Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: A method of manufacturing a pressure vessel (10) comprising the steps of dividing a wall (104) of a section (100) of the pressure vessel (10) into a first segment (120) and a second segment (150), separating the first segment (120) from the second segment (150), fitting apparatus (400) onto the first segment (120), and then re-attaching the first segment (120) and the second segment (150).

Abstract: A rotor unit assembly (10) having a rotor unit (90). The rotor unit (90) comprises a chamber (104) and a rotor (200) located within the chamber (104). The rotor (200) has a piston (214) which extends radially outward from the main body (202) of the rotor (200); and a valve flange (240) with an aperture (242). The rotor unit further comprises a rotatable hub (300), with a cavity (314) configured to receive the piston (214). The rotor unit (90) further comprises a first low pressure port (130) provided in the path described the piston (214); a first high pressure port (120) positioned in the path described the valve flange aperture (242) around the clearance volume (210); and a second high pressure port (122) positioned in the path described by the cavity (314) around the hub axis (306).

Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: A method of manufacturing a pressure vessel (10) comprising the steps of dividing a wall (104) of a section (100) of the pressure vessel (10) into a first segment (120) and a second segment (150), separating the first segment (120) from the second segment (150), fitting apparatus (400) onto the first segment (120), and then re-attaching the first segment (120) and the second segment (150).

Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: A turbine module (100) for a heat engine (104) wherein the turbine module (100) defines a working fluid flow duct (60) between a turbine module inlet (110) and a turbine module outlet (114) configured to expand a working fluid as the working fluid passes along the working fluid flow duct (60). The turbine module comprises a first heat exchanger (37) and a turbine rotor stage (24) each provided in the working fluid flow duct (60). The first heat exchanger (37) is provided in flow series between the turbine module inlet (110) and the turbine rotor stage (24); and the turbine stage (24) is provided in flow series between the first heat exchanger (37) and the turbine module outlet (114). The first heat exchanger (37) defined by a wall (126) having an external surface (182) which is located in the working fluid flow duct (60).

Abstract: A compressor module (200) wherein the compressor module (200) defines a working fluid flow duct (60) between a compressor module inlet (210) and a compressor module outlet (214). The compressor module comprises: a first heat exchanger (37) and a compressor rotor stage (24) each provided in the working fluid flow duct (60). The first heat exchanger (37) is provided in flow series between the compressor module inlet (210) and the compressor rotor stage (24). The compressor stage (24) is provided in flow series between the first heat exchanger (37) and the compressor module outlet (214). The first heat exchanger (37) is defined by a wall (226) having an external surface (282) which is located in the working fluid flow duct (60). There is provided a heat sink unit (236) which defines a portion (240) of the working fluid flow duct (60) in flow series between the compressor rotor stage (24) and compressor module outlet (214).

Abstract: A turbine module (100) for a heat engine (104) wherein the turbine module (100) defines a working fluid flow duct (60) between a turbine module inlet (110) and a turbine module outlet (114) configured to expand a working fluid as the working fluid passes along the working fluid flow duct (60). The turbine module comprises a first heat exchanger (37) and a turbine rotor stage (24) each provided in the working fluid flow duct (60). The first heat exchanger (37) is provided in flow series between the turbine module inlet (110) and the turbine rotor stage (24); and the turbine stage (24) is provided in flow series between the first heat exchanger (37) and the turbine module outlet (114). The first heat exchanger (37) defined by a wall (126) having an external surface (182) which is located in the working fluid flow duct (60).