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US 11,078,802 B2Granted
Turbine engine assembly with ceramic matrix composite components and end face seals
AssigneeROLLS-ROYCE plc
InventorsAnthony G. Razzell, Michael J. Whittle, Steven Hillier
Life of this patent
Estimating the term…
Abstract
A gas turbine engine assembly includes a first component, a second component, and a seal. The first component is spaced apart from the second component to form a gap between the first component and the second component. The seal is configured to block gases from flowing in the gap between the first component and the second component.
Claims17
A gas turbine engine assembly comprising
- a first component comprising ceramic matrix composite materials, the first component having a first radial outer surface that extends circumferentially partway around an axis and a first circumferential end face that extends radially inward from the first radial outer surface toward the axis,
- a second component comprising ceramic matrix composite, the second component having a second radial outer surface that extends circumferentially partway around the axis and a second circumferential end face that extends radially inward from the second radial outer surface toward the axis, and the second circumferential end face facing being spaced apart circumferentially from the first circumferential end face of the first component to define a gap therebetween, and
- a seal configured to block gases from flowing axially and radially between the first component and the second component, the seal includes an outer segment and a radial segment, the outer segment extends circumferentially along the first radial outer surface across the gap and along the second radial outer surface to allow for changes in a size of the gap due to thermal growth of the gas turbine engine assembly and the radial segment extends radially inward from the outer segment into the gap,
- wherein the first component includes a radial innermost surface that is spaced apart radially from the first radial outer surface toward the axis, the seal includes an outer end and an inner end that is spaced apart radially from the outer end, and the inner end is radially flush with the radial innermost surface of the first component.
1 more element
A gas turbine engine assembly comprising
- a first component comprising ceramic matrix composite materials, the first component extends circumferentially between a first end and second end thereof relative to an axis,
- a second component comprising ceramic matrix composite materials, the second component extends circumferentially between a first end and second end thereof relative to the axis, and the first end of the second component is spaced apart circumferentially from the second end of the first component to define a gap therebetween, and
- a seal configured to block gases from flowing between the first component and the second component, the seal includes an outer segment, a first leg segment, and a second leg segment, the outer segment extends circumferentially over the first radial outer surface, across the gap, and over the second radial outer surface, the first leg segment extends radially inward from the outer segment toward the axis and engages the first component, the second leg segment is spaced apart circumferentially from the first leg segment, and the second leg segment extends radially inward from the outer segment toward the axis and engages the second component,
- wherein the first leg segment is formed to include a first channel that extends radially outward into the first leg segment, the second leg segment is formed to include a second channel that extends radially outward into the second leg segment, the first component covers the first channel, and the second component covers the second channel.
1 more element
A gas turbine engine assembly comprising
- a first component comprising ceramic matrix composite materials, the first component extends circumferentially between a first end and second end thereof relative to an axis,
- a second component comprising ceramic matrix composite materials, the second component extends circumferentially between a first end and second end thereof relative to the axis, and the first end of the second component is spaced apart circumferentially from the second end of the first component to define a gap therebetween, and
- a seal configured to block gases from flowing between the first component and the second component, the seal includes an outer segment, a first leg segment, and a second leg segment, the outer segment extends circumferentially over the first radial outer surface, across the gap, and over the second radial outer surface, the first leg segment extends radially inward from the outer segment toward the axis and engages the first component, the second leg segment is spaced apart circumferentially from the first leg segment, and the second leg segment extends radially inward from the outer segment toward the axis and engages the second component,
- wherein the first leg segment includes a mating surface that engages the first component, the second leg segment includes a mating surface that engages the second component, and the mating surface of the first leg segment and the mating surface of the second leg segment are curvilinear to allow the seal to remain engaged with the first and second components in response to relative radially radial movement between the first component and the second component.
1 more element
Dependencies are inferred from the claim text.