Abstract: Composite components having structurally reinforced contact interfaces are provided. In one example, the component can include an inner laminate formed of one or more inner plies having reinforcement fibers oriented along a reference direction within a matrix material. The component can also include an interface laminated positioned on the inner laminate along at least a portion of a contact surface of the component. The interface laminate is formed of one or more interface plies having reinforcement fibers oriented along a direction offset from the reference direction within a matrix material. Methods for fabricating such components are also provided.

Abstract: Composite components having structurally reinforced contact interfaces are provided. In one example, the component can include an inner laminate formed of one or more inner plies having reinforcement fibers oriented along a reference direction within a matrix material. The component can also include an interface laminated positioned on the inner laminate along at least a portion of a contact surface of the component. The interface laminate is formed of one or more interface plies having reinforcement fibers oriented along a direction offset from the reference direction within a matrix material. Methods for fabricating such components are also provided.

Abstract: Various embodiments are provided which provide an architecture for CMC plies to improve strength of damper retaining features of a turbine blade assembly. The plies (62) may also be integrated with the platform structure (50) to strength the CMC blade assembly.

Abstract: Various embodiments are provided which provide an architecture for CMC plies to improve strength of damper retaining features of a turbine blade assembly. The plies (62) may also be integrated with the platform structure (50) to strength the CMC blade assembly.

Abstract: A process for producing components containing ceramic materials. The process entails forming a first region of a component with plies containing a reinforcement material in a precursor of a ceramic material. The plies include at least a first set of plies between at least second and third sets of plies. Distal portions of the second and third sets of plies are then folded away from the first set of plies so that they are oriented transverse to the first set of plies. A fourth set of plies is then interleaved among the folded distal portions of the second and third sets of plies.

Abstract: Robust turbine blade designs that minimize damage to turbine blades during a tip rub event, guard against further tip recession, and improve the resiliency of turbine blades 24 are provided. This may be achieved through various blade tip 12 designs, such as a recessed tip 28 or a protruding tip 98. It may also be achieved by providing the blade tip, shroud, or both with an environmental barrier coating (EBC) 22 having an abradable or abrasive layer.

Abstract: A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material.

Abstract: A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.

Abstract: A damper system and a turbine are provided. The damper system includes a plurality of CMC blades. Each CMC blade has a first member of a tip shroud, the first member opposite a second member of the tip shroud, a radial flange extending between the first member and the second member of the tip shroud, and at least one aperture in the radial flange for receiving a damping member, the dampening member joining and dampening adjacent CMC blades. The turbine includes a plurality of turbine blade tip shroud segments, each tip shroud segment having a first surface that cooperates with the first surface in an adjacent tip shroud segment to form a first opening, each tip shroud segment having a first receiving surface. The turbine includes a damper member that abuts the first receiving surface of each tip shroud segment.

Abstract: A process for producing components containing ceramic materials. The process entails forming a first region of a component with plies containing a reinforcement material in a precursor of a ceramic material. The plies include at least a first set of plies between at least second and third sets of plies. Distal portions of the second and third sets of plies are then folded away from the first set of plies so that they are oriented transverse to the first set of plies. A fourth set of plies is then interleaved among the folded distal portions of the second and third sets of plies.

Abstract: A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material.

Abstract: A hybrid turbine airfoil component containing a ceramic material, in which detailed features of the component are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the component. The component includes a first subcomponent formed of a ceramic-based material, and a second subcomponent formed of a metallic material. The first subcomponent has an airfoil portion and a nub, and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent includes a blade tip shroud portion having at least one off-axis geometric feature that results in the second subcomponent having a more complex geometry than the first subcomponent.