The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different diameters. Preparing the disc (6, 14) comprises: realizing annular sets of blades (20) in one piece with the disc (6, 14), said sets (20) being concentric and coaxial with a central axis (X-X) and arranged on the front face (7), wherein each blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X); and/or preparing a plurality of reinforcement rings (23) comprises: realizing in one piece with each one of the reinforcement rings (23) an annular set of auxiliary blades (20) arranged around a central axis (X-X), wherein each auxiliary blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X). Each one of the reinforcement rings (23) is applied to the disc (6, 14) at one of the annular sets of blades (20) and/or auxiliary blades (20), so as to define on the front face (7) annular sets of blades (20) and/or auxiliary blades (20), each one provided with a respective reinforcement ring (23).

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.

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.

A mixed flow turbine (1) for the expansion phase of steam thermodynamic cycles of an organic Rankine cycle provided with a first section (A) in which a first expansion of a main flow of working fluid takes place, in a substantially radial direction having at least one stator stage (S1, S2, . . . Sn) and at least one rotor stage (R1, R2, . . . Rn) of a second section (B) in which a second expansion of the main flow of the working fluid takes place in a substantially axial direction having at least one stator stage and at least one rotor stage and, between the first and the second section, with at least one angular stator stage (S4) comprising an array of angular blades which deflect the main flow of working fluid from the initial radial direction to a substantially axial direction. The turbine (1) is provided with means for injection (60) and/or means for extraction (70) of a second flow of working fluid, placed in proximity of the stator stage (S4).

An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall.

A method for the assembly of a counter-rotating radial turbine includes: preparing a central case; pre-assembling a first turbine unit and a second turbine unit, each including: a half-case delimiting a housing; a rotating unit with a shaft housed and rotatably supported in the housing and that is free to rotate about an axis of rotation with respect to said housing; a rotor disc joined to and overhanging a distal end of the shaft and having a front bladed face facing the opposite side with respect to the half-case. The method includes coupling the first pre-assembled turbine unit and the second pre-assembled turbine unit to the central case so as to arrange the front bladed face of the first rotor disc in front of the front bladed face of the second rotor disc, wherein, following the coupling process, the first half-case and the second half-case laterally close the central case.

A set of turbines, including: a first turbine including a first shaft supported in an overhung manner in a first case, a first rotor provided with first rotor blades and joined to a distal end of the first shaft; a second turbine including a second shaft supported in an overhung manner in a second case, and a second rotor provided with second rotor blades and joined to a distal end of the second shaft. A first front face of the first rotor faces a second front face of the second rotor. The set of turbines further includes a connection element connected to the first front face and to the second front face to transmit rotation from the first shaft to the second shaft or vice versa. The connection element includes at least one elastic joint configured to minimize the rotordynamic influence of the first and second turbine on each other.

A mixed flow turbine (1) for the expansion phase of steam thermodynamic cycles of an organic Rankine cycle provided with a first section (A) in which a first expansion of a main flow of working fluid takes place, in a substantially radial direction having at least one stator stage (S1, S2, . . . Sn) and at least one rotor stage (R1, R2, . . . Rn) of a second section (B) in which a second expansion of the main flow of the working fluid takes place in a substantially axial direction having at least one stator stage and at least one rotor stage and, between the first and the second section, with at least one angular stator stage (S4) comprising an array of angular blades which deflect the main flow of working fluid from the initial radial direction to a substantially axial direction. The turbine (1) is provided with means for injection (60) and/or means for extraction (70) of a second flow of working fluid, placed in proximity of the stator stage (S4).

The present invention relates to a radial turbomachine with axial thrust compensation, comprising: a fixed casing (3); a plurality of main concentric bladed rings (9,9,9,9) arranged in the fixed casing (3) around a central axis (X-X); a plurality of concentric auxiliary bladed rings (15, 15, 15) arranged in the fixed casing (3) around the central axis (X-X) and radially alternated with the main bladed rings (9,9,9,9). A rotor (2, 2) comprising a rotor disc (6, 6) and a rotation shaft (4, 4, 4) integral with the rotor disc (6, 6) is rotatable in the fixed casing (3) around the central axis (X-X) and carries, on a front face (7, 7), the main bladed rings (9,9,9,9). The main (9,9,9,9) and auxiliary (15, 15, 15) bladed rings delimit, with the rotor disc (6, 6), a plurality of concentric front main chambers (30, 33, 35, 36) at different pressures. A plurality of concentric rear annular main chambers (41,41,41,41), each in fluid communication with a respective front main chamber (30, 33, 35, 36) and at the same pressure as the respective front main chamber (30, 33, 35, 36), is delimited between a rear face (8, 8) of the rotor disc (6, 6) and the fixed casing (3). A rear annular area (A_1p, A_2p, A_3p, A_4p, A_4p) of the rotor disc (6, 6) delimiting one of the rear annular main chambers (41,41,41,41) is equal to or substantially equal to a front area (A_1f, A_2f, A_3f, A_4f) of the rotor disc (6, 6) delimiting a respective front main chamber (30, 33, 35, 36), so that the force exerted by the pressure of the working fluid in each rear annular main chamber (41,41,41,41) substantially balances the force exerted by the pressure of the working fluid in the respective front main chamber (30, 33, 35, 36).

The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different diameters. Preparing the disc (6, 14) comprises: realizing annular sets of blades (20) in one piece with the disc (6, 14), said sets (20) being concentric and coaxial with a central axis (X-X) and arranged on the front face (7), wherein each blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X); and/or preparing a plurality of reinforcement rings (23) comprises: realizing in one piece with each one of the reinforcement rings (23) an annular set of auxiliary blades (20) arranged around a central axis (X-X), wherein each auxiliary blade (20) has a leading edge (21 ) and a trailing edge (22) substantially parallel to the central axis (X-X). Each one of the reinforcement rings (23) is applied to the disc (6, 14) at one of the annular sets of blades (20) and/or auxiliary blades (20), so as to define on the front face (7) annular sets of blades (20) and/or auxiliary blades (20), each one provided with a respective reinforcement ring (23).