Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

Abstract: A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.

Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.

Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil.

Abstract: Component for gas turbine engines are described. The components include an airfoil body having leading and trailing edges and pressure and suction sides. The airfoil has a leading edge cavity located proximate the leading edge defined between the leading edge and a separator rib and between the pressure side and the suction side. An insert member is installed within the leading edge cavity. The insert member has one or more metering flow apertures at an aft end and one or more impingement apertures at a forward end and at least one axially extending rib along an exterior surface thereof. At least one axial extending flow channel passage is defined along the axial extending rib between an exterior of the insert member and an interior of the airfoil body. Air flow through the metering flow apertures flows into the axial extending flow channel passage and flows forward toward the leading edge.

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: 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: Airfoil assemblies for gas turbine engines are described. The airfoil assemblies include an airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil body extending in a radial direction between a first end and a second end, wherein the airfoil defines an internal cavity bounded by interior surfaces of the airfoil body, the airfoil body formed from a high-temperature-material material and a metallic insert member installed within the internal cavity. One or more radially extending ribs are arranged on an exterior surface of the metallic insert member and defining one or more radially extending passages between the exterior surface of the metallic insert member and the interior surface of the airfoil body.

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: An example airfoil vane according to the present disclosure includes an airfoil section including an outer wall that defines an internal cavity, and an insert situated in the internal cavity. A space is defined between the insert and the airfoil outer wall, the insert including an insert wall. A plurality of standoff features extend from the insert wall into the space and contact the airfoil outer wall at a contact area, whereby the standoff features are configured to block airflow in the space at the contact area and redirect the airflow to gaps between the standoff features. A gas turbine engine with the example airfoil vane and a method of assembling an airfoil vane are also disclosed.

Abstract: An airfoil assembly includes first and second ceramic airfoil pieces that each have first and second platforms and a hollow airfoil section that connects the first and second platforms. First and second spars extend through, respectively, the hollow airfoil sections. A seal has a seal body that defines at least one orifice and a seal portion. The first spar extends through one of the at least one orifices and the seal portion bridges a mate face between the first platforms of the first and second ceramic airfoil pieces.

Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.

Abstract: A gas turbine engine airfoil includes an airfoil section that has an airfoil wall and a rib that are formed of a ceramic matrix composite. The airfoil wall circumscribes an internal cavity for receiving cooling air. The airfoil wall defines leading and trailing ends and first and second sides that join the leading and trailing ends. The rib connects the first and second sides. A metallic shield is disposed in the internal cavity and at least partially encloses the rib to shield the rib from the cooling air.

Abstract: An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.

Abstract: An example airfoil vane according to the present disclosure includes an airfoil section including an outer wall that defines an internal cavity, and an insert situated in the internal cavity. A space is defined between the insert and the airfoil outer wall, the insert including an insert wall. A plurality of standoff features extend from the insert wall into the space and contact the airfoil outer wall at a contact area, whereby the standoff features are configured to block airflow in the space at the contact area and redirect the airflow to gaps between the standoff features. A gas turbine engine with the example airfoil vane and a method of assembling an airfoil vane are also disclosed.

Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.

Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil.

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 includes a continuous airfoil piece that is formed of a laminated ceramic matrix composite. The continuous airfoil piece defines a platform and an airfoil section adjacent the platform. The airfoil section includes at least one internal passage, an airfoil wall that has an interior surface that borders the internal passage, an exterior, combustion gaspath surface, and a plurality of cooling holes. Each cooling hole spans between first and second hole ends. The first hole end opens at the interior surface to the internal passage and the second hole end opens at the exterior surface.