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Patent Agency Ranking
公开(公告)号：US20240229656A9
公开(公告)日：2024-07-11
申请号：US17970687
申请日：2022-10-21
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nicholas M. Daggett , Nitesh Jain , Matthew Mark Weaver , Srinivas Addagatla
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/323 , F05D2240/30
Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
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公开(公告)号：US20230249838A1
公开(公告)日：2023-08-10
申请号：US17665286
申请日：2022-02-04
Applicant: General Electric Company
Inventor： Srinivas Addagatla , Ravindra Shankar Ganiger , Anil Soni , Sharad Tiwari , Jonathan E. Coleman
CPC classification number: B64D27/26 , F01D25/28 , B64D2027/262 , B64D2027/268 , F05D2220/323 , F05D2240/90
Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.
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公开(公告)号：US20240133301A1
公开(公告)日：2024-04-25
申请号：US17970687
申请日：2022-10-20
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nicholas M. Daggett , Nitesh Jain , Matthew Mark Weaver , Srinivas Addagatla
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/323 , F05D2240/30
Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
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公开(公告)号：US20240124147A1
公开(公告)日：2024-04-18
申请号：US17964982
申请日：2022-10-13
Applicant: General Electric Company
Inventor： William Joseph Bowden , Jonathan Edward Coleman , Sharad Tiwari , Srinivas Addagatla , Sara Elizabeth Carle
CPC classification number: B64D27/12 , B64D27/26 , F02C7/20 , F05D2220/323 , F05D2240/90
Abstract: A gas turbine engine includes an aft frame and a forward frame disposed upstream from the aft frame. The forward frame includes an outer ring. The outer ring includes an inner surface that is radially spaced from an outer surface. A first indention is defined in the outer surface, and a first engine mount flange protrudes radially outwardly from the first indention.
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公开(公告)号：US11884410B2
公开(公告)日：2024-01-30
申请号：US17665286
申请日：2022-02-04
Applicant: General Electric Company
Inventor： Srinivas Addagatla , Ravindra Shankar Ganiger , Anil Soni , Sharad Tiwari , Jonathan E. Coleman
CPC classification number: B64D27/26 , F01D25/28 , B64D2027/262 , B64D2027/268 , F05D2220/323 , F05D2240/90
Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.
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