Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.

Abstract: A method of assembling a ceramic matrix composite (CMC) component is provided. The method includes assessing which portions of the CMC component require relatively high-temperature capability and which portions require at least one of strength, thickness and increased thermal conductivity, making the portions that require the relatively high temperature capability with chemical vapor infiltration (CVI), making the portions that require the at least one of strength, thickness and increased thermal conductivity with melt infiltration (MI) and combining the portions that require the relatively high temperature capability with the CVI and the portions that require the at least one of strength, thickness and increased thermal conductivity with the MI.

Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.

Abstract: An airfoil assembly includes an airfoil fairing, a spar, a seal plate, and a seal. The airfoil fairing has a fairing platform and a hollow airfoil section that extends from the fairing platform. The spar has a spar leg that extends in the hollow airfoil section. The spar leg defines a spar leg periphery. The seal plate is secured with the fairing platform. The seal plate has an opening, and the opening has an opening periphery that is complementary to the spar leg periphery. The spar leg extends through the opening. The seal is between the seal plate and the spar leg. The seal seals around the spar leg periphery.

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 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: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

Abstract: An airfoil fairing includes an airfoil section that is formed of a fiber-reinforced composite wall. The airfoil section has first and second radial ends, pressure and suction sides, leading and trailing ends that join the pressure and suction sides, an internal cavity, and a rib that extends radially in the internal cavity. The rib has a radial rib end at the first radial end of the airfoil section and extends across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side. The rib defines at the radial end first and second shoulders. The first and second shoulders define a radial notch there between.

Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.

Abstract: An airfoil fairing includes an airfoil section that is formed of a fiber-reinforced composite wall. The airfoil section has first and second radial ends, pressure and suction sides, leading and trailing ends that join the pressure and suction sides, an internal cavity, and a rib that extends radially in the internal cavity. The rib has a radial rib end at the first radial end of the airfoil section and extends across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side. The rib defines at the radial end first and second shoulders. The first and second shoulders define a radial notch there between.

Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.

Abstract: An airfoil piece includes at least one inner ceramic matrix composite ply which defines an internal cavity of an airfoil section and first and second collar projections. At least one inner ceramic matrix composite ply is continuous through the airfoil section and first and second collar projections, first and second platforms at the first and second ends of the airfoil section. The first and second collar projections extend radially past the first and second platforms, respectively. A vane for a gas turbine engine and a method of assembling a vane are also disclosed.

Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and an airfoil section that extends there from. The fairing platform defines a gaspath side and a non-gaspath side and includes a flange that projects from the non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite that includes a wishbone-shaped fiber layer structure that has first and second arms that converge and merge into a single leg. The first and second arms are formed of fiber plies comprised of a network of fiber tows. The single leg comprises fiber tows from each of the fiber plies of the first and second arms. The fiber tows of the first arm are interwoven in the single leg with the fiber tows of the second arm. The first arm, the second arm, or the single leg forms at least a portion of the flange.

Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a hollow spar leg that extends from the spar platform and through the hollow airfoil section. The hollow spar leg has an internal passage for receiving cool air there through, a clevis mount, and a pin fairing. The clevis mount is distal from the spar platform and protrudes from the second fairing platform. The clevis mount includes first and second prongs with aligned holes. A pin extends through the aligned holes. The pin fairing extends over the pin between the first and second prongs for guiding the cooling air around the pin. There is a support platform adjacent the second fairing platform. The pin locks the support platform to the spar leg.

Abstract: A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.

Abstract: An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

Abstract: An airfoil assembly includes an airfoil. The airfoil has first and second platforms and an airfoil between the first and second platforms. A support ring is configured to retain the first platform. The support ring has a lip which extends radially inward from the support ring. The lip is configured to engage an axial face of the first platform. The lip has a primary retention feature and a secondary retention feature. The primary and secondary retention features are configured to retain the first face of the first platform with respect to the annular ring. A support structure for an airfoil and a method of retaining an airfoil assembly are also disclosed.