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公开(公告)号：US08919096B2
公开(公告)日：2014-12-30
申请号：US12867835
申请日：2009-02-13
CPC分类号： F02K1/763 , F05D2260/40 , Y02T50/671
摘要： A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.
摘要翻译： 一种用于控制涡轮喷气发动机的多个不同功能的控制系统，每个功能与相应的致动装置相关联。 该系统包括：适于向每个致动装置提供机械能的电动机; 用于电动机的电子控制单元; 以及插入在所述电动机和所述致动装置之间的至少一个开关装置，所述开关装置用于将由所述电动机供应的机械能选择性地分配到所述致动装置中的一个。
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公开(公告)号：US20110048028A1
公开(公告)日：2011-03-03
申请号：US12867835
申请日：2009-02-13
IPC分类号： F02C9/00
CPC分类号： F02K1/763 , F05D2260/40 , Y02T50/671
摘要： A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.
摘要翻译： 一种用于控制涡轮喷气发动机的多个不同功能的控制系统，每个功能与相应的致动装置相关联。 该系统包括：适于向每个致动装置提供机械能的电动机; 用于电动机的电子控制单元; 以及插入在所述电动机和所述致动装置之间的至少一个开关装置，所述开关装置用于将由所述电动机供应的机械能选择性地分配给所述致动装置中的一个。
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公开(公告)号：US09233759B2
公开(公告)日：2016-01-12
申请号：US13703497
申请日：2011-06-06
摘要： An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.
摘要翻译： 一种飞机供电电路，包括：飞机上的配电网，位于飞机发动机或发动机附近的电气设备; 以及内置于飞行器发动机中的电源发生器，以向除冰或防冰系统提供交流电压。 电源发生器通过用于向致动器提供直流电压电力的整流器连接到推力反向器机电致动器。
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公开(公告)号：US20130206902A1
公开(公告)日：2013-08-15
申请号：US13703497
申请日：2011-06-06
摘要： An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.
摘要翻译： 一种飞机供电电路，包括：飞机上的配电网，位于飞机发动机或发动机附近的电气设备; 以及内置于飞行器发动机中的电源发生器，以向除冰或防冰系统提供交流电压。 电源发生器通过用于向致动器提供直流电压电力的整流器连接到推力反向器机电致动器。
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5.发明授权Regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine 有权调节从发动机推进的飞行器的燃料回路中获取的燃料的流量公开(公告)号：US08484977B2
公开(公告)日：2013-07-16
申请号：US12499391
申请日：2009-07-08
IPC分类号： F02C9/00
CPC分类号： F02C7/236 , F02C7/32 , F02C7/36 , F02C9/30 , F02C9/56 , F05D2220/323 , F05D2270/304 , F05D2270/31 , Y02T50/671
摘要： The invention relates to a device for regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine. The device comprises: a positive displacement pump receiving fuel from a fuel circuit of the aircraft and delivering fuel at a flow rate that is proportional to its speed of rotation; a differential gear having a predefined transmission ratio, a first inlet mechanically coupled to the aircraft engine, a second inlet mechanically coupled to an electric motor/generator, and an outlet mechanically coupled to the positive displacement pump to drive it in rotation; and an electronic control system for regulating the speed of rotation of the electric motor/generator as a function of a setpoint value for the flow rate of fuel to be injected.
摘要翻译： 本发明涉及一种用于调节从由发动机推进的飞行器的燃料回路获取的燃料的流量的装置。 该装置包括：容积式泵，其从飞行器的燃料回路接收燃料并以与其旋转速度成比例的流量输送燃料; 具有预定传动比的差速齿轮，机械联接到飞行器发动机的第一入口，机械耦合到电动机/发电机的第二入口，以及机械联接到所述正排量泵以驱动其旋转的出口; 以及用于根据要喷射的燃料的流量的设定点值来调节电动机/发电机的转速的电子控制系统。
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公开(公告)号：US20120266600A1
公开(公告)日：2012-10-25
申请号：US13500756
申请日：2010-09-30
IPC分类号： F02C7/22
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.
摘要翻译： 一种用于航空发动机的燃料供给电路，该电路包括包括第一和第二容积式泵的高压泵送系统，液压致动器和燃料计量单元。 作为致动器的滑动位置的函数，致动器的进料孔可以连接到连接到第二泵的出口的高压输送孔，或连接到低压输送孔 压力进料管线。 燃料计量单元包括贯穿部分，这些通过部分中的一个连接到高压泵送系统的出口，另一个通过部分连接到高压泵送系统的出口，并通向高压引燃器 液压执行器的腔室。
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公开(公告)号：US20120260658A1
公开(公告)日：2012-10-18
申请号：US13500499
申请日：2010-09-30
申请人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
发明人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
IPC分类号： F02C7/236
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.
摘要翻译： 一种用于航空发动机的燃料供给回路，该回路包括用于将燃料高压地输送到燃烧室喷射器的高压泵送系统，所述高压泵送系统包括由发动机同时驱动的第一和第二正排量齿轮泵。 液压开关构件介于泵的相应出口之间，这使得在一个状态下可以组合来自两个泵的出口流将高压燃料输送到燃烧室喷射器，并且在另一种状态下排出一些 或从第一泵到低压进料管线的所有出口流量，用于使液压开关构件从一个状态传递到另一个状态的电气控制构件。
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8.发明授权Method and device for determining the capacity of an aircraft pump to deliver a predetermined fuel output 有权用于确定飞机泵输送预定燃料输出的能力的方法和装置公开(公告)号：US09249683B2
公开(公告)日：2016-02-02
申请号：US13372777
申请日：2012-02-14
申请人： Nicolas Alain Bader
发明人： Nicolas Alain Bader
CPC分类号： F01D21/003 , F02C7/236 , F04C14/08 , F05D2260/80 , F05D2260/85
摘要： The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, characterised in that it comprises a step of rotating the pump at a predetermined speed; a step of supplying at least one cylinder with the totality of the fuel coming out of the pump; a step of determining the fuel flow rate supplying said cylinder, and a diagnostic step which consists in determining whether the pump is able to supply a sufficient flow rate as a function of the determined value of the flow rate supplying the cylinder. The invention also proposes a device implementing the method.
摘要翻译： 本发明提出了一种用于确定飞机泵输送预定燃料流量的能力的方法，其特征在于它包括以预定速度旋转泵的步骤; 提供至少一个气缸的步骤，其中所述燃料从泵中排出; 确定供应所述气缸的燃料流量的步骤，以及诊断步骤，其包括确定所述泵是否能够提供足够的流量，作为所确定的提供所述气缸的流量值的函数。 本发明还提出了实现该方法的装置。
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9.发明授权Fuel feed circuit for an aeroengine having a high pressure pump system with two pumps 有权具有两个泵的高压泵系统的航空发动机的燃料供给回路公开(公告)号：US09500135B2
公开(公告)日：2016-11-22
申请号：US13500499
申请日：2010-09-30
申请人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
发明人： Nicolas Alain Bader , Regis Michel Paul Deldalle , Laurent Gilbert Yves Hodinot , Nicolas Potel
摘要： A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.
摘要翻译： 一种用于航空发动机的燃料供给回路，该回路包括用于将燃料高压地输送到燃烧室喷射器的高压泵送系统，所述高压泵送系统包括由发动机同时驱动的第一和第二正排量齿轮泵。 液压开关构件介于泵的相应出口之间，这使得在一个状态下可以组合来自两个泵的出口流将高压燃料输送到燃烧室喷射器，并且在另一种状态下排出一些 或从第一泵到低压进料管线的所有出口流量，用于使液压开关构件从一个状态传递到另一个状态的电气控制构件。
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10.发明授权Device for monitoring the obstruction of at least two filters of a fluid circulation system of an aircraft gas turbine engine 有权用于监测飞机燃气涡轮发动机的流体循环系统的至少两个过滤器的阻塞的装置公开(公告)号：US08443654B2
公开(公告)日：2013-05-21
申请号：US13163141
申请日：2011-06-17
申请人： Nicolas Alain Bader , Thierry Poix , Nicolas Potel
发明人： Nicolas Alain Bader , Thierry Poix , Nicolas Potel
IPC分类号： G01M15/14
CPC分类号： B01D37/046 , B01D35/143 , B01D2201/54 , F23K5/06 , F23K5/18 , F23K2301/202 , F23R3/00
摘要： A device monitors an obstruction of two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft. A first obstruction sensor sends a first detection signal of an obstruction of a first filter. A second obstruction sensor sends a second detection signal of an obstruction of a second filter. A processor includes a monitoring input to measure the first and second detection signals. The first obstruction sensor includes a Wheatstone bridge including a strain gauge resistor. The second obstruction sensor is connected in parallel with the strain gauge resistor. The first detection signal is sent over a first predetermined variation range. The second detection signal is sent over a second predetermined variation range, distinct from the first variation range. The processor identifies the obstruction of one of the fluid filters as a function of one of the variation ranges of the detection signals.
摘要翻译： 一种装置监测飞机的燃气涡轮发动机的流体循环系统的两个流体过滤器的阻塞。 第一阻塞传感器发送第一滤波器的阻塞的第一检测信号。 第二阻塞传感器发送第二滤波器的阻塞的第二检测信号。 处理器包括用于测量第一和第二检测信号的监视输入。 第一阻塞传感器包括惠斯登电桥，其包括应变计电阻器。 第二阻塞传感器与应变计电阻并联连接。 第一检测信号通过第一预定变化范围发送。 第二检测信号在与第一变化范围不同的第二预定变化范围内发送。 处理器根据检测信号的变化范围之一来识别流体滤波器之一的阻塞。
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