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公开(公告)号：US20230358146A1
公开(公告)日：2023-11-09
申请号：US17905301
申请日：2021-03-04
CPC分类号： F01D11/04 , F01D11/00 , F05D2220/32 , F05D2240/55 , F05D2240/24
摘要： A turbine, and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel reaches the wheel space. The rotor members each include a deflector. The deflector is placed in correspondence with each spacer and deflects the purging air pumped up from the wheel spaces by the rotor members, to prevent the ingested gas flow to heat up the roots of the blades.
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公开(公告)号：US11732753B2
公开(公告)日：2023-08-22
申请号：US17979847
申请日：2022-11-03
申请人： Stein Seal Company
发明人： Glenn M. Garrison
CPC分类号： F16C32/0662 , F01D11/04 , F01D25/22 , F16C32/0607 , F16C32/0625 , F16J15/40 , F16J15/441 , F16J15/442 , F05D2250/75 , F16C2360/23
摘要： A circumferential seal assembly suitable for forming a thin film between a rotatable runner and a sealing ring is presented. The assembly includes an annular seal housing, a rotatable runner, an annular seal ring, and a plurality of groove structures. Each groove structure includes a groove and an optional feed groove. The groove includes at least two adjoining steps defined by base walls arranged to decrease depthwise. Two adjoining base walls are disposed about a base shoulder. Each base shoulder locally redirects a longitudinal flow to form an outward radial flow in the direction of the annular seal ring. The base walls are bounded by and intersect a pair of side walls. A side wall includes side shoulders which narrows the groove widthwise and locally redirects the longitudinal flow to form a lateral flow in the direction of the other side wall. Outward and lateral flows separately or in combination enhance stiffness of a thin-film layer between the annular seal ring and the rotatable runner.
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公开(公告)号：US20230220872A1
公开(公告)日：2023-07-13
申请号：US17979847
申请日：2022-11-03
申请人： Stein Seal Company
发明人： Glenn M. Garrison
CPC分类号： F16C32/0662 , F16C32/0607 , F16C32/0625 , F16J15/40 , F01D25/22 , F16J15/442 , F16J15/441 , F01D11/04 , F05D2250/75 , F16C2360/23
摘要： A circumferential seal assembly suitable for forming a thin film between a rotatable runner and a sealing ring is presented. The assembly includes an annular seal housing, a rotatable runner, an annular seal ring, and a plurality of groove structures. Each groove structure includes a groove and an optional feed groove. The groove includes at least two adjoining steps defined by base walls arranged to decrease depthwise. Two adjoining base walls are disposed about a base shoulder. Each base shoulder locally redirects a longitudinal flow to form an outward radial flow in the direction of the annular seal ring. The base walls are bounded by and intersect a pair of side walls. A side wall includes side shoulders which narrows the groove widthwise and locally redirects the longitudinal flow to form a lateral flow in the direction of the other side wall. Outward and lateral flows separately or in combination enhance stiffness of a thin-film layer between the annular seal ring and the rotatable runner.
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公开(公告)号：US11466578B2
公开(公告)日：2022-10-11
申请号：US17251546
申请日：2019-06-12
发明人： Ludovic Pintat
摘要： A turbine nozzle for an aircraft turbine engine, the nozzle including at least one vane and a base having a platform. The nozzle is fitted with a passive system for reintroducing blow-by gas into the primary jet, the passive system including gas extraction ports on the base as well as gas reinjection ports on the radially outer surface of the platform and/or on a suction-side surface of the vanes, the gas reinjection ports being designed to redirect the gas flow in a reinjection direction having a circumferential orientation.
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公开(公告)号：US11434930B2
公开(公告)日：2022-09-06
申请号：US15970625
申请日：2018-05-03
摘要： A sealing system of a turbomachine for sealing a rotor of the turbomachine relative to a stator of the turbomachine, having a rotor-side component rotating together with the rotor, a stator-side component that is stationary together with the stator, and a dry gas seal, which includes a rotor-side sealing component and a stator-side sealing component compressed via a spring element forming a sealing gap, and a cleaning device, via which detergent is conducted in the direction of the spring element for cleaning the same and/or in the direction of the sealing gap for cleaning the same.
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公开(公告)号：US11326466B2
公开(公告)日：2022-05-10
申请号：US16564292
申请日：2019-09-09
摘要： A supply system of a sealing system of a turbomachine, wherein the sealing system which are suppliable with a seal gas. The supply system comprises, for each sealing sub-system, four seal gas lines: a first seal gas supply line, via which process gas extracted from the turbomachine is suppliable as first seal gas to the respective sealing sub-system. A second seal gas supply line, via which second seal gas is suppliable to the respective sealing sub-system. A seal gas discharge line, via which the first seal gas and the second seal gas are dischargeable from the respective sealing sub-systems. A safety discharge line, which is closed during the normal operation and open in the event of a fault, to discharge at least one part of the first seal gas and of the second seal gas from the respective sealing sub-system via the same in the event of a fault.
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公开(公告)号：US11149575B2
公开(公告)日：2021-10-19
申请号：US16377413
申请日：2019-04-08
IPC分类号： F01D11/04 , F23R3/00 , F01D9/04 , F01D25/12 , F01D25/00 , F02C3/14 , F01D9/02 , F23R3/50 , F01D11/00 , F23R3/60
摘要： Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path.
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公开(公告)号：US11105201B2
公开(公告)日：2021-08-31
申请号：US16492413
申请日：2017-03-16
发明人： Takuro Koda
摘要： A steam turbine includes: a rotor; a casing; a thrust bearing; a steam inlet; a first pipe; a first regulation valve; a second pipe; a second regulation valve; and a control device. The control device estimates an exhaust flow rate of the steam turbine based on an operating point map which derives the exhaust flow rate of the steam turbine from an operating point of the steam turbine and estimates the thrust force applied to the thrust bearing based on the exhaust flow rate.
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公开(公告)号：US11053808B2
公开(公告)日：2021-07-06
申请号：US16790890
申请日：2020-02-14
摘要： A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.
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公开(公告)号：US20210095572A1
公开(公告)日：2021-04-01
申请号：US17050204
申请日：2019-03-19
发明人： Daiki FUJIMURA
摘要： In a combined cycle plant and a method for operating the same, the combined cycle plant is provided with a gas turbine, a waste heat recovery boiler, and a steam turbine, and is also provided with a low-pressure gland steam line for supplying steam to a low-pressure gland portion of a low-pressure turbine, and a first heat exchanging unit which performs heat exchange between gland steam flowing through the low-pressure gland steam line, and fuel gas to be supplied to a combustor.
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