Abstract: A vane assembly includes an airfoil extending from a platform. The platform has a flange that extends radially outward and circumferentially across the platform. A vane cover is arranged adjacent the platform that defines an impingement gap between the platform and the vane cover. The vane cover has a wall that defines a slot. The flange is arranged at least partially within the slot.

Abstract: A vane system includes a plurality of vane assemblies and a continuous support ring. The vane assemblies are arranged circumferentially about an axis and each include a hollow airfoil fairing and a spar. The spar has a spar flange and a spar leg extending radially inwardly from the spar flange and through the hollow airfoil fairing. The continuous support ring has radially inner and outer sides and defines a circumferential row of through-holes between the radially inner and outer sides. The spar legs extend through the through-holes and the spar flanges are affixed at the radially outer side of the continuous support ring.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate and a backing plate that extend circumferentially about an assembly axis. The backing plate includes a main body and a first set of abutments that extend outwardly from the main body to abut the first side plate. A first set of pockets are established between adjacent abutments of the first set of abutments. A first brush seal is between the first side plate and the backing plate. Sections of the first brush seal received in respective pockets of the first set of pockets are dimensioned to join together to establish a first sealing relationship with a first gas turbine engine component. A method of assembly is also disclosed.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate, a second side plate and a backing plate that extend circumferentially about an assembly axis. A first brush seal and a second brush seal are positioned on opposite sides of the backing plate such that the first brush seal is between the first side plate and the backing plate and such that the second brush seal is between the second side plate and the backing plate. The first brush seal is dimensioned to establish a first sealing relationship with a first gas turbine engine component. The second brush seal is dimensioned to establish a second sealing relationship with a second gas turbine engine component. A method of assembly is also disclosed.

Abstract: A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.

Abstract: A vane arc segment includes an airfoil fairing that has a platform and an airfoil section that extends therefrom. The platform defines periphery edge faces, a gaspath face, and a non-gaspath face. The platform has a flange that projects radially from the non-gaspath face. The flange defines a forward flange face, an aft flange face, and a radial flange face. The flange has an end portion adjacent one of the periphery edges. The end portion includes a step that defines a radial step face that is radially intermediate the radial flange face and the non-gaspath face.

Abstract: A pin assembly according to an exemplary embodiment of this disclosure, among other possible things includes a spring housing, a spring situated in the spring housing, a pin having a first end configured to be received in the spring housing and to engage the spring, and a boot configured to receive a second end of the pin. The boot is configured to span a gap between first and second adjacent components and configured to transfer a spring force from the spring to the first and second adjacent components. A vane assembly and a method of assembling a vane assembly are also disclosed.

Abstract: A vane arc segment includes a hollow ceramic airfoil section that has walls that define an internal cavity, a trailing edge, a leading edge, a pressure side, and a suction side. A structural spar piece supports the hollow ceramic airfoil section. The spar piece includes a first spar platform, a hollow leg that has a proximal end at the spar platform and an opposed distal end. The hollow leg extends into the internal cavity of the hollow ceramic airfoil section and has an outer surface with raised bearing pads. Multiple ones of the bearing pads contact the walls of the hollow ceramic airfoil section to support the hollow ceramic airfoil section. A second spar platform is secured with the distal end of the leg.

Abstract: An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.

Abstract: A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.

Abstract: A vane arc segment includes an airfoil wall that defines first and second fairing platforms and a hollow airfoil section. A spar leg extends through the hollow airfoil section and has an end portion that protrudes from the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. There is a support platform adjacent the second airfoil fairing and a second gap therebetween. A baffle is disposed in the first gap and is spaced apart from the airfoil wall and the spar leg so as to divide the first gap into a plenum space between the spar leg and the baffle and an impingement space between the baffle and the airfoil wall. A seal is disposed between the airfoil wall and the spar leg to seal the impingement space from the second gap.

Abstract: A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.

Abstract: A vane arc segment includes a hollow ceramic airfoil section that has walls that define an internal cavity, a trailing edge, a leading edge, a pressure side, and a suction side. A structural spar piece supports the hollow ceramic airfoil section. The spar piece includes a first spar platform, a hollow leg that has a proximal end at the spar platform and an opposed distal end. The hollow leg extends into the internal cavity of the hollow ceramic airfoil section and has an outer surface with raised bearing pads. Multiple ones of the bearing pads contact the walls of the hollow ceramic airfoil section to support the hollow ceramic airfoil section. A second spar platform is secured with the distal end of the leg.

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.

Abstract: A vane for a gas turbine engine includes an airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side that bound an internal cavity. The airfoil section has associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure. The airfoil wall has a single rib connecting the pressure side and the suction side. The single rib is aligned with the aerodynamic load vector.

Abstract: A pin assembly according to an exemplary embodiment of this disclosure, among other possible things includes a spring housing, a spring situated in the spring housing, a pin having a first end configured to be received in the spring housing and to engage the spring, and a boot configured to receive a second end of the pin. The boot is configured to span a gap between first and second adjacent components and configured to transfer a spring force from the spring to the first and second adjacent components. A vane assembly and a method of assembling a vane assembly are also disclosed.

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar piece includes a radial opening defined by first and second opposed faces. The radial opening is configured to receive the collar projection, and a groove in the spar platform opening to the first face. A seal is situated in the groove. The seal seals against the collar projection. A gas turbine engine and a method of assembling a vane are also disclosed.

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar piece includes a radial opening defined by first and second opposed faces. The radial opening is configured to receive the collar projection, and a groove in the spar platform opening to the first face. A seal is situated in the groove. The seal seals against the collar projection. A gas turbine engine and a method of assembling a vane are also disclosed.