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公开(公告)号：US20220372884A1
公开(公告)日：2022-11-24
申请号：US17328706
申请日：2021-05-24
Inventor： Nicholas J. Kray , Nicholas M. Daggett , Frank Worthoff , Damian Osowski
IPC: F01D5/32
Abstract: Preload sleeves and/or other retainers for a collet-mounted blade dovetail and/or other root are disclosed. An example turbofan for an engine includes a trunnion forming a socket for a root of a blade, a primary collet positioning the root with respect to the trunnion, and a radial preload retainer at least partially encircling the primary collet and applying a radial force with respect to the primary collet to support the primary collet positioning the root with respect to the trunnion.
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公开(公告)号：US12123350B2
公开(公告)日：2024-10-22
申请号：US17190076
申请日：2021-03-02
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
CPC classification number: F02C7/18 , F02C7/14 , F02C7/047 , F02K3/077 , F05D2240/12 , F05D2260/213
Abstract: A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.
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公开(公告)号：US20240151147A1
公开(公告)日：2024-05-09
申请号：US17979853
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Gary Willard Bryant, Jr. , Nicholas Joseph Kray , Ming Xie , Elzbieta Kryj-Kos , Douglas Lorrimer Armstrong , Nicholas M. Daggett , Frank Worthoff , Scott Roger Finn
IPC: F01D5/28
CPC classification number: F01D5/282 , F05D2220/32 , F05D2230/60 , F05D2300/603
Abstract: The present disclosure relates to an airfoil assembly for a turbine engine and methods of assembly thereof. The airfoil assembly generally includes a composite airfoil and a spar. The composite airfoil has a pressure side and a suction side extending in an axial direction between a leading edge and a trailing edge defining a chordwise direction and extending radially between a root and a tip defining a spanwise direction and having a span-length. The spar includes a first portion including a first material and a second portion joined at an interface with the first portion. The second portion further includes a second material, different from the first material, joined to the first portion at an interface. The method generally includes joining the first portion with the second portion at the interface; and assembling the spar with the composite airfoil.
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公开(公告)号：US20230279805A1
公开(公告)日：2023-09-07
申请号：US18314187
申请日：2023-05-09
Applicant: General Electric Company
Inventor： Nicholas M. Daggett , Gert Johannes van der Merwe , Daniel Alan Niergarth , Brian Lewis Devendorf
CPC classification number: F02C3/06 , F02C9/58 , F02K3/06 , F05D2220/36 , F05D2220/32
Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.
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公开(公告)号：US12180886B2
公开(公告)日：2024-12-31
申请号：US18314187
申请日：2023-05-09
Applicant: General Electric Company
Inventor： Nicholas M. Daggett , Gert Johannes van der Merwe , Daniel Alan Niergarth , Brian Lewis Devendorf
Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.
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Patent Agency Ranking
公开(公告)号：US20240375763A1
公开(公告)日：2024-11-14
申请号：US18777961
申请日：2024-07-19
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Drew M. Capps , Nicholas M. Daggett , Gary W. Bryant
Abstract: A rotating airfoil including a body and a vibration absorber located within the body. The body has a root end and a tip. The rotating airfoil has a natural frequency, and the vibration absorber has a natural frequency. The natural frequency of the vibration absorber is different than the natural frequency of the rotating airfoil.
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公开(公告)号：US20230021280A1
公开(公告)日：2023-01-19
申请号：US17377668
申请日：2021-07-16
Applicant: General Electric Company
Inventor： Nicholas M. Daggett , Gert Johannes van der Merwe , Daniel Alan Niergarth , Brian Lewis Devendorf
Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.
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公开(公告)号：US20220282925A1
公开(公告)日：2022-09-08
申请号：US17190103
申请日：2021-03-02
Applicant: General Electric Company
Inventor： Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
Abstract: A heat exchanger is provided. The heat exchanger includes a first wall manifold. The heat exchanger further includes a second wall manifold spaced apart from the first wall manifold. The heat exchanger further includes a plurality of vanes that extend generally circumferentially between the first wall manifold and the second wall manifold. The heat exchanger further includes a plurality of fluid circuits defined within the heat exchanger. Each fluid circuit in the plurality of fluid circuits includes an inlet channel portion and an outlet channel portion defined within the first wall manifold. A return channel portion defined within the second wall manifold. At least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes. The at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.
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公开(公告)号：US12043368B2
公开(公告)日：2024-07-23
申请号：US17656109
申请日：2022-03-23
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Drew M. Capps , Nicholas M. Daggett , Gary W. Bryant
CPC classification number: B64C11/008 , F04D29/668 , F05D2260/96
Abstract: A rotating airfoil including a body and a vibration absorber located within the body. The body has a root end and a tip. The rotating airfoil has a natural frequency, and the vibration absorber has a natural frequency. The natural frequency of the vibration absorber is different than the natural frequency of the rotating airfoil.
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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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