A vane arm assembly for a gas turbine engine includes a vane stem having a circumferential groove axially spaced from an outer end of the vane stem. The assembly also includes a vane arm defining an arm aperture that the vane stem is disposed within. The assembly further includes a mechanical fastener retaining an axial position of the vane arm in the axial direction. The assembly yet further includes a retention clip having a base portion and at least one clip arm, the base portion defining a clip aperture that the vane stem is disposed within, the base portion disposed within the circumferential groove of the vane stem to couple the retention clip to the vane stem, the at least one clip arm including a retention member engaged with the vane arm to provide redundant axial retention of the vane arm.

Disclosed herein is a gas turbine blade. The gas turbine blade includes a turbine blade (33) provided in a turbine, and film cooling elements (100), each including a cooling channel (110) for cooling of the turbine blade (33), an outlet (120) through which cooling air is discharged, and a plurality of ribs (130), wherein the outlet (120) extends from a longitudinally extended end of the cooling channel (110) to an outer surface of the turbine blade (33) and has a width increased from one end of the cooling channel (110) to the outer surface of the turbine blade (33), and the ribs (130) face each other on inner walls of the outlet (120).

An electrode for electrical discharge machining (EDM) may comprise a diffuser portion and a tapered portion defining the tip of the electrode. A method for forming a film cooling hole may comprise moving a tool with respect to a film cooled gaspath component, forming a diffuser of the film cooling hole in response to the moving, and forming a tapered surface between a metering section and the diffuser of the film cooling hole.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the TBC sheet spall includes forming a TBC over a selected portion of the exterior surface of the body. The TBC includes a plurality of segments in a cellular pattern. Each segment is defined by one or more slots in the TBC, and each segment has a predefined area such that the extent of the TBC sheet spall is limited by the predefined area of each of the plurality of segments that constitute the TBC sheet spall.

An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

An apparatus and method relating to an airfoil for a turbine engine and cooling channels within the airfoil. The airfoil includes an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. Further, the airfoil includes ribs located within the interior and a flow enhancer extending between the ribs.

A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

A gas turbine exhaust casing includes a tubular casing wall, a bearing box housed in the casing wall, a diffuser portion forming an annular exhaust gas flow passage between the casing wall and the bearing box, a plurality of struts disposed at intervals in a circumferential direction of the casing wall, and coupling the casing wall and the bearing box, and a plurality of fastening bolts disposed on the casing wall. The casing wall includes an upper half casing forming an upper half of the casing wall and a lower half casing forming a lower half of the casing wall. The plurality of fastening bolts fasten the upper half casing and the lower half casing. The plurality of struts include a penetrated strut which has an end penetrated by at least one fastening bolt of the plurality of fastening bolts.