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公开(公告)号：US20240318779A1
公开(公告)日：2024-09-26
申请号：US18613462
申请日：2024-03-22
申请人： BAE SYSTEMS plc
发明人： Andrew Sadler , Alan Phizacklea , Anthony Craig Robinson , James William Spain , Adam William Rawlinson
IPC分类号： F17C1/00
CPC分类号： F17C1/00 , F17C2201/0104 , F17C2209/221 , F17C2209/228 , F17C2209/232
摘要： A support structure for manufacturing a pressure vessel, the support structure configured to be carried on a supporting substrate, the support structure comprising a first segment support structure nestable within, and moveable relative to, a second segment support structure, wherein the first segment support structure is configured to be raised and lowered relative to the second segment support structure to thereby raise and lower the first segment relative to the substrate, and the first segment support structure is configured to move between a nested position within the second segment support structure to a position spaced apart from the second segment support structure across a surface of the substrate.
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公开(公告)号：US12104529B2
公开(公告)日：2024-10-01
申请号：US18533447
申请日：2023-12-08
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： 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).
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公开(公告)号：US11994031B2
公开(公告)日：2024-05-28
申请号：US18252097
申请日：2021-11-03
申请人： BAE SYSTEMS plc
发明人： James William Spain
IPC分类号： F03C2/00 , F01C1/12 , F01C21/18 , F03C4/00 , F04C2/00 , F04C18/00 , F04C18/16 , F04C18/12 , F04C29/12
CPC分类号： F01C1/123 , F01C21/18 , F04C18/165 , F04C18/123 , F04C29/12
摘要： A rotor unit assembly includes a rotor unit having a chamber and a rotor located within the chamber. The rotor has a piston which extends radially outward from the main body of the rotor; and a valve flange with an aperture. The rotor unit further comprises a rotatable hub, with a cavity configured to receive the piston. The rotor unit further comprises a first low pressure port provided in a path described by the piston; a first high pressure port positioned in a path described by the valve flange aperture around the clearance volume; and a second high pressure port positioned in a path described by the cavity around the hub axis.
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公开(公告)号：US20230250921A1
公开(公告)日：2023-08-10
申请号：US18004518
申请日：2021-06-24
申请人： BAE SYSTEMS plc
发明人： Andrew Sadler , Alan Phizacklea , Anthony Craig Robinson , James William Spain , Adam William Rawlinson
IPC分类号： F17C1/00
CPC分类号： F17C1/00 , F17C2201/0104 , F17C2209/221 , F17C2209/228 , F17C2209/232
摘要： 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).
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公开(公告)号：US20230122100A1
公开(公告)日：2023-04-20
申请号：US17907420
申请日：2021-03-16
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： 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).
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公开(公告)号：US20210363892A1
公开(公告)日：2021-11-25
申请号：US17282046
申请日：2019-10-09
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： 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). There is provided a heat supply unit (136) which defines a portion (140) of the working fluid flow duct (60) in flow series between the turbine rotor stage (24) and turbine module outlet (114). The first heat exchanger (37) is in heat transfer communication with the heat supply unit (136), and the first heat exchanger (37) is configured such that it is operable to transfer heat received from the heat supply unit (136) to the working fluid (150) passing the first heat exchanger (37).
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公开(公告)号：US12078113B2
公开(公告)日：2024-09-03
申请号：US17282044
申请日：2019-10-09
申请人： BAE SYSTEMS plc
发明人： James William Spain
CPC分类号： F02C9/18 , F01D9/041 , F01D25/12 , F02C1/10 , F02C7/143 , F02K3/115 , F04D19/002 , F04D29/5826
摘要： 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). The first heat exchanger (37) is in heat transfer communication with the heat sink unit (236). The first heat exchanger (37) is configured such that it is operable to transfer heat to the heat sink unit (236) from the working fluid (250) passing the first heat exchanger (37).
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公开(公告)号：US11434776B2
公开(公告)日：2022-09-06
申请号：US17282046
申请日：2019-10-09
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： 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). There is provided a heat supply unit (136) which defines a portion (140) of the working fluid flow duct (60) in flow series between the turbine rotor stage (24) and turbine module outlet (114). The first heat exchanger (37) is in heat transfer communication with the heat supply unit (136), and the first heat exchanger (37) is configured such that it is operable to transfer heat received from the heat supply unit (136) to the working fluid (150) passing the first heat exchanger (37).
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公开(公告)号：US20210388730A1
公开(公告)日：2021-12-16
申请号：US17282044
申请日：2019-10-09
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： 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). The first heat exchanger (37) is in heat transfer communication with the heat sink unit (236). The first heat exchanger (37) is configured such that it is operable to transfer heat to the heat sink unit (236) from the working fluid (250) passing the first heat exchanger (37).
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公开(公告)号：US20240117767A1
公开(公告)日：2024-04-11
申请号：US18533447
申请日：2023-12-08
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： 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).
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