A multi-stage turbine (16) is designed as an induction turbine with vapour induction in at least one intermediary stage. It is more particularly conceived as a radial-outward-flow type multi-stage turbine, with an axial main vapour inlet port (82) and an annular secondary vapour inlet port (84), which is arranged in the turbine (16) so as to annularly induce, in an intermediary stage of said turbine, a secondary vapour stream into an already partially expanded radial main vapour stream. The annular secondary vapour inlet port (84) comprises as a ring-zone (92) with through holes (94), which radially surrounds said axial main vapour inlet port (82) in a first turbine housing part (80). The axial vapour inlet port comprises a first tubular vapour inlet connection (82). The annular vapour inlet port comprises a second tubular vapour inlet connection (84) surrounding the first tubular vapour inlet connection (82), so as to define with the latter an annular space (86), wherein the ring-zone (92) with through holes (94) is arranged in this annular space (86).

A multi-stage turbine (16) is designed as an induction turbine with vapour induction in at least one intermediary stage. It is more particularly conceived as a radial-outward-flow type multi-stage turbine, with an axial main vapour inlet port (82) and an annular secondary vapour inlet port (84), which is arranged in the turbine (16) so as to annularly induce, in an intermediary stage of said turbine, a secondary vapour stream into an already partially expanded radial main vapour stream. The annular secondary vapour inlet port (84) comprises as a ring-zone (92) with through holes (94), which radially surrounds said axial main vapour inlet port (82) in a first turbine housing part (80). The axial vapour inlet port comprises a first tubular vapour inlet connection (82). The annular vapour inlet port comprises a second tubular vapour inlet connection (84) surrounding the first tubular vapour inlet connection (82), so as to define with the latter an annular space (86), wherein the ring-zone (92) with through holes (94) is arranged in this annular space (86).

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 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 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 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 rotary directional pressure engine having a case within which a plurality of rotors rotate in parallel. The rotors include asymmetrical cavities on the circumferential faces thereof, which cavities function to move air and/or other gases into a combustion chamber area during an intake phase, to cooperatively form a combustion chamber during an ignition and combustion phase, and to move exhaust gases to the area of one or more exhaust ports for removal from the engine during an exhaust phase. Continued rotation of the rotors is accomplished by harnessing and properly directing the forces of combustion against the asymmetrical cavities of the rotors.

A rotary directional pressure engine having a case within which a plurality of rotors rotate in parallel. The rotors include asymmetrical cavities on the circumferential faces thereof, which cavities function to move air and/or other gases into a combustion chamber area during an intake phase, to cooperatively form a combustion chamber during an ignition and combustion phase, and to move exhaust gases to the area of one or more exhaust ports for removal from the engine during an exhaust phase. Continued rotation of the rotors is accomplished by harnessing and properly directing the forces of combustion against the asymmetrical cavities of the rotors.

A centrifugal radial turbine includes at least one support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path. The disc has through induction channels situated in a position radially external with respect to a respective shaft and radially internal with respect to the radial rotor stage. At the respective through induction channels, the disc includes a plurality of induction rotor blades of at least one respective axial rotor stage.

A centrifugal radial turbine includes at least one support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path. The disc has through induction channels situated in a position radially external with respect to a respective shaft and radially internal with respect to the radial rotor stage. At the respective through induction channels, the disc includes a plurality of induction rotor blades of at least one respective axial rotor stage.