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

IPC: F02C7/06 ,  F01D25/16

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.

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

IPC: F01D25/16 ,  F02C7/06 ,  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.

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.

公开(公告)号：US20240133342A1

公开(公告)日：2024-04-25

申请号：US18049112

申请日：2022-10-23

Applicant: General Electric Company

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

IPC: F02C7/06 ,  F01D25/16

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.

公开(公告)号：US12173611B2

公开(公告)日：2024-12-24

申请号：US17808211

申请日：2022-06-22

Applicant: General Electric Company

Inventor： Vignesh Selvam ,  Raghavendra Muralidhar ,  Surender Reddy Bhavanam

IPC: F01D25/28 ,  F01D25/04

Abstract: A device for balancing a shaft in a turbomachine engine includes an annular insert configured to be positioned inside the shaft at any axial position along the shaft, and a weight that is attached to the annular insert at any angular position inside the shaft.

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：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：US20250043795A1

公开(公告)日：2025-02-06

申请号：US18517240

申请日：2023-11-22

Applicant: General Electric Company

Inventor： Kudum Shinde ,  Surender Reddy Bhavanam

IPC: F04D27/00 ,  F02C7/057

Abstract: A gas turbine engine including a frame, a plurality of fan blades configured to rotate about a longitudinal centerline axis of the gas turbine engine, and a mounting assembly coupling the frame to a structure. The gas turbine engine includes a sensor assembly coupled to the mounting assembly and having at least one sensor configured to detect a loading on the mounting assembly and to take a corrective action when propeller whirl is detected above a predetermined limit, and a feature configured to take a corrective action when propeller whirl is detected above a predetermined limit.

公开(公告)号：US20240240570A1

公开(公告)日：2024-07-18

申请号：US18452030

申请日：2023-08-18

Applicant: General Electric Company

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

IPC: F01D17/16 ,  F01D7/00

CPC classification number: F01D17/16 ,  F01D7/00 ,  F05D2260/70 ,  F05D2270/334

Abstract: A high-pressure (HP) rotor control system includes an HP rotor and a controller. The HP rotor includes a plurality of rotor blades that rotate about a centerline axis, and a plurality of variable stator vanes (VSVs) that are rotatable about a variable stator vane (VSV) pitch axis. The plurality of VSVs are disposed at an incidence angle. The controller controls the plurality of VSVs to rotate the plurality of VSVs about the VSV pitch axis to change the rotor incidence angle of the plurality of VSVs as the HP rotor approaches a thrust crossover condition.