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公开(公告)号：US12221892B2
公开(公告)日：2025-02-11
申请号：US18463970
申请日：2023-09-08
Applicant: General Electric Company
Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
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公开(公告)号：US11773741B2
公开(公告)日：2023-10-03
申请号：US17343454
申请日：2021-06-09
Applicant: General Electric Company
CPC classification number: F01D11/127 , F01D11/14 , F05D2240/11 , F05D2250/183 , F05D2260/38 , F05D2270/114 , F05D2270/42
Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
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公开(公告)号：US20230235679A1
公开(公告)日：2023-07-27
申请号：US17704581
申请日：2022-03-25
Applicant: General Electric Company
Inventor： Praveen Sharma , Ravindra Shankar Ganiger , Milind Chandrakant Dhabade
CPC classification number: F01D11/127 , F01D25/04 , F05D2240/11 , F05D2250/711 , F05D2250/712 , F05D2260/96
Abstract: Curved beams stacked structures-compliant shrouds for gas turbine engines are disclosed. An example shroud assembly comprising a plurality of concave curved beams, a plurality of convex curved beams, and a plurality of bumpers, wherein a first concave curved beam of the plurality of concave curved beams is inversely coupled to a first convex curved beam of the plurality of convex curved beams, a second concave curved beam of the plurality of concave curved beams, inversely coupled to a second convex curved beam of the plurality of convex curved beams, the first and second concave curved beams configured to stack on top of the first and second convex curved beams, a first bumper of the plurality of bumpers coupled to the first and second concave curved beams, and a second bumper of the plurality of bumpers coupled to the first and second convex curved beams.
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公开(公告)号：US20230008935A1
公开(公告)日：2023-01-12
申请号：US17408986
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray , Ravindra Shankar Ganiger , Praveen Sharma
Abstract: An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.
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公开(公告)号：US20220098999A1
公开(公告)日：2022-03-31
申请号：US17387002
申请日：2021-07-28
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shivam Mittal , Bhujabal Prashant Mahadeo , Weize Kang , Richard Schmidt
IPC: F01D25/16 , F02C7/36 , F01D25/18 , F02C7/06 , F16C27/04 , F16C35/077 , F16C19/26 , F16C19/06 , F03G7/06
Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.
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Patent Agency Ranking
公开(公告)号：US20190162077A1
公开(公告)日：2019-05-30
申请号：US15823631
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shuvajyoti Ghosh , Ravindra Shankar Ganiger , Praveen Sharma , Ishita Sehgal , Prashant Bhujabal , Shivam Mittal
IPC: F01D25/16
Abstract: A support system for a gas turbine engine is provided. The support system includes a load-bearing unit that includes a first flange, a support element supporting the load-bearing unit and having a second flange, a fastener connecting the first flange and the second flange, a first super-elastic shape memory alloy component in contact with the first flange, and a second super-elastic shape memory alloy component in contact with the second flange. The first and the second super-elastic shape memory alloy components are configured to deform when a load exerted by the fastener exceeds a threshold load value of the fastener.
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公开(公告)号：US20190128329A1
公开(公告)日：2019-05-02
申请号：US16226211
申请日：2018-12-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shuvajyoti Ghosh , Akash Joshi , Shivaram AC , Ravindra Shankar Ganiger , Praveen Sharma
IPC: F16C39/02 , F01D21/08 , F01D25/16 , F16C29/12 , F16C35/077 , F16C35/067
Abstract: A load reduction assembly includes an annular bearing cone configured to extend between a bearing assembly and a frame assembly and form a first load path therebetween. The load reduction assembly further includes an annular recoupler member configured to extend between the bearing assembly and the frame assembly and form a second load path therebetween. The second load path is parallel to the first load path. The recoupler member includes a shape memory alloy configured to change stiffness in response to a change in a stress condition, thereby regulating an imbalance condition of a rotor shaft coupled to the bearing assembly.
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公开(公告)号：US20180112554A1
公开(公告)日：2018-04-26
申请号：US15331158
申请日：2016-10-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shuvajyoti Ghosh , Akash Joshi , Shivaram AC , Ravindra Shankar Ganiger , Praveen Sharma
IPC: F01D25/16 , F01D5/02 , F16C35/077 , F16C39/02
CPC classification number: F16C39/02 , F01D21/08 , F01D25/164 , F05D2260/15 , F05D2300/505 , F16C29/123 , F16C35/067 , F16C35/077 , F16C2202/06 , F16C2202/28 , F16C2360/23 , Y02T50/671
Abstract: A load reduction assembly includes an annular bearing cone configured to extend between a bearing assembly and a frame assembly and form a first load path therebetween. The load reduction assembly further includes an annular recoupler member configured to extend between the bearing assembly and the frame assembly and form a second load path therebetween. The second load path is parallel to the first load path. The recoupler member includes a shape memory alloy configured to change stiffness in response to a change in a stress condition, thereby regulating an imbalance condition of a rotor shaft coupled to the bearing assembly.
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公开(公告)号：US12188358B2
公开(公告)日：2025-01-07
申请号：US18325621
申请日：2023-05-30
Applicant: General Electric Company
Inventor： Santosh Potnuru , Pradeep Hemant Sangli , Ravindra Shankar Ganiger , Praveen Sharma , Scott Alan Schimmels
Abstract: A seal assembly for a rotary machine. The seal assembly includes a rotor and a stator. The rotor is rotatable about a rotational axis and has a rotor seal face. The stator has a stator seal face. The stator seal face is positioned opposite the rotor seal face and faces the rotor seal face with a gap therebetween. A portion of one of the rotor and the stator is formed of (i) a shape memory alloy or (ii) a first metal and a second metal with the second metal having a coefficient of thermal expansion different from the first metal. The seal assembly is characterized by a seal clearance compliance ratio (SCCR) from 20% to 90%.
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公开(公告)号：US11674397B2
公开(公告)日：2023-06-13
申请号：US16950940
申请日：2020-11-18
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Naleen Kumar Verma , Nicholas Joseph Kray
CPC classification number: F01D5/10 , F01D25/164 , F05D2240/50 , F05D2250/14 , F05D2260/96
Abstract: A variable stiffness damper system including an inner spring positioned between a first wall and a second wall, in which the inner spring includes a first member and a second member each coupled together at a distal end by an inner bumper. The first member and the second member are each contoured toward one another. The first member, the second member, and the inner bumper form a cavity therebetween. An outer spring is positioned between the inner spring and the first wall or the second wall. The outer spring includes a spring arm contoured toward the inner spring. The outer spring includes an outer bumper positioned between the inner bumper and the first wall or the second wall. The inner bumper and the outer bumper are selectively couplable to one another based on a load applied to the damper system.
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