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公开(公告)号：US20240052752A1
公开(公告)日：2024-02-15
申请号：US18493508
申请日：2023-10-24
Applicant: General Electric Company
Inventor： Naveena KP , Ravindra Shankar Ganiger , Domala Uma Maheshwar , Kishore Budumuru , Kudum Shinde , Abhishek Goverdhan
CPC classification number: F01D11/24 , F01D25/24 , F01D25/10 , F05D2240/11 , F05D2260/50 , F05D2300/50212 , F05D2270/821 , F05D2260/20
Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate including a first surface and a second surface that is radially inward relative to the first surface; an actuator structure coupled to the second surface of the annular substrate; and a smart structure cantilevered from the second surface of the annular substrate, the smart structure including: a support structure, a first region of the support structure coupled to the second surface of the annular substrate, a second region of the support structure coupled to the actuator structure; and a radially inward surface defining a variable surface, the support structure to move the variable surface in a radial direction.
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公开(公告)号：US11549392B2
公开(公告)日：2023-01-10
申请号：US15842168
申请日：2017-12-14
Applicant: General Electric Company
Inventor： Milind Chandrakant Dhabade , Kudum Shinde , Thomas Edward Agin , Weize Kang , Praveen Sharma , Shivam Mittal
IPC: F01D21/12 , F01D17/10 , F01D5/02 , F01D25/36 , F01D19/02 , F02C7/32 , F02C7/268 , F02C6/14 , F02C7/275
Abstract: A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.
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3.发明申请
公开(公告)号：US20210381433A1
公开(公告)日：2021-12-09
申请号：US16893546
申请日：2020-06-05
Applicant: General Electric Company
Inventor： Kudum Shinde , Ajit Kumar Verma
Abstract: A system for modulating airflow into a bore defined by a rotor of a gas turbine engine defining an axial direction, a circumferential direction, and a radial direction is provided. The system includes a movable member positioned forward of a first stage of rotor blades of the rotor. The movable member is movable between at least a first position and a second position to modulate airflow into the bore via a plurality of opening in fluid communication with the bore.
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公开(公告)号：US20210261262A1
公开(公告)日：2021-08-26
申请号：US16797078
申请日：2020-02-21
Applicant: General Electric Company
Inventor： Timothy Leo Schelfaut , Anthony Michael Metz , Jonathan Edward Coleman , Thomas P. Joseph , Michael C. Borner , Mahesh Khandeparker , Kudum Shinde
IPC: B64D27/26
Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle θ of at least one of the plurality of engine-mounting links.
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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
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.
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公开(公告)号：US20250043692A1
公开(公告)日：2025-02-06
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：US12078105B2
公开(公告)日：2024-09-03
申请号：US18081217
申请日：2022-12-14
Applicant: General Electric Company
Inventor： Pankaj Dhaka , Kudum Shinde , Paul Mathew , Gautam Naik , Vidyashankar Ramasastry Buravalla
IPC: F02C7/18
CPC classification number: F02C7/18 , F05D2260/232
Abstract: A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.
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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
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.
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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：US20240159157A1
公开(公告)日：2024-05-16
申请号：US18158618
申请日：2023-01-24
Applicant: General Electric Company
Inventor： Kudum Shinde , Sesha Subramanian , Yashpal Patel
CPC classification number: F01D9/06 , F02C6/08 , F02C9/18 , F05D2220/323 , F05D2240/14 , F05D2260/232 , F05D2260/605 , F05D2260/606
Abstract: A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall.
