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US 10,704,404 B2Granted
Seals for a gas turbine engine assembly
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsJun Shi, Ted J. Freeman, David J. Thomas
Life of this patent
Estimating the term…
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.
Claims25
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.
4 more elements
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 end and the second end of the channel to block the seal from radial movement out of the channel and the second component includes a plurality of retention features that extend over portions of the channel located between the first end and the second end of the channel to block the seal from radial movement out of the channel.
2 more elements
A gas turbine engine assembly comprising
- a first component including a panel arranged to separate a first pressure zone from a second pressure zone and a plurality of attachment features that extend radially outward from the panel of the first component and are configured to couple the panel of the first component to a surrounding structure, the panel of the first component formed to include a first chamfer surface that extends from a radially-facing surface of the first component to a first circumferentially-facing side surface of the first component,
- a second component including a panel arranged to separate the first pressure zone from the second pressure zone and a plurality of hangers that extend radially outward from the panel of the second component and are configured to couple the panel of the second component to the surrounding structure, the panel of the second component formed to include a second chamfer surface that extends from a radially-facing surface of the second component 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 first 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 channel extends only partway along an interface between the first component and the second component, and the plurality of attachment features 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.
1 more element
Dependencies are inferred from the claim text.