A method for manufacturing bladed rings for radial turbomachines, including: assembling a first support ring with a second support ring, with a plurality of blades, with a first and second connecting ring, to make a bladed ring including the first and second support ring coaxial and axially spaced and the plurality of blades disposed equidistant from a central axis and interposed between the rings. The method includes joining a first end of each blade to the first connecting ring, joining a second end of each blade to the second connecting ring, fixing the first connecting ring to the first support ring and fixing the second connecting ring to the second support ring. The first support ring, second support ring, plurality of blades, first and second connecting rings are finished elements before assembling, meaning they present their final geometry and need no further machining and/or plastic deformations during and/or after assembly.

A method for the construction of bladed rings for radial turbomachines, including: preparing an annular block; roughing the annular block by removing material to define a first, second, third and fourth axial section, wherein the first axial section defines a reinforcement ring, wherein the third axial section defines a base ring; roughing the second axial section by removing material to delimit a plurality of separate elements, wherein the separate elements axially connect the base ring to the reinforcement ring; finishing each of the separate elements by removing material to provide the separate element with the shape of an airfoil blade, wherein a leading edge of the blade and a trailing edge of the blade develop substantially parallel to a central axis of the bladed ring; roughing the fourth axial section by removing material for delimiting an annular anchoring appendage of the base ring to a radial turbomachine.

A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.

A radial turbine impeller includes a turbine wheel module including a first surface and a second surface being mutually opposite in the axial direction of the radial turbine impeller. The radial turbine impeller includes blade modules attached to the turbine wheel module. Each blade module is a single piece of material and includes a body portion and blades connected to the body portion and protruding in the axial direction from the body portion. At least the first surface of the turbine wheel module is provided with one or more annular grooves opening in the axial direction and containing the body portions of the blade modules so that, in each of the grooves, the blade modules are successively in the circumferential direction. The radial turbine impeller further includes a securing system for keeping the body portions of the blade modules in the one or more grooves.

A method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the stop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.

A flywheel is provided in combination with a hybrid machine, wherein said flywheel comprises, in a radial direction, from inward to outward, an inner turbine, an intermediate compressor, and an outer array of magnets. The turbine cooperates with said hybrid machine to spin faster when said machine decelerates, and slower when said machine accelerates. An inner turbine drives both said intermediate compressor and said hybrid machine. The outer array of magnets is driven by said hybrid machine to accelerate the flywheel to accelerate the flywheel during braking of said hybrid machine. Said hybrid machine communicates with said flywheel to house it and render energy from it, in a hybrid manner such that energy is stored in a pressure or electrical storage mode, or both pressure and electrical storage mode, to effect a regenerative mode that attains low fuel consumption.

Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions. Several of first circular portions bear projecting elements and second circular portions are more deformable, along radial directions, than first circular portions in manner to allow relative movements between first circular portions when support plate is subjected to action of thermal gradients.