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1. 发明申请

US20120046896A1 MONITORING PARTICLES IN A LUBRICATION SYSTEM 有权
标题翻译：在润滑系统中监测颗粒
公开(公告)号：US20120046896A1
公开(公告)日：2012-02-23
申请号：US13210012
申请日：2011-08-15
申请人： Xavier FLANDROIS , Jean-Rémi André Masse , Maurice Georges Vernochet
发明人： Xavier FLANDROIS , Jean-Rémi André Masse , Maurice Georges Vernochet
IPC分类号： G06F19/00
CPC分类号： F16N29/00 , F16N2200/04 , F16N2200/14 , G01N27/10 , G01N33/2888
摘要： A process for monitoring a machine including moving pieces, a lubrication system and an electromagnetic sensor fitted with a magnet and two electrodes is disclosed. The sensor is capable of collecting particles present in the lubrication system between the electrodes. The monitoring process includes a step for obtaining measurements of resistance between the electrodes of the sensor, taken during an operating period of the machine; a step for determining from said measurements a first autoregressive mathematical model characterizing the resistance; a step for comparison between the first model and a predetermined reference model; and a step for working out an opinion on maintenance of the machine as a function of the comparison result.
摘要翻译：公开了一种用于监测包括移动件，润滑系统和装配有磁体和电极的电磁传感器的机器的过程。传感器能够收集电极之间存在于润滑系统中的颗粒。该监视过程包括一个步骤，用于获得传感器的电极之间的电阻测量值，该电极在机器的运行期间中被采集; 从所述测量确定表征所述电阻的第一自回归数学模型的步骤; 第一模型和预定参考模型之间的比较步骤; 以及作为比较结果的函数来确定机器的维护意见的步骤。

2. 发明授权

US08756026B2 Monitoring particles in a lubrication system 有权
标题翻译：监控润滑系统中的颗粒
公开(公告)号：US08756026B2
公开(公告)日：2014-06-17
申请号：US13210012
申请日：2011-08-15
申请人： Xavier Flandrois , Jean-Rémi André Masse , Maurice Georges Vernochet
发明人： Xavier Flandrois , Jean-Rémi André Masse , Maurice Georges Vernochet
IPC分类号： G06F19/00 , G01R27/00 , F16N29/00 , G01N33/28 , G01N27/10
CPC分类号： F16N29/00 , F16N2200/04 , F16N2200/14 , G01N27/10 , G01N33/2888
摘要： A process for monitoring a machine including moving pieces, a lubrication system and an electromagnetic sensor fitted with a magnet and two electrodes is disclosed. The sensor is capable of collecting particles present in the lubrication system between the electrodes. The monitoring process includes a step for obtaining measurements of resistance between the electrodes of the sensor, taken during an operating period of the machine; a step for determining from said measurements a first autoregressive mathematical model characterizing the resistance; a step for comparison between the first model and a predetermined reference model; and a step for working out an opinion on maintenance of the machine as a function of the comparison result.
摘要翻译：公开了一种用于监测包括移动件，润滑系统和装配有磁体和电极的电磁传感器的机器的过程。传感器能够收集电极之间存在于润滑系统中的颗粒。该监视过程包括一个步骤，用于获得传感器的电极之间的电阻测量值，该电极在机器的运行期间内被采集; 从所述测量确定表征所述电阻的第一自回归数学模型的步骤; 第一模型和预定参考模型之间的比较步骤; 以及作为比较结果的函数来确定机器的维护意见的步骤。

3. 发明申请

US20080258560A1 Electric Supply for an Aircraft Gas Turbine Engine Equipment 有权
标题翻译：飞机燃气轮机发动机设备供电
公开(公告)号：US20080258560A1
公开(公告)日：2008-10-23
申请号：US11816423
申请日：2006-02-17
申请人： Gilles Guy Dubois , Regis Bernard Albert Meuret , Maurice Georges Vernochet
发明人： Gilles Guy Dubois , Regis Bernard Albert Meuret , Maurice Georges Vernochet
IPC分类号： H02J4/00 , B60L1/00
CPC分类号： H02J4/00 , Y10T307/25 , Y10T307/406 , Y10T307/615
摘要： A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.
摘要翻译：向燃气轮机飞机发动机供电和启动设备的设备，包括专用于发动机的电力供应电路，并且与飞机上的电网不同的激励，控制或伺服电路，用于发动机。发动机电源电路包括向发动机的第一电气设备的激励，控制或伺服电路分配DC或AC电压的第一总线，将DC或AC电压分配给用于其他部件的激励，控制或伺服电路的第二总线与第一设备相比需要更高电力的发动机的电气设备，以及连接到从诸如飞机机载配电网络或专用于发动机和驱动的发电机的电源接收电力的第三总线从而。第三辆公交车用第一和第二辆公共汽车供电。

4. 发明授权

US09182310B2 Method and a device for correcting a measurement of the pressure of a gas stream flowing in an aircraft engine 有权
标题翻译：用于校正在飞行器发动机中流动的气流的压力测量的方法和装置
公开(公告)号：US09182310B2
公开(公告)日：2015-11-10
申请号：US13577776
申请日：2011-02-11
申请人： Bruno Robert Gaully , Maurice Georges Vernochet
发明人： Bruno Robert Gaully , Maurice Georges Vernochet
IPC分类号： G01L27/00 , F01D17/08 , G01L19/02 , F01D21/00
CPC分类号： G01L27/002 , F01D17/08 , F01D21/003 , F05D2200/12 , F05D2220/323 , F05D2260/80 , F05D2270/051 , G01L19/02
摘要： A method to correct a current measurement of pressure of a gas stream delivered during a mission by a sensor in the engine. The method includes: estimating a drift error affecting the sensor on the basis of a difference existing between: (1) a calibration measurement of the pressure of the gas stream as delivered by the sensor in the engine, and (2) an atmospheric pressure measurement delivered by a sensor of the aircraft presenting accuracy greater than that of the sensor in the engine; these measurements being performed while the sensor in the engine and the sensor of the aircraft are subjected to same surrounding atmospheric pressure; and subtracting the estimated drift error from the current measurement.
摘要翻译：一种用于校正在任务期间由发动机中的传感器传送的气流的当前压力测量的方法。该方法包括：基于以下之间存在的差异来估计影响传感器的漂移误差：（1）由发动机中的传感器传递的气流的压力的校准测量，以及（2）大气压力测量由飞行器的传感器提供的精度大于发动机中的传感器的精度; 在发动机中的传感器和飞行器的传感器经受相同的周围大气压力时进行这些测量; 并从当前测量中减去估计漂移误差。

5. 发明申请

US20130051426A1 DEVICE FOR MEASURING TEMPERATURE IN A PRIMARY STREAM FLOW PASSAGE OF A BYPASS TURBOJET 有权
标题翻译：用于测量旁路涡轮机主流流量中的温度的装置
公开(公告)号：US20130051426A1
公开(公告)日：2013-02-28
申请号：US13640648
申请日：2011-04-05
申请人： Bruno Robert Gaully , Thierry Poix , Maurice Georges Vernochet
发明人： Bruno Robert Gaully , Thierry Poix , Maurice Georges Vernochet
IPC分类号： G01K13/02
CPC分类号： G01K13/02 , F01D17/085 , F01D17/105 , F02C9/18 , F02C9/52 , G01K1/14
摘要： A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.
摘要翻译：一种用于测量旁通涡轮喷气发动机的一次流流道中的压缩机入口温度的装置。该装置包括气密中空结构，其形成涡轮喷气发动机的中间壳体的连接臂并且被配置为径向地通过用于主流的流动通道和用于涡轮喷气发动机的二次流的流动通道，连接臂包括至少一个入口空气孔口在压缩机的入口处打开到主流流动通道中，并且至少一个空气出口孔口通向涡轮喷气发动机的区域，其中周围压力小于主流道中的压力。压缩机; 以及温度探针，其敏感元件布置在连接臂的内部。

6. 发明授权

US09194755B2 Device for measuring temperature in a primary stream flow passage of a bypass turbojet 有权
标题翻译：用于测量旁通涡轮喷气发动机的一次流动通道中的温度的装置
公开(公告)号：US09194755B2
公开(公告)日：2015-11-24
申请号：US13640648
申请日：2011-04-05
申请人： Bruno Robert Gaully , Thierry Poix , Maurice Georges Vernochet
发明人： Bruno Robert Gaully , Thierry Poix , Maurice Georges Vernochet
IPC分类号： G01K1/14 , G01K13/02 , F01D17/08 , F01D17/10 , F02C9/18 , F02C9/52
CPC分类号： G01K13/02 , F01D17/085 , F01D17/105 , F02C9/18 , F02C9/52 , G01K1/14
摘要： A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.
摘要翻译：一种用于测量旁通涡轮喷气发动机的一次流流道中的压缩机入口温度的装置。该装置包括气密中空结构，其形成涡轮喷气发动机的中间壳体的连接臂并且被配置为径向地通过用于主流的流动通道和用于涡轮喷气发动机的二次流的流动通道，连接臂包括至少一个入口空气孔口在压缩机的入口处打开到主流流动通道中，并且至少一个空气出口孔口通向涡轮喷气发动机的区域，其中周围压力小于主流道中的压力。压缩机; 以及温度探针，其敏感元件布置在连接臂的内部。

7. 发明申请

US20130031949A1 METHOD AND A DEVICE FOR CORRECTING A MEASUREMENT OF THE PRESSURE OF A GAS STREAM FLOWING IN AN AIRCRAFT ENGINE 有权
标题翻译：用于校正在飞机发动机中流动的气流的压力测量的方法和装置
公开(公告)号：US20130031949A1
公开(公告)日：2013-02-07
申请号：US13577776
申请日：2011-02-11
申请人： Bruno Robert Gaully , Maurice Georges Vernochet
发明人： Bruno Robert Gaully , Maurice Georges Vernochet
IPC分类号： G01L27/00
CPC分类号： G01L27/002 , F01D17/08 , F01D21/003 , F05D2200/12 , F05D2220/323 , F05D2260/80 , F05D2270/051 , G01L19/02
摘要： A method to correct a current measurement of pressure of a gas stream delivered during a mission by a sensor in the engine. The method includes: estimating a drift error affecting the sensor on the basis of a difference existing between: (1) a calibration measurement of the pressure of the gas stream as delivered by the sensor in the engine, and (2) an atmospheric pressure measurement delivered by a sensor of the aircraft presenting accuracy greater than that of the sensor in the engine; these measurements being performed while the sensor in the engine and the sensor of the aircraft are subjected to same surrounding atmospheric pressure; and subtracting the estimated drift error from the current measurement.
摘要翻译：一种用于校正在任务期间由发动机中的传感器传送的气流的当前压力测量的方法。该方法包括：基于以下之间存在的差异来估计影响传感器的漂移误差：（1）由发动机中的传感器传递的气流的压力的校准测量，以及（2）大气压力测量由飞行器的传感器提供的精度大于发动机中的传感器的精度; 在发动机中的传感器和飞行器的传感器经受相同的周围大气压力时进行这些测量; 并从当前测量中减去估计漂移误差。

8. 发明授权

US07663264B2 Electric supply for an aircraft gas turbine engine equipment 有权
标题翻译：飞机燃气轮机发动机设备供电
公开(公告)号：US07663264B2
公开(公告)日：2010-02-16
申请号：US11816423
申请日：2006-02-17
申请人： Gilles Guy Dubois , Régis Bernard Albert Meuret , Maurice Georges Vernochet
发明人： Gilles Guy Dubois , Régis Bernard Albert Meuret , Maurice Georges Vernochet
IPC分类号： B60L1/00
CPC分类号： H02J4/00 , Y10T307/25 , Y10T307/406 , Y10T307/615
摘要： A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.
摘要翻译：向燃气轮机飞机发动机供电和启动设备的设备，包括专用于发动机的电力供应电路，并且与飞机上的电网不同的激励，控制或伺服电路，用于发动机。发动机电源电路包括向发动机的第一电气设备的激励，控制或伺服电路分配DC或AC电压的第一总线，将DC或AC电压分配给用于其他部件的激励，控制或伺服电路的第二总线与第一设备相比需要更高电力的发动机的电气设备，以及连接到从诸如飞机机载配电网络或专用于发动机和驱动的发电机的电源接收电力的第三总线从而。第三辆公交车用第一和第二辆公共汽车供电。

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