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1. 发明公开

EP3381809A1 PROCEDE DE COUPURE AUTOMATIQUE DES MOTEURS D'UN AERONEF BIMOTEUR 有权
公开(公告)号：EP3381809A1
公开(公告)日：2018-10-03
申请号：EP18153344.9
申请日：2018-01-25
申请人： Airbus Operations S.A.S.
发明人： BEL, Laurent
IPC分类号： B64D31/06 , F02C9/42 , B64D45/00
CPC分类号： B64D31/06 , B64D43/00 , B64D2045/0085 , F02C9/42 , F02C9/46 , F05D2260/80 , F05D2270/093 , F05D2270/13 , G07C5/0825
摘要： L'invention concerne un procédé de coupure automatique des moteurs d'un aéronef bimoteur (1) où chaque moteur (2,3) est piloté par une unité de contrôle (4,5) configurée pour activer automatiquement un mode de protection (résultant en la coupure quasi-instantanée du moteur) sur un moteur (2,3) qui lui est associé si le fonctionnement du moteur présente une anomalie de fonctionnement, l'aéronef comprenant en outre un dispositif d'interface (6) pour coordonner les unités de contrôle (4,5), le dispositif d'interface a deux modes de fonctionnement, la commutation de l'un ou de l'autre mode étant liée à la vitesse et à l'altitude de l'aéronef :
- dans le premier mode de fonctionnement, la coupure automatique ne peut se faire que sur le premier des deux moteurs (2,3) qui présente une anomalie de fonctionnement.
- dans le second mode de fonctionnement, typiquement mis en oeuvre en phase de vol de croisière, la coupure automatique pourra être mise en oeuvre sur un premier puis sur un second moteur (2,3) si le second moteur présente une anomalie de fonctionnement plus sévère que celle présentée par le premier moteur.

2. 发明公开

EP3084175A1 PROCEDE DE COMMANDE AUTOMATIQUE DU REGIME DE FONCTIONNEMENT D'UN TURBOMOTEUR D'UN HELICOPTERE, DISPOSITIF DE COMMANDE CORRESPONDANT ET HELICOPTERE EQUIPE D'UN TEL DISPOSITIF 有权转让
标题翻译：方法自动控制直升机高速轴发动机的运转，相关的控制方法和利用这样的装置EQUIPPED直升机
公开(公告)号：EP3084175A1
公开(公告)日：2016-10-26
申请号：EP14827845.0
申请日：2014-12-15
申请人： Turbomeca
发明人： SEVE, Caroline , POUMAREDE, Vincent , THIRIET, Romain
IPC分类号： F02C6/02 , B64D31/06 , F02C6/20 , F02C9/28
CPC分类号： B64D31/06 , F01D21/02 , F02C6/02 , F02C6/206 , F02C9/28 , F05D2220/329 , F05D2270/02 , F05D2270/07 , F05D2270/09 , F05D2270/093 , F05D2270/13 , Y02T50/671
摘要： The invention relates to a method for automatically controlling an operating speed of a helicopter turboshaft engine, including a step (10) of receiving data (27, 28, 29) that represent the flight of the helicopter; a step (11) of selecting the turboshaft engine for which a change in speed would be more relevant; a step (12) of determining an operating speed of said turboshaft engine, referred to as chosen speed, selected among a plurality of predetermined operating speeds; and a step (14) of controlling the operating speed of said turboshaft engine to said chosen speed. The invention also relates to a corresponding control device.
摘要翻译：本发明涉及一种用于在直升飞机的涡轮轴发动机的工作模式自动地控制，包括：接收数据的步骤（10）（27，28，29）确实是表示直升机的飞行; 选择为其时尚的变化是最相关的涡轮轴发动机的步骤（11）; 的说涡轮轴发动机，被称为所选择的模式，从预定的操作模式中的所选择的多个运行模式的确定性采矿的步骤（12）; 和排列所说涡轮轴发动机的工作模式到所述的步骤（14）中选择的模式。因此，本发明涉及一种相应的控制装置。

3. 发明授权

EP1279810B1 Fuel system 有权
标题翻译：燃料控制系统
公开(公告)号：EP1279810B1
公开(公告)日：2005-12-14
申请号：EP02255184.0
申请日：2002-07-24
申请人： Goodrich Control Systems Limited
发明人： Elliott, Philip Laurence
IPC分类号： F02C7/22 , F02C9/26 , F02C9/46
CPC分类号： F02C9/28 , F02C9/263 , F05D2270/021 , F05D2270/092 , F05D2270/093 , F05D2270/301 , F05D2270/304

4. 发明公开

EP1279810A3 Fuel system 有权
标题翻译：燃料控制系统
公开(公告)号：EP1279810A3
公开(公告)日：2004-05-19
申请号：EP02255184.0
申请日：2002-07-24
申请人： Goodrich Control Systems Limited
发明人： Elliott, Philip Laurence
IPC分类号： F02C7/22 , F02C9/26 , F02C9/46
CPC分类号： F02C9/28 , F02C9/263 , F05D2270/021 , F05D2270/092 , F05D2270/093 , F05D2270/301 , F05D2270/304
摘要： A fuel control system for a gas turbine engine comprising, a main fuel metering valve (11) for controlling the flow of fuel to a respective gas turbine engine in use, the valve (11) including a valve control member (13) moveable relative to a valve body (12) by fluid pressure applied to a pressure chamber (27) of the valve, to control the quantity of fuel supplied through the valve between zero in a valve closed condition and a maximum in a valve fully-open condition, a first fluid control valve (28) operable to control the application of fluid pressure to said pressure chamber (27) of said metering valve (11) to determine the setting of said metering valve and thus the quantity of fuel supplied to the gas turbine engine through the metering valve, means (30) for detecting an over-speed operating condition of the respective gas turbine engine in use, and a second fluid control valve (36) moveable from a first condition to a second condition in response to detection of such over-speed condition, said second fluid control valve (36) serving in said first condition to apply fluid pressure derived from said first fluid control valve (28) to said pressure chamber (27) of said metering valve (11), and serving in its said second condition to prevent the application of fluid pressure derived from said first fluid control valve (28) to said pressure chamber (27) of said metering valve (11) and to vent said pressure chamber (27) to permit said control member (13) of said metering valve to move towards a valve closed position.

5. 发明授权

EP2964945B1 MULTI-ENGINE AIRCRAFT WITH POWER BOOSTER SYSTEM 有权转让
公开(公告)号：EP2964945B1
公开(公告)日：2018-09-12
申请号：EP14766241.5
申请日：2014-02-18
申请人： Rolls-Royce Corporation
发明人： KARAM, Michael Abraham , HEATHCO, Craig , EIFERT, Andrew
IPC分类号： F02C7/045 , F02K3/12 , F02C3/30
CPC分类号： F02C7/045 , F02C1/02 , F02C3/13 , F02C3/305 , F02C6/04 , F02C6/06 , F02C6/08 , F02C6/14 , F02C6/16 , F02C7/26 , F02C7/262 , F02C7/27 , F02C9/18 , F02C9/50 , F02C9/52 , F02K3/12 , F05B2260/42 , F05B2270/103 , F05B2270/1031 , F05B2270/1033 , F05B2270/1073 , F05B2270/111 , F05D2260/42 , F05D2260/963 , F05D2270/05 , F05D2270/051 , F05D2270/093 , F05D2270/13 , F05D2270/3061
摘要： A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

6. 发明授权

EP3000986B1 PROCÉDÉ POUR ARRÊTER UN MOTEUR DE GIRAVION EN SURVITESSE ET GIRAVION ASSOCIÉ 有权
标题翻译： PROCÉDÉPOUR ARRESTER UN MOTEUR DE GIRAVION EN SURVITESSE ET GIRAVIONASSOCIÉE
公开(公告)号：EP3000986B1
公开(公告)日：2017-07-05
申请号：EP15182636.9
申请日：2015-08-27
申请人： Airbus Helicopters
发明人： CERTAIN, Bernard
IPC分类号： F01D21/02 , F02C3/10 , F02C9/28 , F02C9/46
CPC分类号： F02C9/28 , F01D21/00 , F01D21/003 , F01D21/02 , F01D21/04 , F01D21/06 , F01D21/14 , F02C3/04 , F02C3/10 , F02C7/22 , F02C9/26 , F02C9/46 , F05D2220/323 , F05D2220/329 , F05D2270/021 , F05D2270/09 , F05D2270/091 , F05D2270/093 , F05D2270/304 , F05D2270/331 , F05D2270/335

7. 发明公开

EP2964945A2 AIRCRAFT POWER SYSTEM 有权转让
标题翻译： FLUGZEUGENERGIESYSTEM
公开(公告)号：EP2964945A2
公开(公告)日：2016-01-13
申请号：EP14766241.5
申请日：2014-02-18
申请人： Rolls-Royce Corporation
发明人： KARAM, Michael Abraham , HEATHCO, Craig , EIFERT, Andrew
IPC分类号： F02K3/12 , F02C3/30
CPC分类号： F02C7/045 , F02C1/02 , F02C3/13 , F02C3/305 , F02C6/04 , F02C6/06 , F02C6/08 , F02C6/14 , F02C6/16 , F02C7/26 , F02C7/262 , F02C7/27 , F02C9/18 , F02C9/50 , F02C9/52 , F02K3/12 , F05B2260/42 , F05B2270/103 , F05B2270/1031 , F05B2270/1033 , F05B2270/1073 , F05B2270/111 , F05D2260/42 , F05D2260/963 , F05D2270/05 , F05D2270/051 , F05D2270/093 , F05D2270/13 , F05D2270/3061
摘要： A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
摘要翻译：公开了一种燃气涡轮发动机，其包括在一些实施例中能够被配置为用作谐振空间的旁路通道。谐振空间可用于衰减/加重/等待其他地方产生的噪声。旁路通道可以以多种方式配置以形成共振空间。例如，空间可以具有各种几何形状，配置等。在一个非限制性形式中，谐振空间可以衰减旁路管道前方的噪声。在另一个非限制性形式中，谐振空间可以衰减旁路管道的噪声。任何数量的变化是可能的。

8. 发明公开

EP2492451A2 Low pressure spool emergency generator 有权转让
标题翻译： Niederdruckwelle gekoppelter Notfallgenerator
公开(公告)号：EP2492451A2
公开(公告)日：2012-08-29
申请号：EP12157402.4
申请日：2012-02-28
申请人： Hamilton Sundstrand Corporation
发明人： Finney, Adam M. , Krenz, Michael , Wagner, Carl A. , Jacques, David L.
IPC分类号： F01D15/10 , F02C7/32 , F02C7/36 , B64D41/00
CPC分类号： F02C7/32 , B64D41/00 , F01D15/10 , F02C7/36 , F05D2220/50 , F05D2220/76 , F05D2270/09 , F05D2270/091 , F05D2270/093
摘要： An emergency power system (54) is useable on an aircraft having a gas turbine engine (10) with a low pressure spool (20) and a high pressure spool (28). The emergency power system (54) includes an emergency electrical generator (48) coupled to the low pressure spool (20) during an emergency for generating emergency electrical power and one or more additional electrical power sources (48A,66,70,72,74). A plurality of electrical loads (78,78A) are electrically connected to the emergency electrical generator (48) and the one or more additional electrical power sources (48A,66,70,72,74). Aircraft sensors (96A-96G) provide data regarding emergency electrical power availability and emergency electrical power demand. A controller (94) for controlling the emergency electrical generator determines emergency electrical power demand and emergency electrical power availability based upon data from the aircraft sensors (96A-96G). The controller (94) controls the emergency electrical generator (48) based upon the emergency electrical power demand and the emergency electrical power availability.
摘要翻译：应急电力系统（54）可用于具有带有低压阀芯（20）和高压阀芯（28）的燃气涡轮发动机（10）的飞机上。紧急电力系统（54）包括在紧急情况期间联接到低压线轴（20）的紧急电力发生器（48），用于产生紧急电力和一个或多个附加电力源（48A，66,70,72,74 ）。多个电负载（78,78A）电连接到紧急发电机（48）和一个或多个附加电源（48A，66,70,72,74）。飞机传感器（96A-96G）提供有关应急电力可用性和应急电力需求的数据。用于控制应急发电机的控制器（94）基于来自飞行器传感器（96A-96G）的数据来确定应急电力需求和应急电力可用性。控制器（94）基于紧急电力需求和紧急电力可用性来控制紧急发电机（48）。

10. 发明公开

EP3123020A1 PROCEDE DE DETECTION D'UNE DEFAILLANCE D'UN PREMIER TURBOMOTEUR D'UN HELICOPTERE BIMOTEUR ET DE COMMANDE DU SECOND TURBOMOTEUR, ET DISPOSITIF CORRESPONDANT 有权
标题翻译：检测方法的失败第一涡轮发动机的双引擎直升机操作的第二涡轮发动机关联装置作者：
公开(公告)号：EP3123020A1
公开(公告)日：2017-02-01
申请号：EP15717551.4
申请日：2015-03-20
申请人： Safran Helicopter Engines
发明人： LESCHER, Fabien , MARIN, Jean Philippe, Jacques , ETCHEPARE, Philippe
IPC分类号： F02K3/12 , B64D31/12 , F02C3/10 , F02C9/46 , F02C9/56
CPC分类号： F02C9/56 , B64D31/06 , F02C3/10 , F02C9/46 , F02K3/12 , F05D2220/329 , F05D2270/091 , F05D2270/093 , F05D2270/095 , F05D2270/335 , Y02T50/671
摘要： The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4, 5) comprising protection end stops regulated by a regulating device which define a maximum power speed, characterized in that it comprises: a step (10) of detecting a fault index of said faulty engine (4); a step (11) of modifying said end stops for protecting said sound engine (5) to protection end stops corresponding to a maximum power single-engine speed, in the event of a fault index being detected; a step (12) of confirming a fault with said faulty engine (4); a step (13) of commanding an increase in the rate of supply of fuel to said sound engine (5) in the event of the fault being confirmed.
摘要翻译：本发明涉及一种用于在一个第一涡轮轴发动机检测故障，由被称为上不起作用发动机（4），双发动机直升机的，并用于控制第二涡轮轴发动机，通过被称为健康发动机（5）中，每个发动机（4，5）包括由调节装置限定的最大功率政权调节保护停止，DASS它包括：检测到所述非操作发动机（4）的故障的指示的步骤（10）; 修改所述健康发动机（5）转换成其对应于最大功率的单引擎制度，在发生故障的所检测的指示的情况下，保护停止的所述保护停止的步骤（11）; 的故障的步骤（12），确认所述失效发动机（4）; 控制，以增加在健康所述发动机（5）的燃料供给的流量，在一个确认失败的情况下的步骤（13）。

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