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111. 发明授权

US1242788A Air-propeller. 失效
标题翻译： AIR-PROPELLER。
公开(公告)号：US1242788A
公开(公告)日：1917-10-09
申请号：US15633517
申请日：1917-03-21
申请人： FRANCISCO TONY
发明人： FRANCISCO TONY
CPC分类号： B64C11/306

112. 发明授权

US989412A Flying-machine. 失效
公开(公告)号：US989412A
公开(公告)日：1911-04-11
申请号：US1910565471
申请日：1910-06-07
申请人： PHILLIPS JACOB
发明人： PHILLIPS JACOB
CPC分类号： B64C11/306

113. 发明授权

US922756A Flying apparatus. 失效
标题翻译：飞行器具
公开(公告)号：US922756A
公开(公告)日：1909-05-25
申请号：US1908456464
申请日：1908-10-06
申请人： DEGN PAUL FREDERIK
发明人： DEGN PAUL FREDERIK
CPC分类号： B64C11/306 , Y10T74/19014

114. 发明授权

US11987369B2 Turbomachine with unducted dual propellers 有权
公开(公告)号：US11987369B2
公开(公告)日：2024-05-21
申请号：US17288206
申请日：2019-10-25
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Nicolas Jérôme Jean Tantot , Anthony Binder , Mario Antoine Lambey
IPC分类号： B64D27/10 , B64C11/30 , B64C11/48 , B64D27/24 , F02B61/04 , F02C3/067 , F02C7/36 , B64D27/00 , B64D27/02
CPC分类号： B64D27/10 , B64C11/306 , B64C11/48 , B64D27/24 , F02B61/04 , F02C3/067 , F02C7/36 , B64D2027/005 , B64D2027/026 , F05D2220/324 , F05D2220/325 , F05D2220/76
摘要： A turbomachine of an aircraft comprising an outer casing delimiting with an inner hub, a flow path of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller; and a second propeller downstream of the first propeller, the first propeller being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor, the second propeller being further disposed at a distance between 1.5 and 4 cord lengths from the first propeller defined between the respective axes of shimming of each of the first and second propellers.

115. 发明授权

US09963221B2 Unison ring system for counter rotating propellers 有权
公开(公告)号：US09963221B2
公开(公告)日：2018-05-08
申请号：US14692308
申请日：2015-04-21
申请人： ROLLS-ROYCE PLC
发明人： Christopher Michael Grice
IPC分类号： B64C11/06 , B64C11/48 , B64C11/30 , F16C19/24
CPC分类号： B64C11/06 , B64C11/306 , B64C11/48 , F16C19/24
摘要： Unison ring system includes first unison ring portion, second unison ring portion, and bearing. Second unison ring portion is co-axial with first unison ring portion. First unison ring portion includes first unison ring and first bearing location portion and second unison ring portion includes second unison ring and second bearing location portion. First bearing location portion is co-axial with first unison ring and projects axially from first unison ring, while second bearing location portion is co-axial with second unison ring and projects axially from second unison ring. First bearing location portion includes outwardly opening groove, and second bearing location portion includes inwardly opening groove. First unison ring portion and second unison ring portion positioned with first bearing location portion being concentric with second bearing location portion defining annular cavity there between. Bearing is accommodated in annular cavity, with axial length of annular cavity being greater than axial length of bearing.

116. 发明申请

US20180043991A1 PITCH CHANGE SYSTEM EQUIPPED WITH MEANS FOR SUPPLYING FLUID TO A CONTROL MEANS AND CORRESPONDING TURBINE ENGINE 审中-公开
公开(公告)号：US20180043991A1
公开(公告)日：2018-02-15
申请号：US15672763
申请日：2017-08-09
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Sébastien Emile Philippe Tajan , Adrien Jacques Philippe Fabre , Paul Antoine Foresto , Régis Eugène Henri Servant , Stéphane Ibarzo
IPC分类号： B64C11/38
CPC分类号： B64C11/38 , B64C11/30 , B64C11/306 , Y02T50/66
摘要： A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body translatable along a longitudinal axis (X) relative to the stationary body and defining two chambers. A fluid supply means is configured to be connected to a fluid supply source and to supply the chambers. The fluid supply means includes at least one channel. The channel is arranged and extends along an axis (Q) parallel to the longitudinal axis in an overthickness of a wall of the stationary body, the overthickness extending radially inside relative to the longitudinal axis.

117. 发明授权

US09376202B2 Pitch control of contra-rotating airfoil blades 有权
标题翻译：反转翼型叶片的间距控制
公开(公告)号：US09376202B2
公开(公告)日：2016-06-28
申请号：US13588180
申请日：2012-08-17
申请人： Aleksander Krzysztof Szymandera
发明人： Aleksander Krzysztof Szymandera
IPC分类号： B64C11/06 , B64C11/30 , F01D1/26 , F02K3/072 , F02C9/58 , B64D27/00
CPC分类号： B64C11/306 , B64C11/308 , B64D27/16 , B64D2027/005 , F01D1/26 , F02C9/58 , F02K3/025 , F02K3/072 , F05D2220/323 , F05D2240/30 , F05D2260/40311 , Y02T50/66
摘要： A pitch control mechanism for an open rotor gas turbine engine is provided, the engine having a first rotor assembly and a second rotor assembly, with a plurality of airfoil blades circumferentially mounted on each rotor assembly, and arranged in contra-rotational relationship to each other. The pitch control mechanism includes an actuator assembly configured to be secured to a non-rotating frame of the engine, the actuator assembly having a first actuator and a second actuator, with the actuator assembly being rotationally isolatable from and couplable to the first and second rotor assemblies such that, in use, an actuation signal from the first or second actuator induces a corresponding desired change in pitch of the airfoil blades of the respective first or second rotor assembly independently of the pitch of the airfoil blades of the second or first rotor assembly.
摘要翻译：提供了一种用于开式转子燃气涡轮发动机的变桨控制机构，该发动机具有第一转子组件和第二转子组件，多个翼型叶片周向地安装在每个转子组件上，并且以彼此相互旋转的关系布置。桨距控制机构包括构造成固定到发动机的非旋转框架的致动器组件，致动器组件具有第一致动器和第二致动器，致动器组件可旋转地隔离并可联接到第一和第二转子组件，使得在使用中来自第一或第二致动器的致动信号独立于第二或第一转子组件的翼型叶片的桨距而引起相应的第一或第二转子组件的翼型叶片的螺距的相应的期望变化。

118. 发明申请

US20150336679A1 PROPULSION UNIT WITH A PAIR OF PROPELLERS FOR AN AIRCRAFT 有权
标题翻译：具有飞机的螺旋桨的推进单元
公开(公告)号：US20150336679A1
公开(公告)日：2015-11-26
申请号：US14718024
申请日：2015-05-20
申请人： SNECMA
发明人： Sebastien Emile Philippe Tajan , Denis Louis Bocquet , Gilles Alain Charier
IPC分类号： B64D35/06
CPC分类号： B64D35/06 , B64C11/306 , B64C11/38 , B64D2027/005 , Y02T50/66
摘要： The present invention relates to a propulsion unit comprising a pair of contra-rotating coaxial propellers, that are referred to as upstream (2) and downstream (3), the downstream propeller, forming a rotating reference frame, being mounted for rotation about a central member forming a stationary reference frame, and being provided with a device for changing the pitch of the blades, characterised in that the downstream propeller is supported by bearings arranged externally on the cylindrical central support, an upstream bearing (40) of which is arranged downstream of a device for changing the pitch of the blades of the upstream propeller, and in that said device for changing the pitch of the downstream propeller comprises a linear actuator (23) in the stationary reference frame with an element (235) that is able to move axially along the axis of the downstream propeller, the upstream bearing comprising an inner ring that is rigidly connected to the linear actuator and an outer ring that is rigidly connected to a rotating casing (20) of the downstream propeller, and a movement-transmission mechanism (24) connecting said movable element of the linear actuator to the blades, comprising a load-transfer bearing arranged to transmit the axial forces from the linear actuator to the rotating reference frame of the downstream propeller.
摘要翻译：本发明涉及一种推进单元，其包括一对反转的同轴螺旋桨，其被称为上游（2）和下游（3），所述下游螺旋桨形成旋转参考系，被安装成围绕中心构件，其形成固定的参考框架，并且设置有用于改变叶片间距的装置，其特征在于，所述下游螺旋桨由布置在所述圆柱形中心支撑件外部的轴承支撑，其上游轴承（40）布置在下游用于改变上游螺旋桨的叶片的桨距的装置，并且所述用于改变下游螺旋桨的桨距的装置包括在固定参考系中的线性致动器（23），其具有能够沿着下游螺旋桨的轴线轴向移动，上游轴承包括刚性地连接到线性致动器的内环和外环 t刚性地连接到下游螺旋桨的旋转壳体（20），以及将线性致动器的可移动元件连接到叶片的运动传递机构（24），包括负载传递轴承，其被布置成将轴向力从线性致动器到下游螺旋桨的旋转参考系。

119. 发明申请

US20150217854A1 TURBINE ENGINE HAVING A PAIR OF PROPELLERS FOR AN AIRCRAFT 有权
标题翻译：具有用于飞机的螺旋桨对的涡轮发动机
公开(公告)号：US20150217854A1
公开(公告)日：2015-08-06
申请号：US14612661
申请日：2015-02-03
申请人： SNECMA
发明人： Jean-Christophe DUFFET , Tewfik BOUDEBIZA , Augustin CURLIER
IPC分类号： B64C11/30
CPC分类号： B64C11/306 , B64C11/308 , B64D2027/005 , F02C3/067 , F02C6/206 , Y02T50/66 , Y02T50/672
摘要： The turbine engine includes respective systems for changing the pitch of the propeller blades, the system (22) for the upstream propeller including a linear actuator (23) and a transmission mechanism (24) connecting the actuator to the blades in order to transform the sliding of the actuator into a rotation of the blades, said upstream propeller (2) including a rotatable housing (19) rigidly connected to a rotatable shaft (17) supported in a static housing (27) of the turbine engine by a bearing (29) upstream of the system, and by a bearing (30) downstream of the system. Advantageously:the rotatable housing (19) of the upstream propeller includes a support (36) rigidly connected to said rotatable housing and surrounding the static housing (27),the actuator (23) is annular and fixed to the support (36) of the rotatable housing, outside the support, and the transfer mechanism comprises connecting rods (33) and rotatable radial arms (34) traversing the gaseous flow path in order to control the pitch of the blades, andthe downstream bearing (30) is provided between the static housing (27) and the support (36), inside said support (36).
摘要翻译：涡轮发动机包括用于改变螺旋桨叶片间距的相应系统，用于上游螺旋桨的系统（22）包括线性致动器（23）和将致动器连接到叶片的传动机构（24），以便将滑动所述上游螺旋桨（2）包括通过轴承（29）刚性地连接到支撑在所述涡轮发动机的静态壳体（27）中的可旋转轴（17）的可旋转壳体（19）在系统的上游，以及系统下游的轴承（30）。有利地：上游螺旋桨的可旋转壳体（19）包括刚性地连接到所述可旋转壳体并围绕静态壳体（27）的支撑件（36），致动器（23）是环形的并且固定到支撑件（36）可旋转壳体，支撑件外部，并且传送机构包括连接杆（33）和横穿气体流动路径的可旋转的径向臂（34），以便控制叶片的间距，并且下游轴承（30）设置在静止壳体（27）和支撑件（36）。

120. 发明授权

US08926279B2 Propeller hub 有权
标题翻译：螺旋桨中心
公开(公告)号：US08926279B2
公开(公告)日：2015-01-06
申请号：US13382026
申请日：2010-07-02
申请人： Eric Jacques Boston , Michel Andre Bouru , Laurent Jablonski , Philippe Gerard Edmond Joly
发明人： Eric Jacques Boston , Michel Andre Bouru , Laurent Jablonski , Philippe Gerard Edmond Joly
IPC分类号： F01D7/00 , F01D1/24 , F04D29/32 , B64C11/30 , F02K3/072 , B64D27/00
CPC分类号： F04D29/321 , B64C11/306 , B64D2027/005 , F02K3/072 , Y02T50/66
摘要： A hub of a propeller with variable-pitch blades for a turbine engine, for example for a propfan engine. The hub of the propeller includes a polygonal ring with substantially radial cylindrical recesses distributed about a central axis of the ring for receiving the blades, a turbine rotor element of the turbine engine, and a securing flange that is attached to the ring so as to connect the ring to the rotor element. The hub further includes a plurality of back-up hooks inserted with clearance in openings, the back-up hooks being connected either to the ring or to the rotor element, and the openings being connected to the other one of the two.
摘要翻译：用于涡轮发动机的可变桨叶的螺旋桨的轮毂，例如用于propfan发动机。螺旋桨的轮毂包括多边形环，其具有围绕用于接收叶片的环的中心轴线分布的基本上径向的圆柱形凹部，涡轮发动机的涡轮机转子元件和附接到环的固定凸缘，以便连接环到转子元件。轮毂还包括多个在开口中间隙插入的备用钩，后备钩连接到环或转子元件，并且开口连接到两者中的另一个。

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