Patents by Inventor Nicholas M. Daggett
Nicholas M. Daggett has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20250075672Abstract: A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.Type: ApplicationFiled: February 2, 2024Publication date: March 6, 2025Inventors: Nicholas M. Daggett, Frank Worthoff, Pawel Pres, Daryl John Burford
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Patent number: 12180886Abstract: 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.Type: GrantFiled: May 9, 2023Date of Patent: December 31, 2024Assignee: General Electric CompanyInventors: Nicholas M. Daggett, Gert Johannes van der Merwe, Daniel Alan Niergarth, Brian Lewis Devendorf
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Publication number: 20240375763Abstract: 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.Type: ApplicationFiled: July 19, 2024Publication date: November 14, 2024Inventors: Suryarghya Chakrabarti, Drew M. Capps, Nicholas M. Daggett, Gary W. Bryant
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Patent number: 12123350Abstract: 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.Type: GrantFiled: March 2, 2021Date of Patent: October 22, 2024Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Nicholas M. Daggett, Steven Douglas Johnson, Anand P. Roday, Scott Alan Schimmels
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Publication number: 20240263883Abstract: 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.Type: ApplicationFiled: March 22, 2024Publication date: August 8, 2024Inventors: Nicholas M. Daggett, Steven Douglas Johnson, Anand P. Roday, Scott Alan Schimmels
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Patent number: 12055153Abstract: A variable pitch airfoil assembly for an engine includes a disk having an annular shape extending about an axial direction and an airfoil coupled to the disk via a platform. The airfoil extends outwardly from the disk in a radial direction and is rotatable relative to the disk about a pitch axis. The variable pitch airfoil assembly further includes a damping element positioned at least partially within the disk exterior of and adjacent to a perimeter of the platform so as to provide vibration damping by friction between the damping element, the platform, and the disk while also allowing for a pitch change of the airfoil.Type: GrantFiled: December 5, 2023Date of Patent: August 6, 2024Assignee: General Electric CompanyInventors: Suryarghya Chakrabarti, Nicholas M. Daggett, Zachary Pebley
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Patent number: 12043368Abstract: 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.Type: GrantFiled: March 23, 2022Date of Patent: July 23, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Suryarghya Chakrabarti, Drew M. Capps, Nicholas M. Daggett, Gary W. Bryant
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Publication number: 20240229743Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.Type: ApplicationFiled: March 25, 2024Publication date: July 11, 2024Applicant: General Electric CompanyInventors: Daniel A. Niergarth, Martin Manning, Nicholas M. Daggett, Christopher J. Kroger, Ian F. Prentice
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Publication number: 20240229656Abstract: 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.Type: ApplicationFiled: October 21, 2022Publication date: July 11, 2024Inventors: Abhijeet Jayshingrao Yadav, Nicholas Joseph Kray, Nicholas M. Daggett, Nitesh Jain, Matthew Mark Weaver, Srinivas Addagatla
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Publication number: 20240151147Abstract: 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.Type: ApplicationFiled: November 3, 2022Publication date: May 9, 2024Applicant: AIRFOIL AND METHODS OF ASSEMBLY THEREOFInventors: Gary Willard Bryant, Jr., Nicholas Joseph Kray, Ming Xie, Elzbieta Kryj-Kos, Douglas Lorrimer Armstrong, Nicholas M. Daggett, Frank Worthoff, Scott Roger Finn
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Publication number: 20240133301Abstract: 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.Type: ApplicationFiled: October 20, 2022Publication date: April 25, 2024Inventors: Abhijeet Jayshingrao Yadav, Nicholas Joseph Kray, Nicholas M. Daggett, Nitesh Jain, Matthew Mark Weaver, Srinivas Addagatla
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Patent number: 11965697Abstract: 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.Type: GrantFiled: March 2, 2021Date of Patent: April 23, 2024Assignee: General Electric CompanyInventors: Nicholas M. Daggett, Steven Douglas Johnson, Anand P. Roday, Scott Alan Schimmels
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Patent number: 11946437Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.Type: GrantFiled: August 12, 2022Date of Patent: April 2, 2024Assignee: General Electric CompanyInventors: Daniel A. Niergarth, Martin Manning, Nicholas M. Daggett, Christopher J. Kroger, Ian F. Prentice
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Patent number: 11913408Abstract: A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.Type: GrantFiled: April 17, 2023Date of Patent: February 27, 2024Assignees: General Electric Company, GE Aviation Systems LimitedInventors: Nicholas M. Daggett, Frank Worthoff, Pawel Pres, Daryl John Burford
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Publication number: 20230407759Abstract: 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.Type: ApplicationFiled: October 14, 2022Publication date: December 21, 2023Inventors: 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
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Patent number: 11795964Abstract: 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.Type: GrantFiled: July 16, 2021Date of Patent: October 24, 2023Assignee: General Electric CompanyInventors: Nicholas M. Daggett, Gert Johannes van der Merwe, Daniel Alan Niergarth, Brian Lewis Devendorf
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Publication number: 20230303238Abstract: 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.Type: ApplicationFiled: March 23, 2022Publication date: September 28, 2023Inventors: Suryarghya Chakrabarti, Drew M. Capps, Nicholas M. Daggett, Gary W. Bryant
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Publication number: 20230279805Abstract: 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.Type: ApplicationFiled: May 9, 2023Publication date: September 7, 2023Inventors: Nicholas M. Daggett, Gert Johannes van der Merwe, Daniel Alan Niergarth, Brian Lewis Devendorf
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Patent number: 11674435Abstract: 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.Type: GrantFiled: June 29, 2021Date of Patent: June 13, 2023Assignee: General Electric CompanyInventors: Nicholas M. Daggett, Gert Johannes van der Merwe, Daniel Alan Niergarth, Brian Lewis Devendorf
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Publication number: 20230126551Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.Type: ApplicationFiled: August 12, 2022Publication date: April 27, 2023Applicant: General Electric CompanyInventors: Daniel A. Niergarth, Martin Manning, Nicholas M. Daggett, Christopher J. Kroger, Ian F. Prentice