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公开(公告)号：US11131244B2
公开(公告)日：2021-09-28
申请号：US15803063
申请日：2017-11-03
Applicant: General Electric Company
Inventor： Weize Kang , Richard Alan Wesling , Tod Robert Steen , Richard Schmidt
Abstract: A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.
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公开(公告)号：US20200056677A1
公开(公告)日：2020-02-20
申请号：US16103314
申请日：2018-08-14
Applicant: General Electric Company
Inventor： Richard Schmidt , Bugra Han Ertas , Weize Kang
Abstract: A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.
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公开(公告)号：US20240229715A9
公开(公告)日：2024-07-11
申请号：US18049112
申请日：2022-10-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Kudum Shinde , Surender Reddy Bhavanam , Weize Kang
CPC classification number: F02C7/06 , F01D25/16 , F05D2220/32 , F05D2240/52
Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.
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公开(公告)号：US11976593B1
公开(公告)日：2024-05-07
申请号：US18049112
申请日：2022-10-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Kudum Shinde , Surender Reddy Bhavanam , Weize Kang
CPC classification number: F02C7/06 , F01D25/16 , F01D25/162 , F01D25/164 , F05D2220/32 , F05D2240/52 , F16C19/54 , F16C19/541 , F16C25/083 , F16C27/066 , F16C2360/23
Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.
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公开(公告)号：US11808214B2
公开(公告)日：2023-11-07
申请号：US18058034
申请日：2022-11-22
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Narayanan Payyoor , Weize Kang , Brandon W. Miller , Bugra Ertas , Andrea Piazza
CPC classification number: F02C7/36 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2240/60 , F05D2260/40
Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.
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Patent Agency Ranking
公开(公告)号：US11795882B2
公开(公告)日：2023-10-24
申请号：US18152991
申请日：2023-01-11
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
CPC classification number: F02C7/36 , F02C7/06 , F05D2240/54 , F05D2240/61 , F05D2250/711 , F05D2300/603
Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
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公开(公告)号：US11591932B2
公开(公告)日：2023-02-28
申请号：US17387002
申请日：2021-07-28
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shivam Mittal , Bhujabal Prashant Mahadeo , Weize Kang , Richard Schmidt
IPC: F01D25/16 , F02C7/36 , F01D25/18 , F03G7/06 , F02C7/06 , F16C27/04 , F16C35/077 , F16C19/26 , F16C19/06
Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.
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公开(公告)号：US11092024B2
公开(公告)日：2021-08-17
申请号：US16155107
申请日：2018-10-09
Applicant: General Electric Company
Inventor： Arvind Namadevan , Weize Kang , Hari Shankar Thakur , Arnab Sen , Mayur Ghawat
Abstract: The present disclosure is directed to a system for mitigating rotor bow at a turbine engine. The system includes a casing circumferentially surrounding a rotor assembly in which a heat pipe is attached to the casing and extended circumferentially around the rotor assembly.
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公开(公告)号：US20190186289A1
公开(公告)日：2019-06-20
申请号：US15842168
申请日：2017-12-14
Applicant: General Electric Company
Inventor： Milind Chandrakant Dhabade , Kudum Shinde , Thomas Edward Agin , Weize Kang , Praveen Sharma , Shivam Mittal
CPC classification number: F01D21/12 , F01D5/02 , F01D17/10 , F05D2260/4023
Abstract: A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.
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公开(公告)号：US20240117770A1
公开(公告)日：2024-04-11
申请号：US18486523
申请日：2023-10-13
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
CPC classification number: F02C7/36 , F02C7/06 , F05D2240/54 , F05D2240/61 , F05D2250/711 , F05D2300/603
Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
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