Abstract: A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“CMC”). The vane having an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the outer platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal having an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a base wall define a bathtub seal chamber. The base wall is in contact with the outer platform. The vane is connected to the outer wall. The static structure is received within the bathtub seal chamber. A connection is configured to deliver pressurized air to the bathtub seal chamber. A gas turbine engine is also disclosed.

Abstract: A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the mount structure and formed of ceramic matrix composites (“CMC”). The vane has an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal has an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a bottom wall define a bathtub seal chamber. The bottom wall is in contact with an upper surface of the vane. The vane is connected to the outer wall. Static structure is received within the bathtub seal chamber. A gas turbine engine is also disclosed.

Abstract: A method of forming a vane assembly for a gas turbine engine includes the steps of 1) determining a re-stagger angle for an airfoil on a ceramic matrix composite (“CMC”) vane, 2) determine an adjusted position of a baffle to be inserted within a central chamber in the vane, inserting the baffle into a bathtub seal, and adjusting an upper face of the baffle to an orientation relative to a bathtub seal support face to account for the adjusted position of the baffle and 3) fixing the baffle upper face to the bathtub seal flange support face. A vane assembly and a gas turbine engine are also disclosed.

Abstract: A method of fabricating a ceramic matrix composite component includes fabricating a ceramic preform, the preform comprising a hollow portion with an internal cavity extending along a first axis from a first end to a second end of the hollow portion, supporting the hollow portion with an auxetic mandrel disposed within and the internal cavity and coaxial with the hollow portion, the auxetic mandrel comprising a first mandrel end and a second mandrel end, at least partially densifying the preform with a matrix, and removing the auxetic mandrel from the internal cavity by simultaneously applying a compressive force to each of the first mandrel end and the second mandrel end creating a deformed auxetic mandrel to reduce a cross-sectional profile of the auxetic mandrel along a second axis orthogonal to the first axis, and extracting the deformed auxetic mandrel from the first end of the hollow portion.

Abstract: A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the mount structure and formed of ceramic matrix composites (“CMC”). The vane has an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal has an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a bottom wall define a bathtub seal chamber. The bottom wall is in contact with an upper surface of the vane. The vane is connected to the outer wall. Static structure is received within the bathtub seal chamber. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes first and second CMC vane arc segments arranged about an engine central axis. Each of the CMC vane arc segments has a platform and an airfoil section that extends off of the platform. The platform defines an axially trailing face, an axially leading face that is circumferentially offset from the axially trailing face, and first and second circumferential faces that extend from the axially trailing face to the axially leading face. The first circumferential face of the first CMC vane arc segment interfaces with the second circumferential face of the second CMC vane arc segment. There is at least one friction damper between the first circumferential face of the first CMC vane arc segment and the second circumferential face of the second CMC vane arc segment.

Abstract: A method of forming a vane assembly for a gas turbine engine includes the steps of 1) determining a re-stagger angle for an airfoil on a ceramic matrix composite (“CMC”) vane, 2) determine an adjusted position of a baffle to be inserted within a central chamber in the vane, inserting the baffle into a bathtub seal, and adjusting an upper face of the baffle to an orientation relative to a bathtub seal support face to account for the adjusted position of the baffle and 3) fixing the baffle upper face to the bathtub seal flange support face. A vane assembly and a gas turbine engine are also disclosed.

Abstract: A method is disclosed for a design geometry of a ceramic matrix composite (CMC) vane arc segment that has a platform and an airfoil section that extends off of the platform. The platform defines an axially trailing face, an axially leading face that is circumferentially offset from the axially trailing face, and first and second circumferential faces. In the method, a modal excitation response of the platform is determined based upon an external engine operation excitation frequency. If the modal excitation response is greater than a target modal excitation response, the design geometry of the platform is adjusted to be detuned with the external engine operation excitation frequency by reducing an overhang distance of the platform in which the modal excitation response at the external engine operation excitation frequency is equal to or lower than the target modal excitation response.

Abstract: A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“CMC”). The vane having an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the outer platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal having an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a base wall define a bathtub seal chamber. The base wall is in contact with the outer platform. The vane is connected to the outer wall. The static structure is received within the bathtub seal chamber. A connection is configured to deliver pressurized air to the bathtub seal chamber. A gas turbine engine is also disclosed.

Abstract: A method for processing a CMC airfoil includes nesting an airfoil fiber preform in a cavity of a fixture that has first and second tool segments, closing the fixture by rotating a first tool segment about a hinge, the closing causing the tool segments to clamp on a tail portion of the fiber preform and thereby conform the tail portion to the fixture. While in the fixture, the fiber preform is then partially densified with an interface coating material to form a partially densified fiber preform. While still in the fixture, one or more cooling holes are drilled into the trailing edge of the partially densified fiber preform. After the drilling, the partially densified fiber preform is removed from the fixture and further densified with a ceramic matrix material to form a fully densified CMC airfoil.

Abstract: A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“CMC”). The vane having an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the outer platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal having an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a base wall define a bathtub seal chamber. The base wall is in contact with the outer platform. The vane is connected to the outer wall. The static structure is received within the bathtub seal chamber. A connection is configured to deliver pressurized air to the bathtub seal chamber. A gas turbine engine is also disclosed.

Abstract: A method for processing a CMC airfoil includes nesting an airfoil fiber preform in a cavity of a fixture that has first and second tool segments, closing the fixture by rotating a first tool segment about a hinge, the closing causing the tool segments to clamp on a tail portion of the fiber preform and thereby conform the tail portion to the fixture. While in the fixture, the fiber preform is then partially densified with an interface coating material to form a partially densified fiber preform. While still in the fixture, one or more cooling holes are drilled into the trailing edge of the partially densified fiber preform. After the drilling, the partially densified fiber preform is removed from the fixture and further densified with a ceramic matrix material to form a fully densified CMC airfoil.

Abstract: A method of forming a vane preform includes braiding a sleeve from ceramic fibers, inserting a flared mandrel into the sleeve, the flared mandrel comprising a body region and at least one contoured region, manipulating the sleeve using the flared mandrel to form contours in the sleeve corresponding to the contoured region of the flared mandrel, and laying up at least one ceramic ply with the sleeve to form the vane preform.

Abstract: A vane multiplet includes first and second ceramic matrix composite (CMC) singlet vanes that are arranged circumferentially adjacent each other. Each of the CMC singlet vanes includes an airfoil section and a platform at one end of the airfoil section. The platform defines forward and trailing platform edges and first and second circumferential side edges. A CMC overwrap conjoins the CMC singlet vanes. The CMC overwrap includes fiber plies that are fused to the platforms of the CMC singlet vanes.

Abstract: A vane multiplet includes first and second ceramic matrix composite (CMC) singlet vanes that are arranged circumferentially adjacent each other. Each of the CMC singlet vanes includes an airfoil section and a platform at one end of the airfoil section. The platform defines forward and trailing platform edges and first and second circumferential side edges. A CMC overwrap conjoins the CMC singlet vanes. The CMC overwrap includes fiber plies that are fused to the platforms of the CMC singlet vanes.

Abstract: A method for processing a CMC airfoil includes nesting an airfoil fiber preform in a cavity of a fixture that has first and second tool segments, closing the fixture by rotating a first tool segment about a hinge, the closing causing the tool segments to clamp on a tail portion of the fiber preform and thereby conform the tail portion to the fixture. While in the fixture, the fiber preform is then partially densified with an interface coating material to form a partially densified fiber preform. While still in the fixture, one or more cooling holes are drilled into the trailing edge of the partially densified fiber preform. After the drilling, the partially densified fiber preform is removed from the fixture and further densified with a ceramic matrix material to form a fully densified CMC airfoil.

Abstract: An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.

Abstract: An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.

Abstract: A variable positioner includes a body portion with a cylindrical component, and an axially aligned through hole in the body position. A threading protrudes radially inward from an inner surface of the axially aligned through hole. A first axial end of the variable positioner defines an interface surface for interfacing with a rotor arm.

Abstract: Thermal lifting members for blade outer air seal supports of gas turbine engines include a hollow body defining a thermal cavity therein, at least one inlet fluid connector fluidly connected to the thermal cavity configured to supply hot fluid to the thermal cavity from a fluid source, at least one outlet fluid connector fluidly connected to the thermal cavity configured to allow the hot fluid to exit the thermal cavity, and at least one lifting hook configured to engage with a blade outer air seal support, wherein the thermal lifting member is configured to thermally expand outward when hot fluid is passed through the thermal cavity such that during thermal expansion the at least one lifting hook forces the blade outer air seal support to move outward.