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公开(公告)号：US09500100B2
公开(公告)日：2016-11-22
申请号：US14396784
申请日：2013-04-22
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D25/164 , F16C19/04 , F16C19/06 , F16C27/045 , F16C43/04 , F16C2360/23 , Y02T50/671 , Y10T29/49229
Abstract: A damper bearing assembly for a gas turbine engine is disclosed. The damper bearing assembly is designed to define forward and aft axial gaps which allow for normal deflection under standard operating thrust loads, but then close during a fan blade out event to allow the increased load to transfer to the damper housing. Frictional forces between contacting parts limit torsional windup and increase torsional resistance with increasing load. The damper bearing assembly includes a damper housing configured substantially within a U-shaped spring finger housing and a spanner nut with a radial hook portion coupled to the spring finger housing. The damper housing is coupled to the spring finger housing such that it is substantially confined within the U-shaped void. The spanner nut is coupled to the spring finger housing such that the radial hook portion is configured to limit the deflection of the spring finger housing and damper housing during a fan blade out event.
Abstract translation: 公开了一种用于燃气涡轮发动机的阻尼器轴承组件。 减震器轴承组件被设计成限定前后轴向间隙，其允许在标准操作推力载荷下的正常偏转，但是在风扇叶片移出事件期间关闭，以允许增加的负载传递到阻尼器壳体。 接触部件之间的摩擦力限制了扭转卷绕，并且随着负载的增加而增加了扭转阻力。 阻尼器轴承组件包括阻尼器壳体，该阻尼器壳体基本上构造在U形弹簧指壳体内，并且扳手螺母具有联接到弹簧指壳体的径向钩部分。 阻尼器壳体联接到弹簧指壳体，使得其基本上限制在U形空隙内。 扳手螺母联接到弹簧指壳体，使得径向钩部分构造成在风扇叶片脱出事件期间限制弹簧指壳体和阻尼器壳体的偏转。
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公开(公告)号：US12297743B2
公开(公告)日：2025-05-13
申请号：US18362346
申请日：2023-07-31
Applicant: General Electric Company
Inventor： David Yamarthi , Tod R. Steen , Ravindra Shankar Ganiger , Kudum Shinde , Ankita Sinha , Aman Srivastava , Narayanan Payyoor , Venkata Subramanya Sarma Devarakonda , Rajesh Kumar Undipalli , Dinesh Rakwal , Himanshu Gupta , Hrishi Ragesh
Abstract: A gas turbine engine includes a fan section having a plurality of fan blades, the fan section configured to generate an airflow through the gas turbine engine, an airflow passage having a core passage and a bypass passage separate from the core passage, a low-speed shaft coupled to and configured to rotate the plurality of fan blades, and a sensor assembly coupled to the gas turbine engine and configured to detect torsional vibration in the low-speed shaft. The sensor assembly includes a plurality of dynamic pressure sensors in the airflow passage. The plurality of dynamic pressure sensors detect a dynamic pressure of the airflow passage that is indicative of the torsional vibration in the low-speed shaft. A damping system is configured to dampen the torsional vibration in the low-speed shaft based on a correlation of a measured torsional vibration and an experimental torsional vibration.
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公开(公告)号：US12281577B2
公开(公告)日：2025-04-22
申请号：US18657420
申请日：2024-05-07
Applicant: General Electric Company
Inventor： Raghuveer Chinta , Abhijit Roy , Vaishnav Raghuvaran , Srinivas Nuthi , Ravindra Shankar Ganiger
IPC: F01D11/22
Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction; a second annular substrate positioned radially inward relative to the first annular substrate, the second annular substrate movably coupled to the first annular substrate; and an actuator coupled to the second annular substrate such that a force applied by the actuator moves the second annular substrate relative to the first annular substrate to adjust a tip clearance.
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公开(公告)号：US20250075664A1
公开(公告)日：2025-03-06
申请号：US18952677
申请日：2024-11-19
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor H. Wood , Giridhar Jothiprasad , Nageswar Ganji , Hiranya Kumar Nath , Ravindra Shankar Ganiger , Ambika Shivamurthy
Abstract: Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.
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公开(公告)号：US12241379B2
公开(公告)日：2025-03-04
申请号：US18217913
申请日：2023-07-03
Applicant: General Electric Company
Inventor： Nageswar Ganji , Ravindra Shankar Ganiger , Hiranya Nath , Jonathan K. Remer
Abstract: This disclosure is directed to cooling systems for turbomachine seal assemblies. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. During operation of the turbomachine, the components of the seal assemblies generate heat, which is removed from the seal assembly by the cooling systems of this disclosure. In some examples, the cooling system includes a reservoir of lubricant that is distributed to a face of one of the components of the seal assembly. In other examples, the cooling system includes a lattice structure capable of retaining lubricant against the components of the seal assembly, or a pressurized jet of lubricant directed against the components of the seal assembly. The cooling systems can further include a combination of deflectors, hairpin members, and channels for distributing the lubricant to the components of the seal assemblies.
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Patent Agency Ranking
公开(公告)号：US12241375B2
公开(公告)日：2025-03-04
申请号：US18189379
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , David Raju Yamarthi , Chandrashekhar Kandukuri , Deepak Trivedi , Narendra Anand Hardikar , Vidyashankar Ramasastry Buravalla , Steven Douglas Johnson , Amit Goyal , Grant Robert Portune , Himanshu Gupta , Srinivasan Swaminathan , Shalini Thimmegowda , Guru Venkata Dattu Jonnalagadda , Shalabh Saxena , Prateek Jalan
IPC: F01D11/02
Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.
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公开(公告)号：US20250067438A1
公开(公告)日：2025-02-27
申请号：US18536610
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Michael David Clark
Abstract: A heat shield for a combustor of a gas turbine engine. The heat shield includes an annular ring having an axial direction, a radial direction, and a circumferential direction. The annular ring includes a plurality of circumferential segments. Each circumferential segment of the plurality of circumferential segments is disconnected from an adjacent circumferential segment of the plurality of circumferential segments to allow for thermal growth of each circumferential segment during operation of the combustor.
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公开(公告)号：US12215588B2
公开(公告)日：2025-02-04
申请号：US18190403
申请日：2023-03-27
Applicant: General Electric Company
Inventor： Tajinder Singh , Rajesh Kumar , David Raju Yamarthi , Bryan Jung Woo Hong , Narendra Anand Hardikar , Ravindra Shankar Ganiger , Jeffrey Douglas Rambo
IPC: F01D11/10
Abstract: A turbine engine includes a rotor, a stator, and a seal assembly disposed between the rotor and the stator. The seal assembly includes seal segment. The seal segment includes a seal face that is configured to form a fluid bearing with the rotor. A lift channel extends within the seal segment from an opening on the seal face. The turbine engine further includes a spring assembly disposed within the lift channel. The spring assembly including a biasing element and a piston element coupled to the biasing element. The lift channel includes a lift volume portion extending is between the opening and the piston element. The piston element is movable within the lift channel based on a pressure within the fluid bearing to adjust a size of the lift volume portion.
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公开(公告)号：US12215587B2
公开(公告)日：2025-02-04
申请号：US18189424
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Narendra Anand Hardikar , David Raju Yamarthi , Rahul Anil Bidkar , Ravindra Shankar Ganiger , Prateek Jalan , Deepak Trivedi
Abstract: A turbine engine is provided. The turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a first seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprising a prestressed spring assembly extending from the seal segment for biasing the seal segment along the radial direction.
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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
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.
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