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公开(公告)号：US20220098999A1
公开(公告)日：2022-03-31
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 , F02C7/06 , F16C27/04 , F16C35/077 , F16C19/26 , F16C19/06 , F03G7/06
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：US20210156279A1
公开(公告)日：2021-05-27
申请号：US16697350
申请日：2019-11-27
Applicant: General Electric Company
Inventor： Shashank Suresh Puranik , Bhaskar Nanda Mondal , Richard Schmidt , Peeyush Pankaj , Narayanan Payyoor
IPC: F01D25/16 , F04D29/059
Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
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33.发明授权公开(公告)号：US10669893B2
公开(公告)日：2020-06-02
申请号：US15605351
申请日：2017-05-25
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, an axial centerline extended along the longitudinal direction, an upstream end and a downstream end opposite of the upstream end along the longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes a high speed turbine rotor coupled to a high pressure (HP) shaft and HP compressor, a low speed turbine rotor comprising an axially extended hub, and a first turbine bearing disposed radially between the low speed turbine rotor and the high speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit through the high speed turbine rotor. The low speed turbine rotor includes a rotating nozzle adjacent to the turbine cooling conduit. The first turbine bearing defines an outer air bearing and an inner air bearing. The first turbine bearing defines a stationary nozzle adjacent to the rotating nozzle of the first turbine rotor.
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公开(公告)号：US20190338675A1
公开(公告)日：2019-11-07
申请号：US15967885
申请日：2018-05-01
Applicant: General Electric Company
Inventor： Richard Schmidt
Abstract: A static support structure including a plurality of members extended along a lengthwise direction coupled to a support body. Each of the plurality of members is disposed in adjacent arrangement along a load direction. Each adjacent pair of members defines a gap therebetween. The plurality of members provides a nonlinear force versus deflection of the static support structure.
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公开(公告)号：US20190085702A1
公开(公告)日：2019-03-21
申请号：US15710164
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt , Bhaskar Nanda Mondal
Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
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Patent Agency Ranking
36.发明申请公开(公告)号：US20180340446A1
公开(公告)日：2018-11-29
申请号：US15605225
申请日：2017-05-25
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor including a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor including a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; and a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit extended within the high speed turbine rotor. The first turbine bearing defines an outer air bearing along an outer diameter of the first turbine bearing and adjacent to the hub of the low speed turbine rotor. The first turbine bearing defines an inner air bearing along an inner diameter of the first turbine bearing and adjacent to the HP shaft. The first turbine bearing further defines a cooling orifice adjacent along the longitudinal direction to the turbine cooling conduit of the high speed turbine rotor. The cooling orifice and the turbine cooling conduit are in fluid communication.
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公开(公告)号：US20180209336A1
公开(公告)日：2018-07-26
申请号：US15412175
申请日：2017-01-23
Applicant: General Electric Company
Inventor： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end long the longitudinal direction. The gas turbine engine includes a turbine section including a low speed turbine rotor, a high speed turbine rotor, and an intermediate speed turbine rotor. The low speed turbine rotor includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction. The outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction. The low speed turbine rotor further includes at least one connecting airfoil coupling the inner shroud to the outer shroud. The high speed turbine rotor is disposed upstream of the one or more connecting airfoils of the low speed turbine rotor along the longitudinal direction. The high speed turbine rotor includes a plurality of high speed turbine airfoils extended outward in the radial direction. The intermediate speed turbine rotor is disposed upstream of the one or more connecting airfoils of the low speed turbine rotor along the longitudinal direction. The intermediate speed turbine rotor includes a plurality of intermediate speed turbine airfoils extended outward in the radial direction. The intermediate speed turbine rotor is disposed among the plurality of outer shroud airfoils of the low speed turbine rotor along the longitudinal direction.
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公开(公告)号：US11940032B2
公开(公告)日：2024-03-26
申请号：US16103314
申请日：2018-08-14
Applicant: General Electric Company
Inventor： Richard Schmidt , Bugra Han Ertas , Weize Kang
CPC classification number: F16F15/16 , F01D25/164 , F16C2360/23
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：US11879498B2
公开(公告)日：2024-01-23
申请号：US17140925
申请日：2021-01-04
Applicant: General Electric Company
Inventor： Richard Schmidt , Narayanan Payyoor , Peeyush Pankaj
CPC classification number: F16C27/045 , F01D5/26 , F01D25/164 , F05D2260/96
Abstract: A rotor damping device for a turbomachine is provided. The rotor damping device includes a first fluid damper; and a second damper in communication with the first fluid damper, the second damper comprising a wire mesh, wherein the first fluid damper is transitionable between a working condition and an interruption condition, and wherein, during the interruption condition, the wire mesh of the second damper dampens vibration of the turbomachine.
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公开(公告)号：US11603801B2
公开(公告)日：2023-03-14
申请号：US17328795
申请日：2021-05-24
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
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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