Abstract: A gas turbine engine including a core having a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via the core flow path. An assembly is disposed within the gas turbine engine and includes a first part connected to a second part via a radial stack joint. The first part includes a radially inward facing surface contacting a corresponding radially outward facing surface of the second part. A fastener protrudes through the first part and the second part and is configured to maintain the relative positions of the first part and the second part. A channel is disposed on at least one of the radially inward facing surfaces and is positioned between the fastener and a circumferential edge of the first part. The channel is connected to at least one cooling air source.

Abstract: A gas turbine engine including a core having a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via the core flow path. An assembly is disposed within the gas turbine engine and includes a first part connected to a second part via a radial stack joint. The first part includes a radially inward facing surface contacting a corresponding radially outward facing surface of the second part. A fastener protrudes through the first part and the second part and is configured to maintain the relative positions of the first part and the second part. A channel is disposed on at least one of the radially inward facing surfaces and is positioned between the fastener and a circumferential edge of the first part. The channel is connected to at least one cooling air source.

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: An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.

Abstract: An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.

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.