公开(公告)号：US20240084737A1

公开(公告)日：2024-03-14

申请号：US18510848

申请日：2023-11-16

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/32 ,  F01D5/02 ,  F01D25/34

CPC classification number: F02C7/32 ,  F01D5/02 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/20 ,  F05D2260/941

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

公开(公告)号：US11891905B2

公开(公告)日：2024-02-06

申请号：US17644475

申请日：2021-12-15

Applicant: General Electric Company

Inventor： Prashant Bhujabal ,  Ravindra Shankar Ganiger ,  Narayanan Payyoor ,  Mohankumar Banakar ,  Weize Kang

IPC: F01D25/16 ,  F01D5/06 ,  F02C7/06

CPC classification number: F01D25/162 ,  F01D5/06 ,  F02C7/06 ,  F05D2240/54 ,  F05D2240/61 ,  F05D2260/40311

Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

公开(公告)号：US11821371B1

公开(公告)日：2023-11-21

申请号：US17816018

申请日：2022-07-29

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/32 ,  F01D25/34 ,  F01D5/02

CPC classification number: F02C7/32 ,  F01D5/02 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/20 ,  F05D2260/941

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

公开(公告)号：US20230160346A1

公开(公告)日：2023-05-25

申请号：US18152991

申请日：2023-01-11

Applicant: General Electric Company

Inventor： Narayanan Payyoor ,  Weize Kang ,  Thomas Lee Becker ,  Richard Schmidt

IPC: F02C7/36 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F05D2300/603 ,  F05D2240/54 ,  F05D2250/711 ,  F05D2240/61

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.

公开(公告)号：US20220373019A1

公开(公告)日：2022-11-24

申请号：US17328800

申请日：2021-05-24

Applicant: General Electric Company

Inventor： Narayanan Payyoor ,  Weize Kang ,  Thomas Lee Becker ,  Richard Schmidt

IPC: F16C3/02 ,  F02C7/06

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.

公开(公告)号：US20220372917A1

公开(公告)日：2022-11-24

申请号：US17328795

申请日：2021-05-24

Applicant: General Electric Company

Inventor： Narayanan Payyoor ,  Weize Kang ,  Thomas Lee Becker ,  Richard Schmidt

IPC: F02C7/36 ,  F02C7/06

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.

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.

公开(公告)号：US10677087B2

公开(公告)日：2020-06-09

申请号：US15977006

申请日：2018-05-11

Applicant: General Electric Company

Inventor： Weize Kang

IPC: F01D21/00 ,  F01D25/16 ,  F16M13/02 ,  F16F15/023

Abstract: A gas turbine engine including a support structure including a conduit coupled to a static support. The conduit defines an end wall between which a fluid is contained within a volume defined by the conduit. An effort variable provided to the support structure modulates a stiffness of the support structure.

公开(公告)号：US12209540B2

公开(公告)日：2025-01-28

申请号：US18510848

申请日：2023-11-16

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/32 ,  F01D5/02 ,  F01D25/34

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

公开(公告)号：US20240271565A1

公开(公告)日：2024-08-15

申请号：US18644554

申请日：2024-04-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/06 ,  F01D25/16 ,  F16C19/54 ,  F16C25/08 ,  F16C27/06

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.