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公开(公告)号：US20180134407A1
公开(公告)日：2018-05-17
申请号：US15284001
申请日：2016-10-03
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A cooling system includes a first conduit positioned within a cavity and extends from a radially inner casing aperture to a radially outer casing aperture. The cooling system also includes a second conduit coupled in flow communication with the first conduit and extending into the cavity. The cooling system further includes at least one valve positioned within the first conduit and the second conduit. The at least one valve and the first conduit are configured to channel a first fluid from the radially inner casing aperture to the radially outer casing aperture during a first mode of operation. The at least one valve, the second conduit, and the first conduit are configured to channel a second fluid from the radially outer casing aperture to the cavity during a second mode of operation.
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公开(公告)号：US10196928B2
公开(公告)日：2019-02-05
申请号：US15059116
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Jeffrey Wayne Litzler
Abstract: A pipe fault detection system is provided for a gas turbine engine having a compressor and a turbine. The pipe fault detection system includes a cooling manifold configured to direct cooling air from the compressor to the turbine. The cooling manifold includes at least two cooling pipes, a sensor configured to detect an operating condition indicative of a pipe break, and a controller configured to control the amount of cooling air through the cooling manifold in response to the operating condition detected by the sensor.
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公开(公告)号：US20220154594A1
公开(公告)日：2022-05-19
申请号：US17471576
申请日：2021-09-10
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bojan Lukovic , Michael John Murray , Christian Michael Fernholz , Davide Lauria , Rocco Pellettieri , Steven Edward Nolte
IPC: F01D19/00
Abstract: An aspect of the present disclosure is directed to a method for mitigating rotor bow in a turbo machine. The method includes rotating a rotor over a first period of time; discontinuing rotation of the rotor for a second period of time; and iterating, over an overall period of time, rotation of the rotor over the first period of time and discontinuing rotation of the rotor for the second period of time.
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公开(公告)号：US11525370B2
公开(公告)日：2022-12-13
申请号：US17471576
申请日：2021-09-10
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bojan Lukovic , Michael John Murray , Christian Michael Fernholz , Davide Lauria , Rocco Pellettieri , Steven Edward Nolte
IPC: F01D19/00
Abstract: An aspect of the present disclosure is directed to a method for mitigating rotor bow in a turbo machine. The method includes rotating a rotor over a first period of time; discontinuing rotation of the rotor for a second period of time; and iterating, over an overall period of time, rotation of the rotor over the first period of time and discontinuing rotation of the rotor for the second period of time.
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公开(公告)号：US20140058644A1
公开(公告)日：2014-02-27
申请号：US13954541
申请日：2013-07-30
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
IPC: B64D31/06
Abstract: A method for reducing a turbine clearance between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. Said method includes determining, with a flight operation controller, that an airplane is in a first flight condition, wherein the first flight condition is associated with a first turbine clearance and a first engine responsiveness level, determining, with the flight operation controller, that the airplane is in a second flight condition, adjusting an engine responsiveness level from the first engine responsiveness level to a second engine responsiveness level based on determining the airplane is in the second flight condition, and adjusting the turbine clearance from the first turbine clearance to a second turbine clearance based on the engine responsiveness level.
Abstract translation: 提供了一种用于减小涡轮发动机的多个转子叶片和涡轮发动机的护罩之间的涡轮间隙的方法。 所述方法包括使用飞行操作控制器确定飞机处于第一飞行状态，其中第一飞行条件与第一涡轮机间隙和第一发动机响应度水平相关联，用飞行操作控制器确定： 飞机处于第二飞行状态，基于确定飞机处于第二飞行状态，将发动机响应性水平从第一发动机响应水平调整到第二发动机响应水平，并且将涡轮机间隙从第一涡轮机间隙调整到第二飞行器间隙 基于发动机响应性水平的涡轮间隙。
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Patent Agency Ranking
公开(公告)号：US10583933B2
公开(公告)日：2020-03-10
申请号：US15284001
申请日：2016-10-03
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A cooling system includes a first conduit positioned within a cavity and extends from a radially inner casing aperture to a radially outer casing aperture. The cooling system also includes a second conduit coupled in flow communication with the first conduit and extending into the cavity. The cooling system further includes at least one valve positioned within the first conduit and the second conduit. The at least one valve and the first conduit are configured to channel a first fluid from the radially inner casing aperture to the radially outer casing aperture during a first mode of operation. The at least one valve, the second conduit, and the first conduit are configured to channel a second fluid from the radially outer casing aperture to the cavity during a second mode of operation.
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公开(公告)号：US09758252B2
公开(公告)日：2017-09-12
申请号：US15077731
申请日：2016-03-22
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
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公开(公告)号：US20170254216A1
公开(公告)日：2017-09-07
申请号：US15059116
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Jeffrey Wayne Litzler
CPC classification number: F01D21/003 , F01D21/14 , F02C6/08 , F02C9/18 , F05D2260/80 , F05D2270/09
Abstract: A pipe fault detection system is provided for a gas turbine engine having a compressor and a turbine. The pipe fault detection system includes a cooling manifold configured to direct cooling air from the compressor to the turbine. The cooling manifold includes at least two cooling pipes, a sensor configured to detect an operating condition indicative of a pipe break, and a controller configured to control the amount of cooling air through the cooling manifold in response to the operating condition detected by the sensor.
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公开(公告)号：US20170191420A1
公开(公告)日：2017-07-06
申请号：US14986101
申请日：2015-12-31
Applicant: General Electric Company
Inventor： Brandon Christopher Clarke , Daniel Jean-Louis Laborie , Steven Edward Nolte , Erhan Turan
CPC classification number: F02C7/18 , F01D17/085 , F01D17/145 , F01D25/12 , F05D2260/20 , F05D2270/3032 , F05D2270/3062 , F05D2270/54 , F05D2270/80 , Y02T50/675
Abstract: A system for cooling an equipment compartment of a gas turbine engine includes a cooling manifold for directing cooling air from outside of the equipment compartment to within the equipment compartment, a temperature sensor disposed within the equipment compartment, an electronically controlled cooling valve configured to control the volume of air flowing through said cooling manifold, and a control unit configured to receive electronic data information from the temperature sensor and transmit electronic data information to the electronically controlled cooling valve based on electronic information received from said temperature sensor.
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公开(公告)号：US20160311546A1
公开(公告)日：2016-10-27
申请号：US15077731
申请日：2016-03-22
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
Abstract translation: 提供了一种用于减小涡轮发动机的多个转子叶片和涡轮发动机的护罩之间的涡轮机间隙的方法。 该方法包括确定飞机处于第一飞行状态，并且将涡轮机间隙间隙调整到与第一飞行状态相关联的第一间隙间隙距离。 该方法还包括确定对第二飞行状态的需求，以及调整发动机对功率参数的第一预定变化的第一发动机响应性的发动机响应性。 该方法还包括将引擎响应性从第一发动机响应级别降低到用于发动机的功率参数的第二预定变化的第二发动机响应性水平，并且在第二预定变化期间关闭与护罩相关联的间隙控制阀 发动机的功率参数。
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