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公开(公告)号：US20180306109A1
公开(公告)日：2018-10-25
申请号：US15768187
申请日：2016-10-17
摘要： Disclosed herein is an integrated power generation and load driving system, comprising in combination a multi-shaft gas turbine engine comprising a high-pressure turbine mechanically coupled to an air compressor; and a low-pressure turbine, fluidly coupled to but mechanically separated from the high-pressure turbine and mechanically coupled to an output power shaft wherein the output power shaft is connected to a shaft line an electric generator, mechanically coupled to the shaft line and driven into rotation by the gas turbine engine a rotating load, mechanically coupled to the shaft line and driven into rotation by the gas turbine engine a load control arrangement, configured for controlling at least one operating parameter of the rotating load to adapt the operating condition of the rotating load to process requirements from a process, whereof the rotating load forms part, while the low-pressure turbine and the electric generator rotate at a substantially constant speed.
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公开(公告)号：US20190041124A1
公开(公告)日：2019-02-07
申请号：US16077354
申请日：2017-03-07
IPC分类号： F25J1/00 , F01D15/00 , F01D25/16 , F02C1/02 , F02C7/06 , F04D25/02 , F04D25/06 , F04D29/058 , F04D29/58 , F25B1/10 , F25B11/04 , F25B31/02 , F25J1/02 , F25J3/04 , F25J3/06 , F25B1/04
摘要： An expander and motor-compressor unit is disclosed. The unit includes a casing and an electric motor arranged in the casing. A compressor is arranged in the casing and drivingly coupled to the electric motor through a central shaft. Furthermore, a turbo-expander is arranged for rotation in the casing and is drivingly coupled to the electric motor and to the compressor through the central shaft.
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3.发明申请公开(公告)号：US20180266433A1
公开(公告)日：2018-09-20
申请号：US15759838
申请日：2016-09-14
发明人： Giuseppe IURISCI , Simone CORBO
CPC分类号： F04D29/284 , F04D17/02 , F04D17/122 , F04D29/285 , F04D29/30
摘要： A turbomachine impeller is disclosed, which includes: a hub having a rotation axis; a shroud; a plurality of blades between the hub and the shroud; and a plurality of flow vanes, each flow vane being defined between the hub, the shroud and neighboring blades, each flow vane having a flow vane inlet and a flow vane outlet. Each flow vane extends radially inwardly from the flow vane inlet towards a radially innermost flow vane section, and from the radially innermost flow vane section to a flow vane outlet.
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公开(公告)号：US20190249921A1
公开(公告)日：2019-08-15
申请号：US16345454
申请日：2017-10-25
发明人： Elvira BONGERMINO , Angelo GRIMALDI , Giuseppe IURISCI , Antonio PELAGOTTI , Leonardo BALDASSARRE
CPC分类号： F25J1/0022 , F04D25/163 , F25J1/0052 , F25J1/0055 , F25J1/0087 , F25J1/0216 , F25J1/0279 , F25J1/0283 , F25J1/0284 , F25J1/029 , F25J1/0292 , F25J2230/20
摘要： According to one aspect of the present disclosure, a natural gas liquefaction system (100) is provided. The system comprises an integrally-geared turbo-compressor (150) with a plurality of compressor stages; a prime mover (160) for driving the compressor; a pre-cooling loop (110), through which a first refrigerant is adapted to circulate, wherein one or more first compressor stages (151) of the plurality of compressor stages are adapted to pressurize the first refrigerant; a cooling loop (130), through which a second refrigerant is adapted to circulate, wherein one or more second compressor stages (155) of the plurality of compressor stages are adapted to pressurize the second refrigerant; a first heat exchanger device (170) for transferring heat from a natural gas and/or from the second refrigerant to the first refrigerant; and a second heat exchanger device (180) for transferring heat from the natural gas to the second refrigerant. A further aspect relates to a compressor arrangement for a natural gas liquefaction system. A yet further aspect relates to a method of liquefying natural gas.
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公开(公告)号：US20190234301A1
公开(公告)日：2019-08-01
申请号：US16254820
申请日：2019-01-23
CPC分类号： F02C1/02 , F01D1/08 , F01D5/02 , F01D5/04 , F01D5/043 , F01D13/003 , F01D15/06 , F01D15/12 , F02C6/16 , F02C7/32 , F05D2220/62 , F05D2260/211
摘要： A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.
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公开(公告)号：US20190017393A1
公开(公告)日：2019-01-17
申请号：US15745212
申请日：2016-07-18
发明人： Giuseppe IURISCI , Angelo GRIMALDI , Simone CORBO
摘要： An unshrouded turbomachine impeller is disclosed. The impeller comprises a hub and a plurality of sequentially arranged blades. Each blade extends from a blade root at the hub to a blade tip and is comprised of a first blade edge and a second blade edge. A flow vane is formed between each pair of neighboring blades. A connection member extends across each flow vane between neighboring blades and rigidly or monolithically connects a first modal displacement region of a first one of the pair of neighboring blades to a second modal displacement region of a second one of the pair of neighboring blades.
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公开(公告)号：US20180209427A1
公开(公告)日：2018-07-26
申请号：US15747178
申请日：2016-07-22
IPC分类号： F04D17/02 , F04D25/16 , F04D25/02 , F04D29/28 , F04D29/32 , F04D29/52 , F04D17/12 , F04D19/02 , F25J1/00 , F25J1/02
CPC分类号： F04D17/025 , F04D17/12 , F04D19/028 , F04D25/02 , F04D25/16 , F04D27/023 , F04D27/0238 , F04D27/0269 , F04D29/286 , F04D29/321 , F04D29/522 , F25J1/0022 , F25J1/004 , F25J1/0052 , F25J1/0055 , F25J1/0072 , F25J1/0082 , F25J1/0085 , F25J1/0087 , F25J1/0207 , F25J1/021 , F25J1/0216 , F25J1/0218 , F25J1/0279
摘要： The LNG plant comprises a compression train and a further compression. The compression train (100) comprises comprising an engine and a compressor driven by the engine; the compressor is an axial compressor and comprises a first set of axial compression stages and a second set of axial compression stages arranged downstream the first set of axial compression stages; at least the first set and the second set of axial compression stages are housed inside one case. The further compression train comprises a further engine and a further compressor driven by the further engine; the further compressor is a centrifugal compressor and comprises a first set of impellers and a second set of impellers arranged downstream or upstream the first set of impellers.
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