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1. 发明公开

EP3400170A1 SYSTEME DE COMMANDE DE L'ORIENTATION DES PALES DE SOUFFLANTE D'UNE TURBOMACHINE A PION DE BLOCAGE DE MISE EN DRAPEAU 审中-公开
公开(公告)号：EP3400170A1
公开(公告)日：2018-11-14
申请号：EP17702674.7
申请日：2017-01-04
申请人： Safran Aircraft Engines
发明人： YVON, Didier Jean-Louis , MOUTON, Clémentine Charlotte Marie , PATSOURIS, Emmanuel Pierre Dimitri
IPC分类号： B64C11/38
CPC分类号： B64C11/385 , B64D27/16 , B64D2027/005 , F01D7/00 , F04D29/323 , F04D29/36 , F05D2220/323 , F05D2220/36 , F05D2240/14 , F05D2260/57 , F05D2260/70 , F05D2260/74 , Y02T50/66 , Y02T50/671
摘要： The invention relates to a system for controlling the direction of the fan blades of a turbine engine propeller, including a cylinder (2) rigidly connected to a housing (5) of the turbine engine, including a movable portion (6) that is translatable in relation to said housing, the movable portion being mechanically coupled to a movement transfer bearing (10) having an outer race (12) that is coupled to fan blade pivots (16) such that translation of the movable portion of the cylinder changes the direction of said fan blades, and at least one locking pin (20) rigidly connected to the housing of the turbine engine and capable of, in the event of failure of the cylinder, mechanically locking the movement transfer bearing in the fan blade feathering position.

3. 发明授权

EP2452877B1 Method and apparatus for reducing aircraft noise 有权
标题翻译：降低飞机噪音的方法和设备
公开(公告)号：EP2452877B1
公开(公告)日：2018-03-28
申请号：EP11188620.6
申请日：2011-11-10
申请人： The Boeing Company
发明人： Moore, Matthew D , Boren, Kelly L. , Lan, Justin
IPC分类号： B64D27/00 , B64D27/14 , B64D27/20 , B64D27/02
CPC分类号： B64D27/14 , B64D27/20 , B64D2027/005 , B64D2027/026 , Y02T50/66
摘要： An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is located longitudinally between the rear spar and the wing trailing edge. The propulsor may also be mounted such that a lowest point of the rotor diameter is located vertically above the wing upper surface.

4. 发明授权

EP3049327B1 DISPOSITIF D'ALIMENTATION EN FLUIDE HYDRAULIQUE D'UN VERIN ET MECANISME DE COMMANDE DE PAS DES PALES D'UNE HELICE DE TURBOMOTEUR COMPORTANT LE VERIN 有权
标题翻译： DISPOSITIF D'ALIMENTATION EN FLUIDE HYDRAULIQUE D'UNVERIN ET MECANISME DE COMMANDE DE PAS DES PALES D'UNE HELICE DE TURBOMOTEUR COMPORTANT LE VERIN
公开(公告)号：EP3049327B1
公开(公告)日：2017-08-09
申请号：EP14784324.7
申请日：2014-09-22
申请人： Safran Aircraft Engines
发明人： BELMONTE, Olivier , CURLIER, Augustin
IPC分类号： B64C11/38 , B64C11/48 , F15B15/14
CPC分类号： B64C11/38 , B64D2027/005 , F15B15/149 , Y02T50/66

5. 发明公开

EP2623712A3 Method and apparatus for model based control for counter-rotating open-rotor gas turbine engine 审中-公开
标题翻译：用于反转开式转子燃气涡轮发动机的基于模型的控制的方法和设备
公开(公告)号：EP2623712A3
公开(公告)日：2017-08-09
申请号：EP13154024.7
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： F02C9/54 , B64C11/305 , B64D2027/005 , F01D1/24 , F01D7/00 , F02C9/58 , Y02T50/66
摘要： A counter-rotating open-rotor gas turbine engine includes: a forward un-ducted rotor (15) including a plurality of forward rotor blades and including a forward rotor angle actuator (14) for setting blade pitch angles of the plurality of forward rotor blades; an aft un-ducted rotor (13) including a plurality of aft rotor blades and including an aft rotor angle actuator (12) for setting blade pitch angles of the plurality of aft rotor blades; a gas turbine engine (10) driving forward and aft un-ducted rotors and including a fuel actuator (16) for setting the fuel flow to the gas turbine engine; and an open rotor control system (18/20) including, a forward rotor blade pitch angle command (BetaF) electrically connected to the forward rotor angle actuator, an aft rotor blade pitch angle command (BetaA) electrically connected to the aft rotor angle actuator, a fuel flow command (Wf) electrically connected to the fuel actuator, a forward rotor speed feedback signal (Nf), an aft rotor speed feedback signal (Na), and an engine core speed feedback signal or engine pressure ratio signal (EPR). The open rotor control system may include a multiple-input-multiple output (MIMO) control algorithm including a dynamic inverstion approach for at least the forward rotor blade pitch angle command (BetaF), the aft rotor blade pitch angle command (BetaA), the forward rotor speed feedback signal (Nf) and the aft rotor speed feedback signal (Na).
摘要翻译：反转开式转子燃气涡轮发动机包括：包括多个前向转子叶片并包括前向转子角致动器（14）的前向不导管转子（15），所述前向转子角致动器（14）用于设定多个前向转子叶片 ; 包括多个后转子叶片并且包括用于设定所述多个后转子叶片的叶片倾斜角的后转子角致动器（12）的后部不导管转子（13）（10），所述燃气涡轮发动机（10）驱动前部和后部无管道转子并且包括用于设定到所述燃气涡轮发动机的燃料流量的燃料致动器（16）和开式转子控制系统（18/20），其包括电连接到所述前转子角致动器的前转子叶片俯仰角命令（BetaF），电连接到所述后转子角致动器的后转子叶片俯仰角命令（BetaA），与燃料致动器电连接的燃料流量指令（Wf），前进转子速度反馈信号（Nf），后转子速度反馈信号（Na）以及发动机核心速度反馈信号或发动机压力比信号（EPR）。开放式转子控制系统可以包括多输入多输出（MIMO）控制算法，该算法包括用于至少前向转子叶片俯仰角命令（BetaF），后转子叶片俯仰角命令（BetaA），正转转速反馈信号（Nf）和后转速反馈信号（Na）。

6. 发明公开

EP2604791A3 A propulsion engine 审中-公开
标题翻译：推进引擎
公开(公告)号：EP2604791A3
公开(公告)日：2017-06-21
申请号：EP12195663.5
申请日：2012-12-05
申请人： Rolls-Royce plc
发明人： Edwards, David , Nicholson, Richard
IPC分类号： F01D1/26 , F01D17/10 , F04B1/04 , F02K3/072 , F02C7/32 , F02C9/56
CPC分类号： F04D13/02 , B64C11/48 , B64D2027/005 , F02C7/32 , F02C9/56 , F02K3/072 , F03C1/0409 , F03C1/0447 , F03C1/053 , F04B1/053 , F04B1/06 , F04B7/0076 , F04B2205/03 , F05D2220/324 , F05D2260/406 , F05D2260/56 , F05D2260/79 , F05D2270/023 , Y02T50/66 , Y02T50/671
摘要： A propulsion engine for an aircraft, the propulsion engine comprising: one or more fans (1, 2) rotatably linked to one or more respective shafts (11); a driving means arranged to drive the one or more fans; and a first hydraulic pump-motor (10) connected to one of the fan shafts, the first hydraulic pump-motor comprising a cam (12) disposed about the shaft and one or more radially extending pistons (13) arranged to engage a surface of the cam, the cam and pistons being arranged such that the pistons reciprocate due to the rotation of the cam, wherein the first hydraulic pump-motor is arranged to selectively transfer a variable amount of power to or from the one or more fans so as to control the rotational speed of the one or more fans.
摘要翻译： 1。一种用于飞机的推进引擎，所述推进引擎包括：一个或多个风扇（1,2），所述风扇可旋转地连接至一个或多个相应的轴（11）; 驱动装置，其布置成驱动所述一个或多个风扇; 和连接到所述风扇轴之一的第一液压泵马达（10），所述第一液压泵马达包括围绕所述轴设置的凸轮（12）和一个或多个径向延伸的活塞（13），所述活塞所述凸轮，所述凸轮和所述活塞被布置成使得所述活塞由于所述凸轮的旋转而往复运动，其中所述第一液压泵马达被布置为选择性地将可变量的动力传递到所述一个或多个风扇或从所述一个或多个风扇传递可变量的动力以便控制一个或多个风扇的转速。

7. 发明公开

EP2163474A3 Blade pitch control 有权转让
标题翻译：叶片桨距控制
公开(公告)号：EP2163474A3
公开(公告)日：2017-05-24
申请号：EP09251853.9
申请日：2009-07-23
申请人： Rolls-Royce plc
发明人： David Michael Gainford , Jonathan Edmund Holt , Stephen Granville Garner
IPC分类号： B64C11/30 , B64C11/48 , F01D7/00
CPC分类号： F01D7/00 , B64C11/306 , B64C11/44 , B64C11/48 , B64D2027/005 , Y02T50/66
摘要： A method of controlling blade pitch angle, comprising the steps of:
comparing demanded (54,56) and measured (58,74) blade pitch angle and calculating any difference (62,74) therebetween,
in a primary electrical control system (50), where there is a difference (62), applying torque (66) to a blade pitch regulator (68) to reduce the magnitude of the difference (62) to zero, and
in a secondary electrical control system (52), where the difference (76) is greater than a pre-determined threshold (86), applying torque (80) to a blade pitch regulator (82) to reduce the magnitude of the difference (76) to the threshold (86).
Also an electrical system of blade pitch angle control for a set of blades (23,24) comprising: primary (50) and secondary (52) electrical control systems, means for comparing (60,72) demanded (54,56) and measured (58,74) blade pitch angle and calculating any difference (62,76) therebetween, a look-up function (64,78) having the difference (62,76) as its input and outputting a required torque (66,80), and a torque regulator (68,82) to apply the required torque (66,80) to the set of blades (23,24).
摘要翻译：一种控制叶片桨距角的方法，包括以下步骤：在主电控制系统（50）中比较叶片桨距角的需求（54,56）和测量（58,74）并计算它们之间的差值（62,74），在存在差值（62）的情况下，将扭矩（66）施加到叶片斜度调节器（68）以将差值（62）的幅值减小到零，并且在次级电气控制系统（52）中，（76）大于预定阈值（86）时，向叶片斜度调节器（82）施加转矩（80）以将差值（76）的幅值减小到阈值（86）。用于一组叶片（23,24）的叶片桨距角控制的电气系统还包括：主要（50）和次要（52）电气控制系统，用于比较（60,72）需求（54,56）和测量（58,74）叶片俯仰角并计算它们之间的任何差值（62,76），将差值（62,76）作为其输入的查找函数（64,78）并输出所需扭矩（66,80）以及将所需扭矩（66,80）施加到该组叶片（23,24）的扭矩调节器（68,82）。

8. 发明授权

EP2481669B1 Attenuation of open rotor noise 有权转让
标题翻译：开放式转子噪音的衰减
公开(公告)号：EP2481669B1
公开(公告)日：2017-05-17
申请号：EP12151061.4
申请日：2012-01-13
申请人： Rolls-Royce plc
发明人： Kingan, Michael
IPC分类号： B64C7/02 , B64C11/48 , B64D29/00
CPC分类号： B64C7/02 , B64C11/48 , B64C2230/14 , B64D29/00 , B64D2027/005 , Y02T50/166 , Y02T50/66

9. 发明授权

EP2928769B1 PALE D'HELICE POUR TURBOMACHINE 有权
标题翻译： PROPELLERBLATTFÜRTURBOTRIEBWERK
公开(公告)号：EP2928769B1
公开(公告)日：2017-02-08
申请号：EP13815063.6
申请日：2013-12-05
申请人： Snecma
发明人： VLASTUIN, Jonathan , DEJEU, Clément, Marcel, Maurice
IPC分类号： B64C11/18 , B64C27/467 , F01D5/14
CPC分类号： B64C11/48 , B64C11/18 , B64D2027/005 , F01D5/141 , F01D5/145 , F05D2220/30 , F05D2240/30 , F05D2240/303 , F05D2240/307 , Y02T50/66 , Y02T50/673

10. 发明授权

EP2763893B1 TURBOMACHINE A HELICE(S) POUR AERONEF AVEC SYSTEME POUR CHANGER LE PAS DE L'HELICE 有权
标题翻译：与PROPELLERVERSTELLVORRICHTUNG飞机螺旋桨发动机
公开(公告)号：EP2763893B1
公开(公告)日：2017-01-11
申请号：EP12781132.1
申请日：2012-10-03
申请人： Safran Aircraft Engines , GE Aviation Systems Limited
发明人： ESCURE, Didier, René, André , BOCQUET, Denis, Louis , CHARIER, Gilles, Alain , SZYMANDERA, Aleksander , MALITKA, Marek , SIKORSKI, Jan , CARRINGTON, Christopher
IPC分类号： B64C11/30 , B64C11/38 , F01D7/00
CPC分类号： B64C11/30 , B64C11/385 , B64D2027/005 , F01D1/26 , F02C3/067 , F02K3/072 , F05D2260/70 , Y02T50/66 , Y02T50/671

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