the second chamfer surface having a first end that is spaced apart from a forward side surface of the panel included in the second component and a second end spaced apart from an aft side surface of the panel included in the second component, and the plurality of hangers of the second component are arranged axially between the first end and the second end of the second chamfer surface,
wherein the plurality of hangers of the first component includes a first hanger and a second hanger spaced apart axially from the first hanger of the first component, the first hanger of the first component includes a first retention tab that extends over the channel to block the seal from movement out of the channel, and the second hanger of the first component includes a second retention tab that extends over the channel to block the seal from movement out of the channel, and
wherein the plurality of hangers of the second component includes a first hanger and a second hanger spaced apart axially from the first hanger of the second component, the first hanger of the second component includes a first retention tab that extends over the channel to block the seal from movement out of the channel, and the second hanger of the second component includes a second retention tab that extends over the channel to block the seal from movement out of the channel.

2. The assembly of claim 1 , wherein the seal has a first leg that provides the first seal surface and a second leg that provides the second seal surface, the seal is shaped to form a trough between the first leg and the second leg, and the seal is arranged so that the trough is open to the high pressure zone.

3. The assembly of claim 2 , wherein the seal has a V-shaped cross-section.

4. The assembly of claim 2 , wherein the first leg and the second leg each have a curved shaped cross-section.

5. The assembly of claim 2 , wherein the first and second retention tabs of the first component and the first and second retention tabs of the second component block the first leg and the second leg of the seal from extending radially outward past the radially-outwardly facing surface of the first component and radially-outwardly facing surface of the second component.

6. The assembly of claim 1 , wherein the seal is formed to include a bleed feature configured to allow a predetermined amount of gas to pass through the seal.

7. The assembly of claim 6 , wherein the bleed feature includes a plurality of bleed channels formed in the first seal surface and the second seal surface.

8. The assembly of claim 7 , wherein the seal has a first leg and a second leg that extends from the first leg to form a trough between the first leg and the second leg, the seal is arranged so that the trough is open to the high pressure zone, and both the first leg and the second leg are corrugated to form the plurality of bleed channels.

9. The assembly of claim 6 , wherein the bleed feature includes a plurality of holes formed in the seal.

10. The assembly of claim 9 , wherein the plurality of holes are arranged midway between the first seal surface and the second seal surface.

11. A gas turbine engine assembly comprising
a first component including a panel arranged to separate a high pressure zone from a low pressure zone, a first chamfer surface that extends from a radially-outwardly facing surface of the first component to a first circumferentially-facing side surface of the first component, and a plurality of attachment features that extend radially outward from the radially-outwardly facing surface of the panel of the first component and are configured to couple the first component to a surrounding structure,
a second component including a panel arranged to separate the high pressure zone from the low pressure zone, a second chamfer surface that extends from a radially-outwardly facing surface of the second component to a second circumferentially-facing side surface of the second component, and a plurality of attachment features that extend radially outward from the radially-outwardly facing surface of the panel of the second component and are configured to couple the second component to the surrounding structure, and
a seal arranged in a channel formed by the first chamfer surface and the second chamfer surface between the first component and the second component that opens toward the high pressure zone, the seal having a first seal surface that contacts the first component and a second seal surface that contacts the second component, and the seal shaped to be pushed into contact with the first component and the second component by pressure in the high pressure zone,
wherein the channel extends only partway along an interface between the first component and the second component, and the plurality of attachment features of the first and second components are arranged axially along the channel between a first end of the channel and a second end of the channel spaced axially from the first end, and
wherein the first component includes a plurality of retention features that extend over portions of the channel located between the first e

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Shi Jun
• Freeman Ted J
• Thomas David J

Classifications

• Y02T50/60

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

• F05D2240/55

  Seals · CPC title

• F05D2250/61

  corrugated · CPC title

• F05D2250/11

  triangular · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title