Lamellate CMC structure with interlock to metallic support structure
First Claim
1. A component for a gas turbine engine comprising:
- a lamellate stack, each lamella of the stack comprising a first surface exposed to a hot combustion gas flow and a second surface comprising an interlock feature; and
a support structure comprising at least one interlock feature cooperating with each respective lamella interlock feature to transmit forces between respective opposed mating surfaces to support the lamellae while accommodating differential thermal expansion between the support structure and the lamellate stack.
3 Assignments
0 Petitions
Accused Products
Abstract
A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperating interlock features (30, 32) formed on the lamella and on the support structure respectively. Mating load-transferring surfaces (34, 36) of the interlock features are disposed in a plane (44) oblique to local axes of thermal growth (38, 40) in order to accommodate differential thermal expansion there between with delta alpha zero expansion (DAZE). Reinforcing fibers (62) within the CMC material may be oriented in a direction optimized to resist forces being transferred through the interlock features. Individual lamellae may all have the same structure or different interlock feature shapes and/or locations may be used in different groups of the lamellae. Applications for this invention include an airfoil assembly (10) and a ring segment assembly (82).
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Citations
29 Claims
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1. A component for a gas turbine engine comprising:
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a lamellate stack, each lamella of the stack comprising a first surface exposed to a hot combustion gas flow and a second surface comprising an interlock feature; and
a support structure comprising at least one interlock feature cooperating with each respective lamella interlock feature to transmit forces between respective opposed mating surfaces to support the lamellae while accommodating differential thermal expansion between the support structure and the lamellate stack. - View Dependent Claims (2, 3, 4, 5)
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6. An airfoil assembly comprising:
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a stacked plurality of lamellae, each lamella comprising an outer surface collectively defining an airfoil shape, and each lamella comprising an inner surface collectively defining a core;
a support structure disposed in the core and comprising at least one interlock feature;
each lamella comprising an interlock feature cooperatively interfaced with a respective support structure interlock feature, the cooperating interlock features effective to transmit forces there between to support the lamellae relative to the support structure while accommodating differential thermal expansion there between. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24)
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25. A ring segment assembly for a gas turbine engine comprising:
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a first carrier portion comprising an interlock feature;
a second carrier portion removably attached to the first carrier portion and comprising an interlock feature;
a stacked plurality of lamellae each comprising a wear surface and an opposed surface defining an interlock feature cooperatively interfaced with the interlock feature of at least one of the first carrier portion and the second carrier portion, the cooperating interlock features effective to support the stacked lamellae relative to the attached carrier portions while accommodating differential thermal growth there between. - View Dependent Claims (26, 27, 28, 29)
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Specification