A component for a fluid flow engine, such as a gas turbine, includes a first side, e.g. a top side and a second side, e.g. a bottom side, wherein the component further includes a mesh of interior channels for guiding a fluid through the component, wherein a fluid inlet being in fluid communication with channels of the mesh is provided at the first side and at the second side, respectively, and wherein the mesh is further arranged and configured such that channels originating from the fluid inlet of the first side and channels originating from the fluid inlet of the second side are interlaced such that a fluid entering the component is at least partly guided according to opposing directions in the mesh.

A component for a fluid flow engine, such as a gas turbine, includes a first side, e.g. a top side and a second side, e.g. a bottom side, wherein the component further includes a mesh of interior channels for guiding a fluid through the component, wherein a fluid inlet being in fluid communication with channels of the mesh is provided at the first side and at the second side, respectively, and wherein the mesh is further arranged and configured such that channels originating from the fluid inlet of the first side and channels originating from the fluid inlet of the second side are interlaced such that a fluid entering the component is at least partly guided according to opposing directions in the mesh.

Tail cone assemblies for gas turbine engines are described. The tail cone assemblies include a generator housing having an electrical connector, the generator housing defining a longitudinal axis. A first casing is arranged radially outward from the generator housing relative to the longitudinal axis and a second casing arranged radially outward from the first casing relative to the longitudinal axis. A hollow strut extends radially between the first casing and the second casing and defining an interior cavity, the hollow strut located circumferentially relative to the longitudinal axis at a location radially aligned with the electrical connector of the generator housing. An electrical conductor is arranged within the interior cavity of the hollow strut and an adapter is configured to electrically connect the electrical conductor with the electrical conductor.

A flex seal assembly includes a plurality of duct segments configured to be disposed about a joint between a turbine of a turbine system and a diffuser of the turbine system. The plurality of duct segments includes a groove configured to extend circumferentially around the joint. Additionally, the plurality of duct segments includes a first duct segment of the plurality of duct segments and a second duct segment of the plurality of duct segments. The second duct segment includes a drain. Furthermore, the plurality of duct segments include insulation disposed within the groove of the plurality of duct segments.

A flex seal assembly includes a plurality of duct segments configured to be disposed about a joint between a turbine of a turbine system and a diffuser of the turbine system. The plurality of duct segments includes a groove configured to extend circumferentially around the joint. Additionally, the plurality of duct segments includes a first duct segment of the plurality of duct segments and a second duct segment of the plurality of duct segments. The second duct segment includes a drain. Furthermore, the plurality of duct segments include insulation disposed within the groove of the plurality of duct segments.

A gas turbine engine, having an engine central longitudinal axis, includes at least one of a vane support, a vane stage, a blade outer air seal support, and a blade outer air seal. At least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal is rotatable about the engine central longitudinal axis. The gas turbine engine may further include a drive system configured to rotate at least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal about the engine central longitudinal axis.

A gas turbine engine, having an engine central longitudinal axis, includes at least one of a vane support, a vane stage, a blade outer air seal support, and a blade outer air seal. At least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal is rotatable about the engine central longitudinal axis. The gas turbine engine may further include a drive system configured to rotate at least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal about the engine central longitudinal axis.

A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly.

A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly.

A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.