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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：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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3.发明申请公开(公告)号：US20240369022A1
公开(公告)日：2024-11-07
申请号：US18440063
申请日：2024-02-13
Applicant: General Electric Company
Inventor： Kudum Shinde , Prateek Jalan , Sharad Pundik Patil , Ravindra Shankar Ganiger
Abstract: A torque extraction system for a turbine engine includes an electric machine coupled to a shaft of the turbine engine by way of a gearbox disposed between the electric machine and the shaft of the turbine engine, and the electric machine draws torque from the shaft and converts the torque to electrical energy. A power bus is electrically coupled to the electric machine and provides power to the electric machine. A sensor senses vibrational forces acting on a rotor of the turbine engine, and a controller electrically coupled to the electric machine receives signals from the sensor corresponding to the sensed vibrational forces. The controller operates the gearbox disposed between the electric machine and the shaft of the turbine engine to increase the torque that the electric machine draws from the shaft when the vibrational forces sensed by the sensor meet or exceed a predetermined threshold.
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公开(公告)号：US12241372B2
公开(公告)日：2025-03-04
申请号：US18497202
申请日：2023-10-30
Applicant: General Electric Company
Inventor： Grant Portune , Steven Douglas Johnson , Bryan Jung Woo Hong , Prateek Jalan , Ravindra Shankar Ganiger , Narendra Hardikar , David Yamarthi
Abstract: A seal assembly for a gas turbine includes a seal case, and a seal shoe arranged within the seal case. The seal shoe includes a main seal portion that is configured to engage with a radial bearing engagement portion of a rotor shaft, a radial bearing surface that engages with the radial bearing engagement portion of the rotor shaft, at least one hydrodynamic lift cavity extending through the radial bearing surface, and at least one airflow passage extending from a first side of the seal shoe through the at least one hydrodynamic lift cavity and providing airflow communication between the first side of the seal shoe and the at least one hydrodynamic lift cavity.
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公开(公告)号：US20240384661A1
公开(公告)日：2024-11-21
申请号：US18497202
申请日：2023-10-30
Applicant: General Electric Company
Inventor： Grant Portune , Steven Douglas Johnson , Bryan Jung Woo Hong , Prateek Jalan , Ravindra Shankar Ganiger , Narendra Hardikar , David Yamarthi
Abstract: A seal assembly for a gas turbine includes a seal case, and a seal shoe arranged within the seal case. The seal shoe includes a main seal portion that is configured to engage with a radial bearing engagement portion of a rotor shaft, a radial bearing surface that engages with the radial bearing engagement portion of the rotor shaft, at least one hydrodynamic lift cavity extending through the radial bearing surface, and at least one airflow passage extending from a first side of the seal shoe through the at least one hydrodynamic lift cavity and providing airflow communication between the first side of the seal shoe and the at least one hydrodynamic lift cavity.
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Patent Agency Ranking
公开(公告)号：US20240318570A1
公开(公告)日：2024-09-26
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
CPC classification number: F01D11/025 , F05D2240/53 , F05D2240/55 , F05D2260/38
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：US12116896B1
公开(公告)日：2024-10-15
申请号：US18189408
申请日：2023-03-24
Applicant: General Electric Company
Inventor： Grant Robert Portune , Steven Douglas Johnson , Mallikarjun Metri , Ajith Jogi , Pratish Patil , Nageswar Rao Ganji , Rahul Anil Bidkar , Prateek Jalan , Ravindra Shankar Ganiger , David Raju Yamarthi , Narendra Anand Hardikar , Chandrashekhar Kandukuri
CPC classification number: F01D11/001 , F01D11/025 , F01D11/04 , F01D25/22 , F16J15/40 , F16J15/445 , F16J15/164
Abstract: A turbine engine is provided. The gas 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 plurality of seal segments, the plurality of seal segments having a 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 comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.
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公开(公告)号：US12006833B2
公开(公告)日：2024-06-11
申请号：US17929554
申请日：2022-09-02
Applicant: General Electric Company
Inventor： Prateek Jalan , Kudum Shinde , Milind Dhabade , Ravindra Shankar Ganiger , Tyler F. Hooper
IPC: F01D5/02
CPC classification number: F01D5/027 , F05D2220/323 , F05D2240/60 , F05D2260/96
Abstract: A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.
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公开(公告)号：US20240133308A1
公开(公告)日：2024-04-25
申请号：US18315736
申请日：2023-05-10
Applicant: General Electric Company
Inventor： David Yamarthi , Prateek Jalan , Grant Portune , Steven Douglas Johnson , Mark L. Hopper , Richard A. Wesling , Ravindra Shankar Ganiger
CPC classification number: F01D11/001 , F01D11/025
Abstract: A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.
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公开(公告)号：US20240026822A1
公开(公告)日：2024-01-25
申请号：US17869060
申请日：2022-07-20
Applicant: General Electric Company
Inventor： Lakshmi Narasimharao Jagata , Prateek Jalan , Veeraraju Vanapalli , Atanu Saha , Scott Alan Schimmels
IPC: F02C7/18
CPC classification number: F02C7/18 , F05D2260/213 , F05D2220/323
Abstract: A gas turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement to define a diffuser cavity between the compressor section and the combustor section, and an aft cavity. A compressor discharge pressure duct fluidly draws air from the diffuser cavity, passes it through a heat exchanger to cool the air, and then supplies the cooled air to the aft cavity.
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