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51 条记录 (耗时 0.031 秒)

    Turbojet engine start system
    1.
    发明授权
    Turbojet engine start system 失效
    涡轮喷气发动机启动系统

    公开(公告)号：US5913807A

    公开(公告)日：1999-06-22

    申请号：US50527

    申请日：1998-03-30

    申请人： Michael J. Bak

    发明人： Michael J. Bak

    IPC分类号： F02C7/22 ,  F02C7/26 ,  F02C7/272

    CPC分类号： F02C7/272 ,  F02C7/22 ,  F02C7/26

    摘要： A turbojet engine one-shot start system utilizes ignition and fuel delivery system components capable of pneumatic actuation and pressurization to initiate the engine start sequence thereby obviating the need for expensive shielded electrical controls and pumps.

    摘要翻译： 涡轮喷气发动机单速启动系统利用能够进行气动致动和加压的点火和燃料输送系统组件来启动发动机起动顺序，从而避免需要昂贵的屏蔽电气控制和泵。

    Secondary ignition system
    2.
    发明授权
    Secondary ignition system 失效
    二次点火系统

    公开(公告)号：US5174106A

    公开(公告)日：1992-12-29

    申请号：US573100

    申请日：1990-08-24

    申请人： Kevin J. Maikis

    发明人： Kevin J. Maikis

    IPC分类号： F02C7/264 ,  F02C7/272

    CPC分类号： F02C7/264 ,  F02C7/272

    摘要： An apparatus and method for igniting a secondary pyrotechnic charge is provided, which uses hot gases produced by a first generating means to effect the secondary ignition.The hot gases from the heat generating means are directed through a heat transfer member in a second generating means, and heat from the gases is transferred to the secondary pyrotechnic charge, which is associated with the heat transfer member. Once ignited, the secondary charge provides flames and hot gases to effect the purpose of the application at hand, e.g., jet engine burner ignition.

    摘要翻译： 提供一种用于点燃次级烟火装置的装置和方法，其使用由第一发生装置产生的热气体来实现二次点燃。 来自发热装置的热气体被引导通过第二发生装置中的传热构件，并且来自气体的热量被传递到与传热构件相关联的二次烟火装料。 一旦点燃，次级电荷提供火焰和热气体以实现手头应用的目的，例如喷气发动机燃烧器点火。

    DRIVE CHAIN FOR A HELICOPTER INCORPORATING A PYROTECHNIC ASSISTANCE DRIVE MODULE AND HELICOPTER COMPRISING THE SAME
    7.
    发明申请
    DRIVE CHAIN FOR A HELICOPTER INCORPORATING A PYROTECHNIC ASSISTANCE DRIVE MODULE AND HELICOPTER COMPRISING THE SAME 审中-公开
    配有PYROTECHNIC辅助驱动模块的直升机的驱动链和包括它的直升机

    公开(公告)号：US20170015411A1

    公开(公告)日：2017-01-19

    申请号：US15300739

    申请日：2015-03-30

    申请人： SAFRAN HELICOPTER ENGINES

    发明人： Jean-Louis Robert Guy BESSE

    IPC分类号： B64C27/14 ,  F01D13/00 ,  F02C7/272 ,  B64C27/00

    CPC分类号： B64C27/14 ,  B64C27/006 ,  B64C27/06 ,  F01D13/003 ,  F02C7/272 ,  F05D2220/329 ,  Y02T50/671

    摘要： The invention relates to a drive chain for driving the rotor(s) (21, 22) of a helicopter, comprising a main transmission gearbox (24) capable of driving the rotor(s) (21, 22) when said gearbox is moving, a main engine (23) for providing the power for the flight, and at least one assistance drive module (31), the main engine (23) and the assistance drive module (31) being mechanically connected to said main transmission gearbox (24) so as to induce the movement of said gearbox. The drive chain is characterised in that the assistance drive module comprises a pyrotechnic device for generating a torque on a power transmission shaft that is mechanically connected to the main transmission gearbox (24). The invention also relates to a helicopter comprising said drive chain.

    摘要翻译： 本发明涉及一种用于驱动直升机的转子（21,22）的驱动链，包括当所述变速箱运动时能够驱动转子（21,22）的主传动齿轮箱（24） 用于提供用于飞行的动力的主发动机（23）和至少一个辅助驱动模块（31），主发动机（23）和辅助驱动模块（31）机械连接到所述主变速箱（24） 以便引起所述变速箱的运动。 驱动链的特征在于辅助驱动模块包括用于在与主变速箱（24）机械连接的动力传动轴上产生扭矩的烟火装置。 本发明还涉及一种包括所述驱动链的直升机。

    METHOD AND SYSTEM FOR THE EMERGENCY START-UP OF AN ENERGY GENERATOR SET
    8.
    发明申请
    METHOD AND SYSTEM FOR THE EMERGENCY START-UP OF AN ENERGY GENERATOR SET 审中-公开
    能源发电机组紧急启动方法与系统

    公开(公告)号：US20150128592A1

    公开(公告)日：2015-05-14

    申请号：US14396235

    申请日：2013-04-18

    申请人： TURBOMECA

    发明人： Hugues Filiputti ,  Franck Garde ,  Romain Thiriet

    IPC分类号： F02C7/272 ,  F02C7/275

    CPC分类号： F02C7/272 ,  F02C7/26 ,  F02C7/275 ,  Y02T50/671

    摘要： An emergency starter that allows responsiveness within a few seconds, without having disadvantages associated with mass and size of a back-up hydraulic or pneumatic starter. An instantaneous gas thrust of pyrotechnic type is coupled with a positive displacement transmission generator in conjunction with automatic coupling to/uncoupling from a set that is to be started. An emergency start-up system includes at least one pyrotechnic gas generator connected to an electrical initiator itself connected to a computer, a positive displacement motor housing straight-cut gears, the pyrotechnic gas generator being coupled to the motor by an inlet in the casing. The motor includes a mechanism of connection capable of moving at one end of the drive shaft configured to couple the transmission shaft to a driven shaft of the set that is to be started via a centrifugal clutch.

    摘要翻译： 一个紧急启动器，可在几秒钟内响应能力，而不会造成与备用液压或气动起动器的质量和尺寸相关的缺点。 烟火类型的瞬时气体推力与正位移传动发生器耦合，并与要启动的组的自动耦合/解耦。 紧急启动系统包括连接到连接到计算机的电启动器本身的至少一个烟火气体发生器，容纳直切齿轮的正位移电动机，烟火气体发生器通过壳体中的入口联接到电动机。 电动机包括能够在驱动轴的一端移动的机构，该机构构造成通过离心式离合器将传动轴联接到待启动的组的从动轴。

    Gas turbine engine starting
    9.
    发明授权
    Gas turbine engine starting 失效
    燃气轮机起动

    公开(公告)号：US5253470A

    公开(公告)日：1993-10-19

    申请号：US916669

    申请日：1992-07-22

    申请人： Arnold C. Newton

    发明人： Arnold C. Newton

    IPC分类号： F02C7/06 ,  F02C7/272

    CPC分类号： F02C7/272 ,  F02C7/06

    摘要： A ducted fan gas turbine engine (10) is provided with an electric motor starter unit (16). The oil lubrication system of the engine (10) is so arranged that during engine starting, the heat generated by the starter unit (16) is used to heat up the oil in the system. This reduces the viscosity of the oil, thereby facilitating easy engine starting under very cold conditions.

    摘要翻译： 风管式燃气涡轮发动机（10）设置有电动机起动器单元（16）。 发动机（10）的油润滑系统被布置成使得在发动机启动期间，由起动器单元（16）产生的热量用于加热系统中的油。 这降低了油的粘度，从而便于发动机在非常冷的条件下起动。

    Propulsion turbine fuel control system
    10.
    发明授权
    Propulsion turbine fuel control system 失效
    推进涡轮燃油控制系统

    公开(公告)号：US5115638A

    公开(公告)日：1992-05-26

    申请号：US461746

    申请日：1990-01-08

    申请人： Wendell E. Reed ,  Malcolm J. McArthur

    发明人： Wendell E. Reed ,  Malcolm J. McArthur

    IPC分类号： F02C7/272 ,  F02C9/26

    CPC分类号： F02C9/26 ,  F02C7/272

    摘要： A fuel control system for a small gas turbine propulsion engine which enables a long term storage with fuel combined with a rapid start and operation as well as rapid stable control of the fuel flow. The control system includes an electrically controlled servo valve disposed upstream of a fuel pump, with the valve and pressure sensing cavities of a differential pressure control device being maintained full of fuel for a long term storage. Leakproof-type flexure pivots are provided for transmitting motion of an electrical torque motor to the servo valve and transmitting motion of a diaphragm to a throttle located downstream of the fuel pump. A frangible diaphragm is provided at the pump inlet which is adapted to be fractured or otherwise opened to activate the system upon a start-up of the turbine engine and, for this purpose, pressurized gas may be used to temporarily pressurize a fuel tank to burst the frangible diaphragm. The fuel flow is proportional to an applied electric current and independent of the tank or engine pressures, with the electric current being controlled by an electronic controller.

    摘要翻译： 一种用于小型燃气轮机推进发动机的燃料控制系统，其能够长期储存燃料并结合快速启动和操作以及快速稳定地控制燃料流。 控制系统包括设置在燃料泵上游的电控伺服阀，差压控制装置的阀和压力感应腔保持充满燃料以进行长期储存。 提供防漏型挠曲枢轴，用于将电动力矩马达的运动传递到伺服阀，并将隔膜的运动传递到位于燃料泵下游的节气门。 在泵入口处设置易碎隔膜，其适于断裂或以其他方式打开以在涡轮发动机起动时启动系统，并且为此目的，可以使用加压气体来暂时加压燃料箱以使其爆裂 易碎隔膜 燃料流量与施加的电流成比例，而与油箱或发动机压力无关，电流由电子控制器控制。