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公开(公告)号：EP2089274A2
公开(公告)日：2009-08-19
申请号：EP06838841.2
申请日：2006-12-08
发明人： STAMPS, Frank B. , RAUBER, Richard E. , POPELKA, David A. , TISDALE, Patrick R. , CAMPBELL, Thomas C. , BRASWELL, James L. Jr. , STANNEY, Keith , WASIKOWSKI, Mark , DONOVAN, Tom , BASKIN, Bryan , SMITH, Ryan , CORRIGAN, John J. III.
CPC分类号： B64C11/30 , B64C27/605 , B64C29/0033
摘要： A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.
摘要翻译： 一种用于飞机转子上的叶片的桨距控制系统具有一个万向球转子轮毂（31）和多个连接到该轮毂并且能够围绕枢转轴线相对于轮毂枢转的跨接臂（61）。 多个俯仰连杆（55）中的每一个将所述跨接臂（61）中的一个连接到飞行控制系统，用于响应于输入使所连接的跨接臂（61）绕枢转轴线并且相对于轮毂枢转 来自控制系统。 多个跨接连杆（69）中的每一个将一个跨接臂（61）连接到叶片中的一个，以响应于相关联的跨接臂的枢转而使关联的叶片绕俯仰轴线旋转。
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公开(公告)号：EP2003055A2
公开(公告)日：2008-12-17
申请号：EP08251245.0
申请日：2008-03-31
发明人： Raes, Mark , Carvalho, Paul A.
IPC分类号： B64C11/30
摘要： A blade pitch actuation mechanism (12) for a plurality of propeller blades (20) supported in a blade hub (44) comprises a plurality of bearing assemblies (54), a bearing support plate (52) and a yoke (48). The plurality of bearing assemblies (54) receives a plurality of actuation trunnion pins (61) from the plurality of propeller blades (20). The bearing support plate (52) is connected to the plurality of bearing assemblies (54) and unifies the plurality of bearing assemblies (54) in a ring-like configuration. The yoke (48) is connected to the bearing support plate (52) and translates within the hub (44) to adjust the pitch of the plurality of propeller blades (20).
摘要翻译： 支撑在叶片毂（44）中的多个螺旋桨叶片（20）的叶片桨距致动机构（12）包括多个轴承组件（54），轴承支撑板（52）和轭架（48）。 多个轴承组件（54）从多个螺旋桨叶片（20）接收多个致动耳轴销（61）。 轴承支撑板（52）连接到多个轴承组件（54）并将多个轴承组件（54）组合成环状构造。 轭（48）连接到轴承支撑板（52）并且在轮毂（44）内平移以调节多个螺旋桨叶（20）的桨距。
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公开(公告)号：EP0522035B1
公开(公告)日：1994-10-05
申请号：EP91907278.5
申请日：1991-04-01
申请人： Lutz, Ferdinand
发明人： Lutz, Ferdinand
摘要： Propeller with twistable blades comprising a spar (1) with ribs (4 to 6) which can be rotated in opposite directions about the axis of the spar (1) by means of an adjusting device. A coupling means in the propeller ensures that when two ribs are rotated in opposite directions by the adjusting device, the other ribs are adjusted accordingly. In this invention, the coupling means consists of a rod (20) substantially parallel to the spar (1) and designed to be relatively bendable in the plane through the spar (1) and the rod (20), and relatively resistant to bending in the plane perpendicular thereto. The rod couples at least three ribs together in such a way that it distorts when two ribs are rotated in opposite directions along a helix about the spar, causing subsequent ribs to move with it on this helix.
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公开(公告)号：EP0493005A1
公开(公告)日：1992-07-01
申请号：EP91311838.6
申请日：1991-12-20
发明人： Komura, Takashi , Bannai, Takashi
IPC分类号： B64C11/30
CPC分类号： B64C11/30
摘要： A variable-pitch mechanism, for use in an airplane, a ship, or the like, for adjusting the pitch of a plurality of blades (8) of a propeller (4) in which attachment shafts (9) of a plurality of radial blades of a propeller are rotatably mounted on a tubular hub (3) which can be driven by a drive shaft (1), and eccentric pins (16) projecting from ends of the attachment shafts are held in an annular groove (15) defined in the outer periphery of an adjusting ring (14) which is disposed concentrically in the hub and axially movable. The attachment shafts can be turned about their own axes through the eccentric pins in response to axial displacement of the adjusting ring for adjusting the pitch of the propeller blades.
摘要翻译： 一种用于飞机，船舶等的可变桨距机构，用于调节螺旋桨（4）的多个叶片（8）的桨距，其中多个径向桨叶（9）的连接轴（9） （1）驱动的管状轮毂（3）上，并且从附接轴的端部突出的偏心销（16）保持在限定在其中的环形凹槽（15）中， 调节环（14）的外周边，该调节环同心地布置在轮毂中并且可轴向移动。 响应于用于调节螺旋桨叶片的螺距的调节环的轴向位移，附接轴可以通过偏心销绕其自身轴线转动。
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公开(公告)号：EP0392968A3
公开(公告)日：1991-01-23
申请号：EP90630087.6
申请日：1990-04-10
CPC分类号： B64C11/30
摘要： A ground mode pitch position logic and control is shown and described in this invention. A method for scheduling and limiting the pitch actuator reference signal in accordance with the actuator commanded schedule, propeller overspeed and propeller underspeed.
摘要翻译： 在本发明中示出和描述了地面模式俯仰位置逻辑和控制。 一种根据执行器命令的时间表，螺旋桨超速和螺旋桨不足调度和限制俯仰致动器参考信号的方法。
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公开(公告)号：EP0380278A2
公开(公告)日：1990-08-01
申请号：EP90300654.2
申请日：1990-01-22
发明人： Adamson, Arthur Paul
IPC分类号： B64C11/30
CPC分类号： B64C11/30
摘要： The invention concerns a system for reducing the resisting torque which must be overcome in changing pitch of aircraft propeller blades. The resisting torque includes gas twisting moment and centrifugal twisting moment. The invention includes a bearing system (R) which derives a torque from radial motion of the blade (6), the radial motion being induced by centrifugal force. The derived torque opposes the resisting torque. The derived torque can also be used to not only oppose, but also overcome, the resisting torques. Such overcoming can be desirable because the resisting torques can drive the propeller blades into a flat pitch position if the pitch change mechanism fails.
摘要翻译： 本发明涉及一种用于降低在改变飞机螺旋桨叶片间距时必须克服的阻力矩的系统。 阻力矩包括气体扭矩和离心扭矩。 本发明包括一个轴承系统（R），其从叶片（6）的径向运动导出扭矩，径向运动由离心力引起。 导出的扭矩与抗扭矩相反。 导出的扭矩也可以用于不仅反对，而且可以克服抗扭矩。 这种克服是可取的，因为如果螺距改变机构失效，则抵抗扭矩可以将螺旋桨叶片驱动到平坦的俯仰位置。
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公开(公告)号：EP4441339A1
公开(公告)日：2024-10-09
申请号：EP22840240.0
申请日：2022-11-28
申请人： SAFRAN , SAFRAN AIRCRAFT ENGINES
CPC分类号： B64C11/30 , F01D7/00 , F05D2260/8120130101 , F05D2200/2020130101 , F05D2270/4420130101 , B64C11/00
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公开(公告)号：EP4281365B1
公开(公告)日：2024-07-03
申请号：EP22703539.1
申请日：2022-01-24
CPC分类号： B64C29/0033 , B64C2220/0020130101 , B64C11/46 , B64C11/30 , Y02T50/60 , B64D27/357 , B64D31/16
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公开(公告)号：EP3508418A2
公开(公告)日：2019-07-10
申请号：EP19150420.8
申请日：2019-01-04
CPC分类号： F04D29/388 , B64C11/16 , B64C11/18 , B64C11/24 , B64C11/26 , B64C11/30 , B64C29/0033 , B64D45/02 , F04D29/164 , F04D29/36 , F04D29/522
摘要： A fan blade comprising a blade body spanning from a blade root to a blade tip in a longitudinal direction and a fluid passageway formed within the blade body and extending from the blade root to the blade tip. The blade body spanning from a leading edge to a trailing edge in a lateral direction. The fluid passageway allowing fluid to flow out of the blade.
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公开(公告)号：EP3406522A1
公开(公告)日：2018-11-28
申请号：EP17198168.1
申请日：2017-10-24
IPC分类号： B64C29/00
CPC分类号： B64C27/57 , B64C11/06 , B64C11/30 , B64C29/0033 , B64C2027/7205 , B64C2027/7211 , B64C2027/7261 , B64C2201/086 , B64C2201/108
摘要： In one aspect, a rotor assembly (200) includes a hub (204) and a plurality of rotor blades (212); at least one blade root actuator (252) configured to adjust at least one of the plurality of rotor blades (212) independently of the other rotor blades to accommodate forces on the aircraft (10); and at least one controller (404) couplable to the at least one blade root actuator (252) and configured to send signals to the at least one blade root actuator (252) to enable adjustment of the at least one of the plurality of rotor blades (212). In another embodiment, at least one blade flap is associated with a rotor blade (212) can be actuated to adjust the shape of the rotor blade (212). In some embodiments, there are methods and systems incorporating at least one of the root blade actuator (252) and the blade flap for stabilizing a tiltrotor aircraft (10) by counteracting destabilizing forces on at least one rotor blade (212).
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