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公开(公告)号：US20220195883A1
公开(公告)日：2022-06-23
申请号：US17126276
申请日：2020-12-18
摘要： Flow restricting arrangements and rotor assemblies are provided. A flow restricting arrangement includes a stationary component and a rotating component. The rotating component is radially spaced apart from the stationary component such that a clearance is defined between the stationary component and the rotating component. A first magnet is embedded within the stationary component. A second magnet embedded within the rotating component. A plurality of magnetically responsive particles is contained within the clearance by a magnetic field produced by the first magnet and the second magnet. The plurality of magnetically responsive particles at least partially span the clearance.
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公开(公告)号：US11299999B2
公开(公告)日：2022-04-12
申请号：US16895220
申请日：2020-06-08
发明人： Yeong Chun Kim
IPC分类号： F01D11/22 , F01D25/24 , F04D29/046 , F01D25/16
摘要： A clearance adjusting apparatus to move a thrust bearing of a gas turbine back and forth to adjust a tip clearance of a turbine is provided. The clearance adjusting apparatus includes an adjusting plate disposed to move forward from or rearward to a reference surface, a biasing cylinder disposed to selectively move the adjusting plate back and forth, a stopper disposed to be moved toward the adjusting plate after being moved forward to prevent a rearward movement of the adjusting plate, a position sensor disposed to measure a distance from the reference surface to the adjusting plate, and a controller configured to receive information about measurements from the position sensor and control an operation of the stopper and the biasing cylinder based on the received information.
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公开(公告)号：US11242765B2
公开(公告)日：2022-02-08
申请号：US16895241
申请日：2020-06-08
发明人： Yeong Chun Kim
IPC分类号： F01D11/22
摘要： A clearance adjusting apparatus disposed in front of a compressor of a gas turbine to axially move a compressor disk back and forth to adjust a tip clearance formed between a compressor blade and a compressor casing is provided. The clearance adjusting apparatus includes a hollow fastening part disposed in front of the compressor casing, a shaft disposed in the fastening part and coupled to a front side of the compressor disk, an adjusting part disposed between the fastening part and the shaft to axially move the shaft back and forth to adjust the tip clearance, and a biasing part disposed on the fastening part to bias the adjusting part back and forth to adjust a position of the adjusting part and the shaft.
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公开(公告)号：US11174798B2
公开(公告)日：2021-11-16
申请号：US16359010
申请日：2019-03-20
发明人： Gary D. Roberge
摘要： A compressor case for a gas turbine engine includes an annular body that extends circumferentially around a center axis and extends axially along the center axis. A first bleed manifold is formed on an outer surface of the annular body and encloses a first plenum. A second bleed manifold is formed on the outer surface of the annular body and is axially aft of the first bleed manifold. The second bleed manifold encloses a second plenum. A bleed inlet extends through the annular body and into the first bleed manifold. Cooling passages are formed in the annular body, and each of the cooling passages extends from the first plenum to the second plenum and fluidically connects the first plenum to the second plenum.
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公开(公告)号：US11105338B2
公开(公告)日：2021-08-31
申请号：US16579011
申请日：2019-09-23
发明人： Michael Nesteroff , Jonathan Acker , Jeffrey Crutchfield , Nate Cooper , Mark Whitlock , Nathan Ottow
IPC分类号： F04D29/42 , F04D29/16 , F01D5/04 , F01D11/22 , F04D17/02 , F04D17/10 , F02C3/08 , F04D27/02 , F01D11/08 , F04D29/62 , F01D11/18
摘要： A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.
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公开(公告)号：US10935044B2
公开(公告)日：2021-03-02
申请号：US16529404
申请日：2019-08-01
发明人： Nathan Ottow , Johnathan Acker , Nate Cooper , Mark Whitlock , Michael Nesteroff
摘要： A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.
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公开(公告)号：US10731666B2
公开(公告)日：2020-08-04
申请号：US16169034
申请日：2018-10-24
发明人： Richard J. Skertic
摘要： A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver is coupled to a closed form refrigeration system having an evaporator, a compressor, a condenser, an expansion valve, and a refrigerant contained therein. The thermal driver is cooled by the refrigeration system, and the rate of cooling causes expansion and contraction of the thermal driver that is translated by linkages into axially forward and aft motion of the shroud.
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公开(公告)号：US10557367B2
公开(公告)日：2020-02-11
申请号：US15105220
申请日：2014-12-19
摘要： An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.
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公开(公告)号：US10415417B2
公开(公告)日：2019-09-17
申请号：US15221061
申请日：2016-07-27
发明人： Michael G. McCaffrey
摘要： A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.
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公开(公告)号：US10364694B2
公开(公告)日：2019-07-30
申请号：US15105358
申请日：2014-12-01
摘要： A turbomachine blade clearance system can include an actuator having an anchor portion for fixation to an interior surface of a turbomachine housing and an actuating portion for actuating movement relative to the anchor portion. A turbomachine blade seal can be operatively connected to the actuating portion of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade.
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