An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

An impeller includes a body with an interior channel extending through the body along a centerline axis of the impeller. A plurality of blades is connected to the body on a forward end of the impeller centerline axis. The plurality of blades surrounds the interior channel and is fluidly connected to an array of inlets. An array of pentagonal channels extends through the body and radially outward in a spiral pattern. Each pentagonal channel is fluidly connected to a corresponding vane inlet and a corresponding pentagonal-shaped outlet. Each channel maintains a pentagonal cross-section shape from the inlet to the outlet. Each downward-sloping face of the cross section is more than 35 degrees from a horizontal plane perpendicular to the centerline axis of the impeller.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

A turbocharger includes: a bearing provided in a turbocharger body, and configured to rotatably support a turbine shaft in an insertion hole formed in the bearing; and an opposing portion which faces an end surface of the bearing in an axial direction of the turbine shaft. An end-surface guide portion is provided to any one of an opposing surface of the bearing which faces the opposing portion, and an opposing surface of the opposing portion which faces the bearing. The end-surface guide portion configured to make the insertion hole and an outer peripheral edge of the end surface of the bearing in radial directions of the turbine shaft communicate with each other extends forward in a rotational direction of the turbine shaft from a part of the end surface of the bearing which communicates with the insertion hole.

Disclosed herein is a gas turbine disk that includes a cooling target, and a disk unit having a main passage that is open to supply cooling air to the cooling target, and a plurality of unit passages that are open at an end of the main passage while each having a predetermined size.

A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow, a tip end at a radial outer end of the airfoil body, and a shank at a radial inner end of the airfoil body. The radially extending chamber extends at least partially into the shank to define a shank inner surface. An integral impingement cooling structure is within the radially extending chamber. The integral impingement cooling structure allows an exterior surface of a hollow body thereof to be uniformly spaced from the airfoil inner surface despite the curvature of the chamber. The turbine rotor blade has impingement cooling throughout the blade.

A fluid delivery assembly for delivering fluid to a component in a gas turbine engine includes a rotating shaft having a central bore and at least one fluid exhaust in communication with the central bore for centrifugally expelling fluid, and a delivery scoop disposed around the rotating shaft and spaced apart from the rotating shaft by an annular gap. The delivery scoop includes an annular body having at least one impingement surface facing the at least one fluid exhaust and configured to scoop the fluid expelled by the at least one fluid exhaust. The impingement surface has at least one outlet for delivering the scooped fluid to the component. A method of delivering pressurised fluid in a fluid system is also presented.

A heat exchanger is provided. The heat exchanger is formed of a spiral wound flow body (70) having a plurality of passages (76) ending therethrough for passage of a first fluid. The flow body is positioned within a housing (42) and a cross-flow of a second fluid passes between or across successive layers of the spiral wound flow body. The intermixing of the thermal energy of the cross-flowing second fluid and the first fluid provide improved heat exchange.

A turbocharger is provided with a valve body which is disposed in a suction flow path leading from an inflow port of a housing covering a turbine rotor blade to a scroll portion and composed of a single piece or multiple divided pieces to supply a fluid to the turbine rotor blade with the inner surface thereof formed using a first wall surface and a second wall surface facing the first wall surface as part thereof, extends from the upstream side to the downstream side of the flow of the fluid, is rotatably provided in the housing in a direction toward and away from the first wall surface and the second wall surface, forms an upstream-side narrowed flow path with the first wall surface therebetween at an end on the upstream side, and forms a downstream-side narrowed flow path with the second wall surface therebetween at an end on the downstream side. The valve body has a first surface at the end on the upstream side, which faces the first wall surface, gradually approaches the first wall surface from the upstream side to the downstream side and thereafter gradually goes away therefrom, and a second surface which faces the second wall surface.

A turbocharger contains a turbine housing having an accommodating region for a turbine rotor disk of the turbocharger, which accommodating region is arranged centrally with respect to a turbine housing axis, and a turbine spiral channel, which tapers helically toward the accommodating region. A wastegate valve, having a spindle arm and a valve plate arranged on the spindle arm, or a variable exhaust-gas guiding device, having bearing disks and guide vanes, is arranged in the turbine housing. At least one of the: turbine housing, spindle arm and valve plate, or bearing disks and guide vanes, has a steel material for high-temperature applications. The material composition of which contains, in addition to iron, Fe, at least the following alloying constituents in amounts within the specified limits in weight percent: carbon: 0.4-0.5%; silicon: 1.25-1.75%; manganese: 3.0-12.0%; chromium: 19.5-20.5%; nickel: 5.0-6.0%; niobium: 1.00-1.5%. The material composition ensures sufficient temperature resistance of the components.