A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.

A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed.

An apparatus and method for a turbine engine for can include an engine component. The engine component can include an interior cooling passage at least partially defining a cooling circuit for passing a flow of cooling fluid through the component. Film holes provide for exhausting a portion of the cooling fluid to an exterior of the component, to form a cooling film along an exterior hot surface of the engine component. A deflector can be position within the cooling passage upstream form the film hole.

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 turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a vane. The support strut is made of metallic materials. The vane is made of composite materials and is arranged around the support strut to insulate the metallic materials of the support strut during use of the turbine vane assembly.

A seal device according to the embodiment includes a seal fin provided between the rotation body and the stationary body and extending in a circumferential direction of the rotation body, and a swirl brake fin provided on the stationary body upstream of the seal fin. The swirl brake fin reduces a circumferential velocity component of the working fluid. The swirl brake fin has a negative pressure surface provided on a side of a rotation direction of the rotation body and a positive pressure surface provided on an opposite side to the negative pressure surface. The positive pressure surface extends in a direction opposite to the rotation direction of the rotation body from radially outward toward radially inward.

The invention relates to a turbine engine extending longitudinally along an X axis and including a main duct in which an air stream flows, the turbine engine including at least one upstream compressor disc, at least one downstream compressor disc and a circuit for collecting air from an air stream collected in the main duct, the air collection circuit including a radial portion in which at least one air collection tube is mounted and a longitudinal portion extending between a cylindrical body and a central bore of the downstream compressor disc. The turbine engine includes a plurality of blades extending in the longitudinal portion of the air collection circuit, configured to be rotated about the X axis, in order to rotate the collected air stream.

A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.

A bearing section for an exhaust turbocharger comprises a receiving opening for receiving a shaft of a rotor assembly of the exhaust turbocharger. The bearing section is designed for positioning bearing elements for supporting the shaft. A lubricant circuit is designed for supplying lubricant to the bearing elements. Lubricant channels are formed in the bearing section. In order to reduce a component temperature of the bearing section, a cooling jacket is provided, through which coolant can flow. The cooling jacket comprises a coolant channel, an inlet channel and an outlet channel. The inlet channel issues at a first opening point into the coolant channel and the outlet channel is connected at a second opening point to the coolant channel in such a way that a flow can pass therethrough. A rib is provided in the coolant channel.