-
公开(公告)号：US20250163829A1
公开(公告)日：2025-05-22
申请号：US18435651
申请日：2024-02-07
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew Hudecki , Ryan T. Roehm , Ravindra Shankar Ganiger
Abstract: A lubrication system for a turbine engine having one or more rotating components. The lubrication system includes a primary reservoir that stores a lubricant therein. A primary lubrication system supplies the lubricant from the primary reservoir to the one or more rotating components during normal operation of the turbine engine. An auxiliary lubrication system includes an auxiliary reservoir in fluid communication with the primary reservoir and the one or more rotating components. The auxiliary reservoir receives the lubricant from the primary reservoir and is positioned at substantially a six o'clock position of the turbine engine. The auxiliary lubrication system supplies the lubricant from the auxiliary reservoir to the one or more rotating components based on at least one of a pressure of the lubricant in the primary lubrication system, a pressure of fuel in the turbine engine, or a pressure of hydraulics of the turbine engine.
-
公开(公告)号：US20240402047A1
公开(公告)日：2024-12-05
申请号：US18329150
申请日：2023-06-05
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew J. Hank , John C. Schilling , Ryan T. Roehm , Kevin Graziano , Geoffrey Whitener
Abstract: A disclosed example non-transitory machine readable storage medium includes instructions to cause programmable circuitry to at least determine, based on output from at least one sensor, (i) a first parameter corresponding to a first position in a casing of a gas turbine engine, the first position at or downstream of a volume at which flows from respective ones of bleed offtakes are combined, and (ii) a second parameter corresponding to a second position in a casing of a gas turbine engine, the second position upstream from the first position, determine a status of at least one of the bleed offtakes or the at least one sensor based on the first and second parameters, and provide or indicate the status in response to the status indicating improper operation of at least one of the bleed offtakes or the at least one sensor.
-
公开(公告)号：US12276333B2
公开(公告)日：2025-04-15
申请号：US18481582
申请日：2023-10-05
Applicant: General Electric Company
Inventor： Brandon W. Miller , Arthur W. Sibbach , Andrew Hudecki , Ryan T. Roehm
Abstract: A lubrication system for a gearbox assembly for a turbine engine. The gearbox assembly includes a gear assembly including one or more gears and one or more bearings. The lubrication system includes a sump. The sump is a primary reservoir that has a first lubricant level. The lubrication system also includes a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level that is greater than the first lubricant level. A plurality of drain ports includes a first drain port and a second drain port. The lubrication system fills the secondary reservoir with lubricant between the first lubricant level and the second lubricant level and a portion of the lubricant drains though the second drain port. The one or more gears collects the lubricant to supply the lubricant from the secondary reservoir to the one or more gears or to the one or more bearings.
-
公开(公告)号：US20250101882A1
公开(公告)日：2025-03-27
申请号：US18947865
申请日：2024-11-14
Applicant: General Electric Company
Inventor： Ryan T. Roehm , Brandon W. Miller , Robert Eugene Dyson , Arthur W. Sibbach , Donald S. Yeager , John C. Schilling
Abstract: Viscous damper apparatus and associated methods to control a response to a resonant vibration frequency are disclosed. An apparatus to support an aircraft engine includes a thrust link including a forward end and an aft end, the forward end of the thrust link coupled to the aircraft engine, and a damper including a piston rod coupled to the aft end of the thrust link, the piston rod including a piston, and a chamber including a fluid, the piston to move within the chamber.
-
Patent Agency Ranking
公开(公告)号：US20250101881A1
公开(公告)日：2025-03-27
申请号：US18947789
申请日：2024-11-14
Applicant: General Electric Company
Inventor： Ryan T. Roehm , Brandon W. Miller , Robert Eugene Dyson , Arthur W. Sibbach , Donald S. Yeager , John C. Schilling
IPC: F01D25/04
Abstract: Variable diameter thrust link apparatus are disclosed. A thrust link for an aircraft engine includes a forward end coupled to the aircraft engine, the forward end having a first diameter, and an aft end coupled to the aircraft engine or a pylon, the aft end having the first diameter, wherein the thrust link defines a thrust link span that extends from the forward end to the aft end, wherein a second diameter greater than the first diameter is defined between the forward end and the aft end, wherein the second diameter spans a center diameter span that is equivalent to or between 60% and 90% of the thrust link span.
-
公开(公告)号：US20250100700A1
公开(公告)日：2025-03-27
申请号：US18947832
申请日：2024-11-14
Applicant: General Electric Company
Inventor： Ryan T. Roehm , Brandon W. Miller , Robert Eugene Dyson , Arthur W. Sibbach , Donald S. Yeager , John C. Schilling
Abstract: Fluid-filled thrust link apparatus and associated method are disclosed. A thrust link for an aircraft engine includes a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine, and a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.
-
公开(公告)号：US20250027427A1
公开(公告)日：2025-01-23
申请号：US18416269
申请日：2024-01-18
Applicant: General Electric Company
Inventor： Jeffrey D. Rambo , Brandon W. Miller , Arthur W. Sibbach , Scott D. Hunter , Ryan T. Roehm
Abstract: A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.
-
公开(公告)号：US20240426374A1
公开(公告)日：2024-12-26
申请号：US18481582
申请日：2023-10-05
Applicant: General Electric Company
Inventor： Brandon W. Miller , Arthur W. Sibbach , Andrew Hudecki , Ryan T. Roehm
Abstract: A lubrication system for a gearbox assembly for a turbine engine. The gearbox assembly includes a gear assembly including one or more gears and one or more bearings. The lubrication system includes a sump. The sump is a primary reservoir that has a first lubricant level. The lubrication system also includes a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level that is greater than the first lubricant level. A plurality of drain ports includes a first drain port and a second drain port. The lubrication system fills the secondary reservoir with lubricant between the first lubricant level and the second lubricant level and a portion of the lubricant drains though the second drain port. The one or more gears collects the lubricant to supply the lubricant from the secondary reservoir to the one or more gears or to the one or more bearings.
-
公开(公告)号：US20240402048A1
公开(公告)日：2024-12-05
申请号：US18329156
申请日：2023-06-05
Applicant: General Electric Company
Inventor： Brandon W. Miller , Andrew J. Hank , John C. Schilling , Ryan T. Roehm , Kevin Graziano , Geoffrey Whitener
Abstract: Methods and apparatus to determine engine status with plenum measurements are disclosed. A disclosed example apparatus for use with a gas turbine engine having bleed offtakes includes at least one sensor on or within the gas turbine engine, the at least one sensor to measure at least one parameter corresponding to: a first plenum within a casing of the gas turbine engine, the first plenum positioned at or downstream of a volume at which flows from respective ones of the bleed offtakes are combined, and a second plenum within the casing, the second plenum positioned upstream of the first plenum, and an interface to communicatively couple the at least one sensor to a controller, the controller to determine a status of the bleed offtakes based on the at least one parameter.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.016 seconds)
