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公开(公告)号：US12281582B2
公开(公告)日：2025-04-22
申请号：US18046651
申请日：2022-10-14
Applicant: General Electric Company
Inventor： Illya Emmanuel Arcos Perez , Ashish Rajput , Amarnath Kakarla , Narayanan Payyoor , Abhijeet Yadav , Abhishek Goverdhan , Balaraju Suresh , Ricardo Hernandez Pandeli , Suryarghya Chakrabarti , Nicholas M. Daggett , Gary W. Bryant
Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.
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公开(公告)号：US20250153854A1
公开(公告)日：2025-05-15
申请号：US18441853
申请日：2024-02-14
Applicant: General Electric Company
Inventor： Abhishek Goverdhan , Abhijeet Jayshingrao Yadav , Andrew Bryan Cannella , Richa Awasthi , Rangasai M C , Pamela M. Boehm , Narayanan P , Saswati Roy
Abstract: Active control apparatus of gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of an unducted gas turbine engine to a pylon, the apparatus includes a mount system; a plurality of sensors to measure at least one parameter indicating propeller whirl stability; and a controller to tune a stiffness of the mount system depending on a function of the at least one parameter measured by the plurality of sensors, the controller to tune the stiffness of the mount system by signaling an actuator, the mount system including: a first linkage; a second linkage; a first pin; a second pin; an interface to engage with the first and second linkages, the interface to at least one of rotate or slide; and the actuator to cause the interface to engage with the first and second linkages based on the signaling from the controller.
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公开(公告)号：US10583913B2
公开(公告)日：2020-03-10
申请号：US15458354
申请日：2017-03-14
Applicant: General Electric Company
Inventor： Abhishek Goverdhan , Ravindra Shankar Ganiger , Richa Awasthi , Viswanadha Gupta Sakala , Vidya Lokammanahalli Shivashankar
Abstract: An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.
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Patent Agency Ranking
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：US20180265181A1
公开(公告)日：2018-09-20
申请号：US15458354
申请日：2017-03-14
Applicant: General Electric Company
Inventor： Abhishek Goverdhan , Ravindra Shankar Ganiger , Richa Awasthi , Viswanadha Gupta Sakala , Vidya Lokammanahalli Shivashankar
Abstract: An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.
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公开(公告)号：US12270308B2
公开(公告)日：2025-04-08
申请号：US18493508
申请日：2023-10-24
Applicant: General Electric Company
Inventor： Naveena K P , Ravindra Shankar Ganiger , Domala Uma Maheshwar , Kishore Budumuru , Kudum Shinde , Abhishek Goverdhan
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：US20230407759A1
公开(公告)日：2023-12-21
申请号：US18046651
申请日：2022-10-14
Applicant: General Electric Company
Inventor： Illya Emmanuel Arcos Perez , Ashish Rajput , Amarnath Kakarla , Narayanan Payyoor , Abhijeet Yadav , Abhishek Goverdhan , Balaraju Suresh , Ricardo Hernandez Pandeli , Suryarghya Chakrabarti , Nicholas M. Daggett , Gary W. Bryant
CPC classification number: F01D15/12 , B64D35/04 , F01D7/00 , F05D2260/70 , F05D2220/36
Abstract: An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.
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公开(公告)号：US11808157B1
公开(公告)日：2023-11-07
申请号：US17899324
申请日：2022-08-30
Applicant: General Electric Company
Inventor： Naveena K P , Ravindra Shankar Ganiger , Domala Uma Maheshwar , Kishore Budumuru , Kudum Shinde , Abhishek Goverdhan
CPC classification number: F01D11/24 , F01D25/10 , F01D25/24 , F05D2240/11 , F05D2260/20 , F05D2260/50 , F05D2270/821 , F05D2300/50212
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 defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.
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