A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.

A torque converter turbine is provided. The torque converter turbine includes a plurality of blades, an annular bowl shaped blade supporting portion supporting the blades and a mass fixed to the blade supporting portion. A method of forming a torque converter turbine is also provided. The method includes providing a blade supporting portion of a turbine shell with mass and connecting a plurality of blades to the blade supporting portion.

A gas compressor comprising a drum affixed to a rotating shaft, the drum including a plurality of compression channels between a common pressure zone and an interior surface of the drum distal to an axis of rotation. A static vane return assembly adjacent the compression channels includes vanes extending from an inlet at an outer circumference to the common pressure zone and directing gas into the common pressure zone, either through the vanes or via separate channels or ducts. Fluid inside the rotating dmm forms an annular lake that is drawn through the vanes and into the common pressure zone. Fluid is then forced into the compression channels where gas in the fluid is compressed as it travels from the common pressure zone toward the interior surface. The pressurized gas is separated from the liquid prior to leaving the compression channel assembly while the liquid is returned to the lake.

A gas compressor comprising a drum affixed to a rotating shaft, the drum including a plurality of compression channels between a common pressure zone and an interior surface of the drum distal to an axis of rotation. A static vane return assembly adjacent the compression channels includes vanes extending from an inlet at an outer circumference to the common pressure zone and directing gas into the common pressure zone, either through the vanes or via separate channels or ducts. Fluid inside the rotating drum forms an annular lake that is drawn through the vanes and into the common pressure zone. Fluid is then forced into the compression channels where gas in the fluid is compressed as it travels from the common pressure zone toward the interior surface. The pressurized gas is separated from the liquid prior to leaving the compression channel assembly while the liquid is returned to the lake.

A bladed rotor wheel of an aero turbine stage includes a portion of a rotor blade with a shank portion and a bottom surface; a portion of a forged rotor disk with a rim portion and an outer surface; and a joining structure provided by an additive manufacturing process configured for integrally merging the portion of a rotor blade with the portion of a forged rotor disk. An aero turbine can include such bladed rotor wheel, and an aircraft can include such aero turbine.

Disclosed is a pressurization air conditioning arrangement, the arrangement having: a turbine including a housing and a rotor within the housing, wherein the rotor is a dual scroll and including an inner shroud separating a first set of rotor blades from a second set of rotor blades; a diffuser extending from an exhaust of the turbine; and an exhaust shroud within the diffuser, the exhaust shroud dividing the diffuser into an inner diffuser passage and an outer diffuser passage.

A turbine wheel for a turbine of a turbocharger. The turbine wheel includes a plurality of turbine blades distributed evenly about the axis of rotation; and a plurality of inter-blade portions distributed evenly about the axis of rotation. Each of the inter-blade portions is disposed between two blades and each of the blades is disposed between two inter-blade portions, the inter-blade portions and the turbine blades being integrally formed. A cross-section, taken along a plane normal to the axis of rotation, of a surface of each inter-blade portion of the plurality of inter-blade portions being described by a smooth curve extending between the two turbines blades of the plurality of turbine blades between which the inter-blade portion is disposed. In some cases, the smooth curve of each inter-blade portion is described by a curve fitted to a biomimicry design form extending between the first blade and the second blade.

An additive manufacturing method includes forming a shaped body by repeating: a material feeding step of forming a powder layer by feeding a shaping material that includes a metal powder onto a base that is provided outside a spindle in a radial direction thereof while rotating the spindle provided to be rotatable about a center axis; and a beam irradiating step of solidifying the shaping material by irradiating a prescribed area of the powder layer with a beam.