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    AIRCRAFT WITH REAR MOUNTED ENGINES
    3.
    发明授权
    AIRCRAFT WITH REAR MOUNTED ENGINES 有权

    公开(公告)号：EP3187420B1

    公开(公告)日：2018-05-23

    申请号：EP15382681.3

    申请日：2015-12-31

    申请人： Airbus Operations S.L.

    发明人： MARTÍNEZ MUÑOZ, José Luis

    IPC分类号： B64D27/02

    CPC分类号： B64D27/02 ,  B64D2027/005 ,  Y02T50/44 ,  Y02T50/66

    摘要： Aircraft (1, 1') with rear mounted engines (2, 2'), comprising a vertical tail plane (3) and a horizontal tail plane (4), in which the engines (2, 2') are mounted on top of the horizontal tail plane (4), such that the horizontal tail plane (4) comprises an inner fixed part (5) attached to the fuselage (8) of the aircraft (1, 1'), the inner fixed part (5) comprising an elevator (7), and two outer movable parts (6), each one of the outer movable parts (6) being located at each side end of the horizontal tail plane (4) which is furthest away from the fuselage (8) of the aircraft (1, 1'), such that both the inner fixed part (5) and the outer movable parts (6) are at least partially subjected to the flow coming from the engines (2, 2') when they are in use.

    DISPOSITIF DE RÉGULATION D'UNE HÉLICE À PALES À CALAGE VARIABLE D'UN TURBOPROPULSEUR
    4.
    发明公开
    DISPOSITIF DE RÉGULATION D'UNE HÉLICE À PALES À CALAGE VARIABLE D'UN TURBOPROPULSEUR 审中-公开
    用于调节涡轮螺旋桨的可变式叶片螺旋桨的装置

    公开(公告)号：EP3313730A1

    公开(公告)日：2018-05-02

    申请号：EP16736531.1

    申请日：2016-06-17

    申请人： Safran Helicopter Engines

    发明人： MOUTAUX, Antoine ,  PRESSE, Jean-Michel

    IPC分类号： B64C11/38

    CPC分类号： B64C11/38 ,  B64C11/303 ,  F15B9/17 ,  F15B13/10 ,  F15B21/08 ,  Y02T50/66

    摘要： The invention relates to a device for controlling a propeller, having variable-pitch blades, of a turboprop engine, including a first hydromechanical device (10) for controlling the pitch of the blades of the propeller and a second hydromechanical device (20) for controlling the speed of rotation of the propeller, characterised in that said device includes a single electromechanical actuator (30) including a movable actuator member (31, 36) mechanically connected both to said first hydromechanical device (10) for controlling the pitch, in order to manage the pitch setpoint, and to said second hydromechanical device (20) for controlling the speed, in order to manage the speed setpoint.

    Blade safety mechanism for open rotor engine system
    6.
    发明公开
    Blade safety mechanism for open rotor engine system 审中-公开
    开式转子发动机系统的叶片安全机构

    公开(公告)号：EP2778068A3

    公开(公告)日：2017-12-27

    申请号：EP14153949.4

    申请日：2014-02-05

    申请人： The Boeing Company

    发明人： Koch IV, William John

    IPC分类号： B64D27/12 ,  B64D45/00 ,  F01D5/14 ,  B64D27/00 ,  B64C27/00

    CPC分类号： F01D5/14 ,  B64C27/006 ,  B64D27/12 ,  B64D45/00 ,  B64D2027/005 ,  Y02T50/44 ,  Y02T50/66

    摘要： BLADE SAFETY MECHANISM FOR OPEN ROTOR ENGINE SYSTEM
    A method and apparatus for safely handling an undesired blade event (225) in an open rotor engine system (208). In one illustrative embodiment, an occurrence of an undesired blade event (225) in an open rotor engine system is detected. Electrical energy (238) is allowed to flow into a conductor (230) embedded in the blade (218) in response to the undesired blade event (225). The conductor (230) is vaporized when the electrical energy (238) flowing through the conductor (230) heats the conductor to a temperature above a selected threshold.

    摘要翻译： 用于开式转子发动机系统的叶片安全机构一种用于安全处理开式转子发动机系统（208）中的不期望的叶片事件（225）的方法和设备。 在一个说明性实施例中，检测到开式转子发动机系统中发生不希望的叶片事件（225）。 响应于不希望的叶片事件（225），电能（238）被允许流入嵌入叶片（218）中的导体（230）。 当流过导体（230）的电能（238）将导体加热到高于选定阈值的温度时，导体（230）蒸发。

    Gas turbine engine installation
    7.
    发明公开
    Gas turbine engine installation 审中-公开
    燃气轮机发动机安装

    公开(公告)号：EP2774852A3

    公开(公告)日：2017-12-27

    申请号：EP14153969.2

    申请日：2014-02-05

    申请人： Rolls-Royce plc

    发明人： Stretton, Richard

    IPC分类号： B64D27/14 ,  B64D29/04 ,  B64D27/00 ,  B64D35/00

    CPC分类号： B64D27/14 ,  B64D29/04 ,  B64D35/00 ,  B64D2027/005 ,  Y02T50/44 ,  Y02T50/66

    摘要： A fuselage (36, 74, 144) mounted gas turbine engine installation (30, 70, 110), the installation (30, 70, 110) comprising at least one propeller stage (46, 82, 122) and a gas turbine core (50, 92, 132) arranged in use to drive the propeller stage (46, 82, 122). The core (50, 92, 132) is external to the fuselage (36, 74, 144) and the rotational axes of the core (50, 92, 132) and propeller stage (46, 82, 122) are offset with respect to each other.

    摘要翻译： 1。一种安装燃气涡轮发动机装置（30,70,110）的机身（36,74,144），所述装置（30,70,110）包括至少一个螺旋桨级（46,82,122）和燃气涡轮机芯（ 50，92,132）布置成用于驱动螺旋桨级（46,82,122）。 芯部（50,92,132）位于机身（36,74,144）的外部，并且芯部（50,92,132）和螺旋桨级（46,82,122）的旋转轴线相对于机身 彼此。

    Propulsion engine
    8.
    发明公开
    Propulsion engine 审中-公开
    推进引擎

    公开(公告)号：EP2525046A3

    公开(公告)日：2017-12-27

    申请号：EP12165602.9

    申请日：2012-04-26

    申请人： Rolls-Royce plc

    发明人： Edwards, David

    IPC分类号： F01D7/02 ,  F02K3/072

    CPC分类号： F02K3/072 ,  B64C11/306 ,  B64C11/308 ,  B64C11/38 ,  B64C11/42 ,  B64D2027/005 ,  F01D7/02 ,  F05D2260/79 ,  Y02T50/66 ,  Y02T50/673

    摘要： A propulsion engine 20 for an aircraft comprises a first fan 30 having a set of first blades 32 and a second fan 40 having a set of second blades 42. There is provided a first angular pitch adjustment mechanism 50 coupled to the first set of blades 32, a second angular pitch adjustment mechanism 60 coupled to the second set of blades 42 and an actuation means 70 coupled to the first angular pitch adjustment mechanism 50. The first and second angular pitch adjustment mechanisms 50, 60 are coupled together such that when the actuation means generates an output, the angular pitch of each of the first blades 32 and each of the second blades 42 changes.

    摘要翻译： 用于飞行器的推进发动机20包括具有一组第一叶片32的第一风扇30和具有一组第二叶片42的第二风扇40.提供了联接到第一组叶片32的第一角度调节机构50 ，联接到第二组叶片42的第二角度调节机构60以及联接到第一角度调节机构50的致动装置70.第一和第二角度调节机构50,60联接在一起，使得当致动 装置产生输出，第一叶片32和第二叶片42中的每一个的角度变化。

    Method and apparatus for non-model based control for counter-rotating open-rotor gas turbine engine
    9.
    发明公开
    Method and apparatus for non-model based control for counter-rotating open-rotor gas turbine engine 审中-公开
    用于反转开式转子燃气涡轮发动机的基于非模型的控制的方法和设备

    公开(公告)号：EP2623711A3

    公开(公告)日：2017-08-16

    申请号：EP13154022.1

    申请日：2013-02-05

    申请人： General Electric Company

    发明人： Lu, Manxue ,  Carpenter, Sheldon

    IPC分类号： F01D1/24 ,  B64C11/48 ,  F01D7/00 ,  F02C9/58

    CPC分类号： B64C11/308 ,  B64D2027/005 ,  F01D1/24 ,  F01D7/00 ,  F02C9/58 ,  Y02T50/66

    摘要： A simple, robust and systematic control solution for open rotor control with a differential gearbox is disclosed. When the two counter rotating rotors of a CROR engine are conditioned by the differential gearbox, the two rotors speeds are coupled for given input torque. The solution provided by the current disclosure mathematically decouples these two rotors by transforming the original individual actuator input and speed output into differential & average input and output. Because the newly formed control system representation of the plant has decoupled input/output mapping, it follows that the simple SISO control can be applied. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.

    摘要翻译： 公开了一种用于具有差速齿轮箱的开式转子控制的简单，稳健且系统化的控制解决方案。 当CROR发动机的两个反向旋转转子由差速齿轮箱调节时，两个转子速度在给定输入转矩时耦合。 本公开提供的解决方案通过将原始单独的致动器输入和速度输出转换为差动＆平均输入和输出来数学地解耦这两个转子。 由于工厂新形成的控制系统表示具有解耦输入/输出映射，因此可以应用简单的SISO控制。 此外，电流控制解决方案允许双引擎车辆上的四个转子之间的简单且协调良好的速度相位同步。