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公开(公告)号：US12110903B2
公开(公告)日：2024-10-08
申请号：US18316656
申请日：2023-05-12
申请人： GE Avio S.r.l.
发明人： Paolo Altamura , Giulio Zagato
CPC分类号： F04D29/323 , B64C11/32 , F05D2220/32 , F05D2260/74 , F05D2260/79
摘要： 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 rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.
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公开(公告)号：US20240280170A1
公开(公告)日：2024-08-22
申请号：US18477960
申请日：2023-09-29
申请人： GE Avio S.r.l.
IPC分类号： F16H57/04
CPC分类号： F16H57/0471 , F16H57/0424 , F16H57/0428 , F16H57/0443 , F02C7/36
摘要： A gearbox assembly includes a plurality of planet gears secured by a planet carrier. The plurality of planet gears and the planet carrier rotate about a longitudinal centerline axis. A planet pin is disposed in each planet gear. One or more journal bearings are defined by the planet pin and the planet gear, each planet gear rotating about the one or more journal bearings. The gearbox assembly includes an auxiliary lubrication system that stores lubricant therein. The auxiliary lubrication system includes one or more lubricant lines that provide fluid communication between the auxiliary lubrication system and the one or more journal bearings. Rotation of the planet carrier and the one or more journal bearings generates a suction effect that causes the lubricant in the auxiliary lubrication system to flow to the one or more journal bearings during windmilling conditions and during zero gravity conditions or negative gravity conditions.
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公开(公告)号：US20240254884A1
公开(公告)日：2024-08-01
申请号：US18635858
申请日：2024-04-15
发明人： Francesco Bertini , Davide Torzo , Pratish Patil , John Joseph , Mahendran Manoharan , Ganesh Seshadri
IPC分类号： F01D5/14
CPC分类号： F01D5/142 , F05D2220/323 , F05D2240/12 , F05D2240/30
摘要： Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.
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公开(公告)号：US20240254882A1
公开(公告)日：2024-08-01
申请号：US18594594
申请日：2024-03-04
发明人： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/301 , F05D2240/305 , F05D2240/306 , F05D2250/181 , F05D2250/711 , F05D2250/712
摘要： An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.
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公开(公告)号：US12049849B2
公开(公告)日：2024-07-30
申请号：US18209689
申请日：2023-06-14
发明人： Andrea Piazza , Jeffrey D. Clements
CPC分类号： F02C7/36 , F02C3/067 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2200/221 , F05D2260/40311 , F05D2260/98
摘要： A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0. The overall engine efficiency rating is greater than or equal to 0.35GR1.5 and less than or equal to 0.7GR1.5.
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公开(公告)号：US20240200497A1
公开(公告)日：2024-06-20
申请号：US18592194
申请日：2024-02-29
CPC分类号： F02C7/224 , B64D37/32 , F02C3/22 , F02C3/30 , F05D2260/213 , F05D2260/607 , F05D2260/99
摘要： Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example apparatus to produce propulsion in a gas turbine engine includes a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor. The apparatus also includes at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line.
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公开(公告)号：US20240191794A1
公开(公告)日：2024-06-13
申请号：US18450050
申请日：2023-08-15
发明人： Leonardo Orlando , Juraj Hrubec
CPC分类号： F16H57/08 , F16C19/38 , F16H1/28 , F16C2361/65 , F16H2057/085
摘要： A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft. The gearbox assembly includes one or more roller bearings disposed within the layshaft and includes a plurality of rolling elements. The gearbox assembly also includes a bearing radial envelope in a range of 1.2 to 4.325. The gearbox assembly can also include a layshaft axial envelope in a range of 3.8 to 12.5.
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公开(公告)号：US12007011B2
公开(公告)日：2024-06-11
申请号：US18165590
申请日：2023-02-07
CPC分类号： F16H55/088 , F16H57/02 , F16H2057/02039
摘要： A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.
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公开(公告)号：US11952948B2
公开(公告)日：2024-04-09
申请号：US17813453
申请日：2022-07-19
申请人： GE Avio S.r.l.
发明人： Juraj Hrubec , Davide Lauria
CPC分类号： F02C7/36 , F02C7/06 , F05D2260/40311
摘要： A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.
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公开(公告)号：US11946388B2
公开(公告)日：2024-04-02
申请号：US17863470
申请日：2022-07-13
申请人： GE Avio S.r.l.
CPC分类号： F01D5/225 , F01D11/125 , F05D2220/32 , F05D2240/30 , F05D2240/55
摘要： A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.
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