A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

A structure for improving performance of cooling a blade of a gas turbine is provided in which interaction vortexes are generated between working fluid flowing along a surface of the blade and cooling fluid discharged onto the surface from an internal flow passage of the blade. The blade includes a surface structure formed by a gas hole having an outlet communicating with the surface of the blade to discharge the cooling fluid; and a vortex relief generator disposed so as to protrude from an inner periphery of the outlet and configured to generate counter vortexes having directionality opposite to the interaction vortexes so that the interaction vortexes are relieved by collision with the counter vortexes. The vortex relief generator includes a pair of opposing fins disposed in a path of the cooling fluid, each of which has a first surface to change a flow direction of the cooling fluid.

A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.

An assembly comprising a lubricating wheel and lubricant nozzles for a planetary gear speed reducer of a turbomachine, the wheel having a lubricator configured to supply lubricant to the nozzles and the bearings of the planetary carriers of the reducer, the wheel being intended to be mounted coaxially on an annular wall of an axis of rotation X of a planetary carrier of the reducer, the wheel having a bearing and attachment surface on the annular wall of the planetary carrier, the lubricant nozzles being distributed around the axis and each having a generally elongated shape, the nozzles having first longitudinal ends for fluidly connecting to the lubricator of the wheel, wherein the first ends of the nozzles being configured to be attached to the wheel before mounting the wheel on the annular wall of the planetary carrier.

An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a blade extending between the root and tip and extending between the leading edge and trailing edge. The blade includes a pressure side and a suction side defining a thickness therebetween at each point along the span. The blade defines a first chord reduction on at least one of the leading edge or trailing edge along a first portion of the span. Further, the blade defines a frangible line extending from the first chord reduction at least partially along the chord at a point along the span within the first portion of the span.

An air cooled component for a gas turbine engine including a first wall and a second wall having opposing inner surfaces to define a gap therebetween, and a lattice of intersecting elongate ribs extending longitudinally along the first and second walls and transversely between the inner surfaces of the first and second walls to provide a plurality of cells. One or more portions of the ribs include an aperture to provide a flow path between adjacent cells so that the cells are in fluid communication.

A turbine blade is provided. The turbine blade may include: a cooling passage configured to be defined by a partition wall which partitions an internal area of the turbine blade; and an inlet passage extending from a root part of the turbine blade toward a platform part of the turbine blade and configured to supply cooling air into the cooling passage, wherein an inclined part having a diameter reduced from the root part toward the platform part is formed in the inlet passage.

A fluid passage assembly and method for manufacturing a fluid passage assembly for a power generator. The fluid passage assembly includes a manifold body having an inlet conduit for receiving a fluid, and at least one distribution conduit fluidly coupled to the inlet conduit for dispensing the fluid to cool the power generator, wherein a cross-section of the at least one distribution conduit is includes at least one corner.

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.