Abstract: A gas turbine engine includes a rotor carrying a blade, a ceramic vane adjacent the blade, a seal carried on the rotor adjacent the tip of the ceramic vane, and a cooling passage circuit extending through the blade, the seal, and the ceramic vane. The cooling passage circuit is configured to provide cooling air into the blade, then from the blade into the seal, and then from the seal into the ceramic vane.

Abstract: A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall including adjacent bounding pedestals that extend from an external wall surface to establish a cooling passage, and including a common pedestal situated between the adjacent bounding pedestals to establish a first branched section and a second branched section of the cooling passage that join together at a merged section of the cooling passage. A method of fabricating a gas turbine engine component is also disclosed.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a fan including a rotor hub rotatable about an engine longitudinal axis and an array of fan blades, a geared architecture, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the fan through the geared architecture. Each fan blade of the array of fan blades includes pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, and facing pressure and suction sides of adjacent fan blades define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent fan blades.