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US 2024/0110488 A1Published application
Blade outer air seal with compliant seal
AssigneeRtx Corporation
InventorsPaul M. Lutjen, Daniel S. Rogers, Timothy J. Harding, James E. Weisheit, Morely S. Sherman, Mikayla M. Rogers, Marshall F. Thayer, Joseph Micucci
Life of this patent
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Abstract
A gas turbine engine includes a turbine section that has a ceramic matrix composite body that defines a core gaspath side that a row of blades, a forward end, an aft end, and circumferential sides. The forward end abuts at least one vane of a first row of vanes, and the aft end including a seal channel. A compliant seal is disposed in the seal channel and seals against at least one vane of a second row of vanes.
Claims15
A gas turbine engine comprising:
- a turbine section including,
- a first row of vanes disposed about an engine axis, a second row of vanes axially spaced from the first row of vanes, and a row of blades axially between the first row of vanes and the second row of vanes;
- and
- a row of blade outer air seals axially between the first row of vanes and the second row of vanes and situated radially outwardly of the row of blades, each blade outer air seal including,
- a ceramic matrix composite body defining a core gaspath side facing the row of blades, a forward end, an aft end, and circumferential sides, the forward end abutting at least one of the vanes of the first row of vanes, the aft end including a seal channel, and
- a compliant seal disposed in the seal channel and sealing against at least one of the vanes of the second row of vanes.
3 more elements
A blade outer air seal comprising:
- a ceramic matrix composite body defining a core gaspath side, a forward end, an aft end, and circumferential sides, the aft end including a seal channel;
- and
- a compliant seal disposed in the seal channel.
Dependencies are inferred from the claim text.