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公开(公告)号：US20240051656A1
公开(公告)日：2024-02-15
申请号：US18085112
申请日：2022-12-20
发明人： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
摘要： An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
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公开(公告)号：US20240052755A1
公开(公告)日：2024-02-15
申请号：US18081813
申请日：2022-12-15
发明人： Stefan Joseph Cafaro , Inenhe Mohammed Khalid , James Ryan Reepmeyer , Amit Zutshi , Daniel Edward Mollmann , Arjan Johannes Hegeman , Rafal Sarba
CPC分类号： F01D17/162 , F01D7/00 , F05D2240/12 , F05D2220/323 , F05D2240/20
摘要： A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.
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公开(公告)号：US20240052753A1
公开(公告)日：2024-02-15
申请号：US18081862
申请日：2022-12-15
发明人： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
摘要： An open rotor engine includes a core engine, a plurality of guide vanes positioned within or extending from the core engine; and a pitch change assembly operably coupled to the plurality of guide vanes. The pitch change assembly includes one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes, and a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators. The plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes. The plurality of linkage arms may have a length that differs from one another, and such length may orient a displacement or a range of motion of the respective linkage arm to an envelope of rotation about a guide vane axis that differs as between the plurality of guide vanes.
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公开(公告)号：US20140064937A1
公开(公告)日：2014-03-06
申请号：US13626553
申请日：2012-09-25
IPC分类号： F04D29/16
CPC分类号： F04D29/164 , F01D11/08 , F05D2220/36 , F05D2240/56 , F16J15/3288 , Y10T29/49297
摘要： A fan assembly is provided. The fan assembly includes a rotor having a hub and a plurality of rotor blades extending radially outward from the hub. Each rotor blade includes a blade tip at a radially distal end of each blade. The rotor blade tips define a rotor diameter. The fan assembly also includes a first cylindrical casing substantially axially aligned with the blade tips, the first casing including a first inner diameter that is greater than the rotor diameter. The fan assembly further includes a brush seal assembly coupled to the blade tip of a least one of the plurality of rotor blades, the brush seal assembly configured to contact the casing segment during a first operational mode of the fan assembly, the brush seal assembly configured to avoid contact with the casing segment during a second operational mode of the fan assembly.
摘要翻译： 提供风扇组件。 风扇组件包括具有毂的转子和从轮毂径向向外延伸的多个转子叶片。 每个转子叶片包括在每个叶片的径向远端处的叶片尖端。 转子叶片尖端限定转子直径。 风扇组件还包括基本上与叶片尖端对齐的第一圆柱形壳体，第一壳体包括大于转子直径的第一内径。 风扇组件还包括耦合到多个转子叶片中的至少一个的叶片尖端的刷密封组件，刷密封组件构造成在风扇组件的第一操作模式期间接触壳体段，刷密封组件构造 以避免在风扇组件的第二操作模式期间与套管段接触。
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公开(公告)号：US11421877B2
公开(公告)日：2022-08-23
申请号：US15689460
申请日：2017-08-29
摘要： A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.
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公开(公告)号：US10920607B2
公开(公告)日：2021-02-16
申请号：US16145759
申请日：2018-09-28
摘要： A blade for a propulsion apparatus. The blade includes a body having opposed pressure and suction sides. The blade extends in span between a root and a tip and the blade extends in chord between a leading edge and a trailing edge. The blade includes a fracture structure that is defined within the body and positioned such that it is spaced-away from the tip. The fracture structure includes at least one chamber. A first fracture wall is disposed between the at least one chamber and the pressure side, and a second fracture wall is disposed between the at least one chamber and the suction side. The fracture structure is configured to fail when a predetermined force is applied to the tip such that the tip separates from the remainder of the body.
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公开(公告)号：US12116903B2
公开(公告)日：2024-10-15
申请号：US17363102
申请日：2021-06-30
CPC分类号： F01D5/147 , F01D5/282 , F01D5/284 , F01D21/045 , F05D2220/36 , F05D2240/304 , F05D2240/307 , F05D2300/6033
摘要： Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.
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公开(公告)号：US11111815B2
公开(公告)日：2021-09-07
申请号：US16161253
申请日：2018-10-16
摘要： An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.
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公开(公告)号：US10422348B2
公开(公告)日：2019-09-24
申请号：US15402536
申请日：2017-01-10
摘要： A containment structure comprising an annular structure configured to provide close tolerance to a rotation structure. The containment structure includes a first abradable structure, a second abradable structure, and a shroud that is defined in part by the first abradable structure and in part by the second abradable structure. An annular surface of the shroud is defined by the first abradable structure and by the second abradable structure. The first abradable structure is harder than the second abradable structure.
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公开(公告)号：US20230003129A1
公开(公告)日：2023-01-05
申请号：US17363102
申请日：2021-06-30
摘要： Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.
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