A turbine blade including a root, a vane extending in a spanwise direction, ending at a tip and including a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, the vane further including at least one upstream duct configured to collect air at the root to cool the leading edge, discharging the air through holes passing through the wall of the leading edge; at least one downstream duct separate from the upstream duct and configured to collect air at the root to cool the trailing edge, discharging the air through holes passing through the pressure wall upstream from the trailing edge; an inner side cavity running along the pressure-side wall to form a heat shield insulating the downstream duct.

An assembly for a turbine engine or turbine engine test bed, including a hub defined about a longitudinal axis, a blade, including a blade root, extending in a radial direction to the longitudinal axis, the hub including a recess capable of receiving the blade root by insertion in the radial direction, wherein the recess includes a groove, the blade root including a groove, so that the two grooves are facing each other when the blade root is inserted into the recess, the assembly further includes a seal located in the two grooves.

Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.

A compressor aerofoil rotor blade for a turbine engine includes: a root portion spaced apart from a tip portion by a main body portion. The main body portion is defined by a suction surface wall having a suction surface and a pressure surface wall having a pressure surface. The suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge. The tip portion comprises a shoulder provided on the pressure surface wall. A tip wall extends from the aerofoil leading edge to the aerofoil trailing edge. A transition region of the pressure surface wall tapers from the shoulder in a direction towards the tip wall. The tip wall includes a squealer defined by a first tip wall region which extends from the trailing edge to a winglet.

Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

A variable nozzle unit is used in a turbine having a gas inflow passage which is sandwiched between a first flow passage wall surface and a second flow passage wall surface facing each other and through which a gas flowing from a scroll flow passage into a turbine impeller flows. The variable nozzle unit includes nozzle vanes, each of which is rotatably supported on both sides thereof by the first flow passage wall surface side and the second flow passage wall surface side and pivots about a pivotal axis parallel to the rotational axis of the turbine impeller in the gas inflow passage. An end face of the nozzle vane is formed with a cut face that is located closer to a leading edge than the pivotal axis, is cut out such that a gap between the cut face and the second flow passage wall surface is greater than other regions, and intersects the leading edge.

A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also includes a plurality of vanes circumferentially spaced from each other and operatively coupled to the radially outer wall of the exhaust flow path, each of the plurality of vanes extending only partially toward the inner hub and terminating at an inner end of the vanes, the inner end defining an open portion.

A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.

A gas turbine engine includes a compressor section and a turbine section. The turbine section has at least one turbine rotor that has a radially extending turbine blade and is rotatable about an axis of rotation and at least one turbine vane. A blade outer air seal is positioned radially outwardly of a radially outer tip of the turbine blade. A structure mounts the blade outer air seal and provides a platform of at least one turbine vane.

A stator vane is comprised of: an airfoil section elongated in a radial direction relative to an axis; an outer band section continuous to an outer end of the airfoil section and bent in a circumferential direction relative to the axis; a first hook section continuous to a leading end in the axial direction of the outer band section and bent outward in the radial direction; a second hook section continuous to a trailing end in the axial direction of the outer band section and bent outward in the radial direction; an inner band section continuous to an inner end of the airfoil section and bent in the circumferential direction; a flange section continuous to an end in the axial direction of the inner band section and bent inward in the radial direction; and a reinforcement fiber fabric continuous throughout these sections and unitized with a ceramic.