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1.发明公开PROCÉDÉ ET CONFIGURATION D'APPORT D'ÉNERGIE PROPULSIVE ET/OU NON PROPULSIVE DANS UNE ARCHITECTURE D'HÉLICOPTÈRE PAR UN MOTEUR AUXILIAIRE DE PUISSANCE 审中-公开方法和配置的辅助单元用于提供输入OR NOT驱动能量在直升机架构
公开(公告)号：EP2867122A1
公开(公告)日：2015-05-06
申请号：EP13733395.1
申请日：2013-06-12
申请人： Turbomeca , Microturbo , Labinal Power Systems
摘要： The invention aims to optimise all of the engine power available on a helicopter provided with an auxiliary engine by allowing that auxiliary engine to provide non-propulsive and/or propulsive energy during flight. For this purpose, this auxiliary engine is coupled in such a way as to be able to directly contribute to the supply of propulsive mechanical or electrical energy and non-propulsive electrical energy of the aircraft. An example configuration architecture comprises an onboard electrical network (2), two main engines (5a, 5b) and an energy conversion system for converting mechanical/electrical energy (6, 6a, 6b, 7) between a main gearbox BTP (40) transferring power to the propulsion members (4, 41) and means for receiving electrical energy comprising the onboard network (2) and a power electronics system (9) linked with starters (8) of the main engines (5a, 5b). The configuration also comprises an auxiliary power engine (3) supplying electrical energy to the means for receiving electrical energy (2, 9) via the energy conversion system (6, 6a, 6b, 7) and mechanical coupling means (8a, 11a to 11d) between the auxiliary engine (3, 0, 30) and at least one propulsion means (4, 41).
摘要翻译： 一种方法和配置通过允许发动机在飞行期间提供非推进和/或推进力，以优化在直升机包括上辅机可用整个系统上的牵引力。 辅助引擎被耦合到在所述飞机提供机械或电推进动力和电力的非推进动力直接参与。 的架构的配置包括一个板上的供电网络中，两个主发动机，和用于向所述推进构件机械能转换成电能的主变速箱之间和机构接收电能，包括机载网络和电力电子系统中的 结合主发动机的起动。 辅助动力引擎提供电能给机构用于通过能量转换系统和用于辅助发动机和至少一个推进构件之间的机械耦合的机理接收电能。
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2.发明公开
公开(公告)号：EP2861493A1
公开(公告)日：2015-04-22
申请号：EP13733392.8
申请日：2013-06-12
申请人： Turbomeca , Microturbo
IPC分类号： B64D35/08
CPC分类号： B64D35/08 , B64D41/00 , B64D2041/002 , F02C6/02 , F02C7/277 , F05D2220/329 , Y02T50/53
摘要： The aim of the invention is to optimize the entirety of the drive power available in a helicopter by using an auxiliary motor to supply power to the equipment and accessories of the helicopter that are connected to the engines. In an example of an optimized power transfer architecture for implementing the invention, the main engines (1, 1') and the APU group (8), as an auxiliary motor, comprise a gas generator (2; 81) connected, for the main engines (1, 1'), to the gearboxes (6) and accessory boxes (7) of mechanical, electric, and/or hydraulic power sockets, and connected, for the APU group (8), to at least one power conversion member (83, 84, 11). The power conversion member (83, 84, 11) of the APU group (8) is connected to the equipment and accessories via the gearbox (6) and/or via the accessory box (7) of the main engines (1, 1').
摘要翻译： 的方法和体系结构通过使用辅助发动机的将能量提供给设备和连接到所述发动机的直升机的配件，以优化在直升机上可用的整个系统上的牵引力。 主发动机和在APU单元，作为辅助发动机，包括连接到气体发生器，对于主发动机，减速齿轮箱和用于机械，电气和/或液压动力输出附件齿轮箱和连接到，对于 APU单元，至少一个电力转换构件。 APU装置的功率转换部件由所述减速齿轮箱和/或所述主发动机的附件齿轮箱连接到所述的设备和附件。
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3.发明公开
公开(公告)号：EP2582923A1
公开(公告)日：2013-04-24
申请号：EP11735492.8
申请日：2011-06-14
申请人： Turbomeca
发明人： BEDRINE, Olivier , PATY, Gérard
摘要： The invention relates to a turbine engine (100) for a helicopter (200), said helicopter comprising a main gearbox, a rotor (204), and a speed-reducing device (206) that is placed entirely within the main gearbox (202) of the helicopter while being connected to said rotor, the turbine engine including a casing (102), a gas generator (114) having a gas generator shaft (115), and a free turbine (124) to be rotated by the gas flow generated by the gas generator, said free turbine comprising a free turbine shaft (128). According to the turbine engine of the invention, when the casing of the turbine engine is attached to the body of the helicopter, the free turbine shaft axially extends inside the main gearbox of the helicopter so as to be directly connected to the speed-reducing device.
摘要翻译： 一种用于直升机的涡轮发动机，所述直升机包括主变速箱，转子和减速装置，其完全容纳在直升机的主变速箱内，同时也连接到转子，所述涡轮发动机包括壳体，气体发生器 具有气体发生器轴和由气体发生器产生的气流驱动旋转的自由涡轮机，所述自由涡轮机包括自由涡轮机轴。 当涡轮发动机紧固到直升机的变速箱时，自由涡轮机轴轴向延伸到直升机的主变速箱中，以直接连接到减速装置。
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公开(公告)号：EP3259462A1
公开(公告)日：2017-12-27
申请号：EP16713955.9
申请日：2016-02-15
申请人： Turbomeca
摘要： The invention relates to a system (12) for recovering exhaust gas energy from at least one turboshaft engine, comprising a turbine (34) rotatably mounted about a recovery shaft (40), suitable for collecting at least one portion (14) of the exhaust gases, referred to as collected gases (14), and to expand said collected gases (14) into expanded gases (42) at a pressure lower than the atmospheric pressure, a first heat exchanger (44), suitable for cooling said expanded gases (42) into cooled gases (46), by means of a cold source (45), and a compressor (36) rotatably mounted about said recovery shaft (40), suitable for compressing said cooled gases (46) to atmospheric pressure.
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公开(公告)号：EP2591219A1
公开(公告)日：2013-05-15
申请号：EP11743295.5
申请日：2011-07-05
申请人： Turbomeca
IPC分类号： F02C6/02
摘要： The invention aims to get around the problems of size, mass or reliability. To do this, energy is recovered in the exhaust nozzle, converted and recirculated using mechanical and/or electrical power recombining means. An example of an architecture of a turbomachine according to the invention includes a main turbine engine (1) and a heat exchanger (18) positioned in the exhaust nozzle (70) and coupled, via pipes (18a and 18b), to an independent system (16) that converts thermal energy into mechanical energy. This independent system (16) is connected to localized (Z1) mechanical recombination means (20) via a power shaft (15) to supply power to a power transmission shaft (80) according to aircraft requirements.
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公开(公告)号：EP2281109A1
公开(公告)日：2011-02-09
申请号：EP09725475.9
申请日：2009-03-24
申请人： Turbomeca
CPC分类号： F01D15/10 , F02C3/103 , F02C7/275 , F05D2220/329 , F05D2220/76 , F05D2260/85
摘要： The invention relates to a turbine engine (10) particularly for a helicopter, which comprises a gas generator (12) and a free turbine (14) rotated by a gas flow (F) generated by the gas generator, wherein the turbine engine further includes a reversible electric machine (30) that can be coupled to the gas generator, said reversible electric machine being capable of rotating the gas generator (12) during the starting phase of the turbine engine. The invention is characterised in that the reversible electric machine (30) can also be coupled to the free turbine (12) after the starting phase of the turbine engine in order to generate electric power.
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公开(公告)号：EP2699819A1
公开(公告)日：2014-02-26
申请号：EP12722408.7
申请日：2012-04-12
申请人： Turbomeca
发明人： DESCUBES, Olivier, Pierre , BEDRINE, Olivier , LADEVEZE, Isabelle, Germaine, Claude , PY, Jean-Michel, Pierre, Claude
CPC分类号： F16D9/06 , F04D13/021 , F04D13/022 , F04D15/0077 , F04D27/008 , F04D27/0292 , F04D29/05 , F16D9/08 , F16D2127/002 , Y10T403/11
摘要： The invention relates to the field of mechanical protection devices comprising a transmission shaft (1) with a main axis of rotation (X) and an element (2) that can rupture in the event of a torsional overload, and in particular to a mechanical protection device further comprising a mobile part (3) secured to the transmission shaft (1) in rotation about the main axis (X) and able to move radially outwards with respect to the main axis (X) from a first position to a second position, a spring (4) for urging the mobile part (3) towards the first position, and a tangential end stop (8) able to arrest the rotation of the mobile part (3) about the main axis (X) when the mobile part (3) is in the second position. The mobile part (3) and the spring (4) are calibrated so that once a predetermined triggering angular velocity has been reached, the mobile part (3) moves from the first into the second position under the effect of a centrifugal force that is stronger than the preload of the spring (4).
摘要翻译： 一种机械保护装置，包括：具有主轴旋转的传动轴和在扭转过载下易碎的元件; 固定在所述传动轴上以便绕所述主轴线旋转并被构造成相对于所述主轴线从第一位置向第二位置径向向外移动的可移动部件; 向第一位置推动可动构件的弹簧; 以及切向邻接构造成当所述可动构件处于所述第二位置时，所述切向邻接构造成停止所述可移动构件围绕所述主轴线的旋转。 可移动部件和弹簧被校准，使得从预定的触发角速度可移动部件在大于弹簧的预应力的离心力的作用下从第一位置移动到第二位置。
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公开(公告)号：EP2281109B1
公开(公告)日：2013-01-02
申请号：EP09725475.9
申请日：2009-03-24
申请人： Turbomeca
CPC分类号： F01D15/10 , F02C3/103 , F02C7/275 , F05D2220/329 , F05D2220/76 , F05D2260/85
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