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1. 发明授权

US08831855B2 Method and a device for monitoring a servo-control loop of an actuator system for actuating variable-geometry components of a turbojet 有权
标题翻译：用于监测用于驱动涡轮喷气发动机的可变几何部件的致动器系统的伺服控制回路的方法和装置
公开(公告)号：US08831855B2
公开(公告)日：2014-09-09
申请号：US13278518
申请日：2011-10-21
申请人： Jean-Remi Andre Masse , Christian Aurousseau , Regis Michel Paul Deldalle , Xavier Flandrois , Aziz Sif
发明人： Jean-Remi Andre Masse , Christian Aurousseau , Regis Michel Paul Deldalle , Xavier Flandrois , Aziz Sif
IPC分类号： G06F19/00 , G05B23/02 , F02C9/00
CPC分类号： F02C9/00 , G05B23/02 , G05B23/0221
摘要： A method for monitoring a servo-control loop (3) of an actuator system (2) for actuating variable-geometry components of a turbojet, said method comprising: an estimation step of estimating a plurality of monitoring parameters from operating data of the servo-control loop (2); an evaluation step of evaluating a plurality of indicators from the monitoring parameters; an evaluation step for evaluating at least one signature matrix, each signature matrix being representative of the values of at least some of the indicators; and a detection and location step of detecting and locating a degradation affecting the servo-control loop as a function of said at least one signature matrix.
摘要翻译：一种用于监视用于驱动涡轮喷气发动机的可变几何部件的致动器系统（2）的伺服控制回路（3）的方法，所述方法包括：估计步骤，从伺服控制回路（3）的运行数据估计多个监视参数，控制回路（2）; 评估步骤，从所述监视参数评估多个指标; 用于评估至少一个签名矩阵的评估步骤，每个签名矩阵代表至少一些所述指示符的值; 以及检测和定位步骤，用于根据所述至少一个签名矩阵来检测和定位影响伺服控制环路的劣化。

2. 发明申请

US20120101706A1 METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET 有权
标题翻译：用于监测用于驱动涡轮机的可变几何部件的致动器系统的伺服控制环的方法和装置
公开(公告)号：US20120101706A1
公开(公告)日：2012-04-26
申请号：US13278518
申请日：2011-10-21
申请人： Jean-Rémi André Masse , Christian Aurousseau , Régis Michel Paul Deldalle , Xavier Flandrois , Aziz Sif
发明人： Jean-Rémi André Masse , Christian Aurousseau , Régis Michel Paul Deldalle , Xavier Flandrois , Aziz Sif
IPC分类号： G05B23/00 , G06F19/00
CPC分类号： F02C9/00 , G05B23/02 , G05B23/0221
摘要： A method for monitoring a servo-control loop (3) of an actuator system (2) for actuating variable-geometry components of a turbojet, said method comprising: an estimation step of estimating a plurality of monitoring parameters from operating data of the servo-control loop (2); an evaluation step of evaluating a plurality of indicators from the monitoring parameters; an evaluation step for evaluating at least one signature matrix, each signature matrix being representative of the values of at least some of the indicators; and a detection and location step of detecting and locating a degradation affecting the servo-control loop as a function of said at least one signature matrix.
摘要翻译：一种用于监视用于驱动涡轮喷气发动机的可变几何部件的致动器系统（2）的伺服控制回路（3）的方法，所述方法包括：估计步骤，从伺服控制回路（3）的运行数据估计多个监视参数，控制回路（2）; 评估步骤，从所述监视参数评估多个指标; 用于评估至少一个签名矩阵的评估步骤，每个签名矩阵代表至少一些所述指示符的值; 以及检测和定位步骤，用于根据所述至少一个签名矩阵来检测和定位影响伺服控制环路的劣化。

3. 发明申请

US20130338898A1 METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET 有权
标题翻译：用于监测用于驱动涡轮机的可变几何部件的致动器系统的伺服控制环的方法和装置
公开(公告)号：US20130338898A1
公开(公告)日：2013-12-19
申请号：US13880815
申请日：2011-10-21
申请人： Christian Aurousseau , Régis Michel Paul Deldalle , Xavier Flandrois , Jean-Rémi André Masse , Aziz Sif , Benjamin Pierre Lamoureux
发明人： Christian Aurousseau , Régis Michel Paul Deldalle , Xavier Flandrois , Jean-Rémi André Masse , Aziz Sif , Benjamin Pierre Lamoureux
IPC分类号： F02C9/00
CPC分类号： F02C9/00 , G05B23/02 , G05B23/0221
摘要： A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature.
摘要翻译：一种监控伺服控制回路的方法，包括：从伺服控制回路的运行数据估计监控参数; 从监测参数中获取指标; 从至少一些指标的值确定至少一个签名; 以及根据所述至少一个确定的签名来检测和定位影响所述伺服控制回路的劣化。

4. 发明授权

US09273613B2 Method and a device for monitoring a servo-control loop of an actuator system for actuating variable-geometry components of a turbojet 有权
标题翻译：用于监测用于驱动涡轮喷气发动机的可变几何部件的致动器系统的伺服控制回路的方法和装置
公开(公告)号：US09273613B2
公开(公告)日：2016-03-01
申请号：US13880815
申请日：2011-10-21
申请人： Christian Aurousseau , Régis Michel Paul Deldalle , Xavier Flandrois , Jean-Rémi André Masse , Aziz Sif , Benjamin Pierre Lamoureux
发明人： Christian Aurousseau , Régis Michel Paul Deldalle , Xavier Flandrois , Jean-Rémi André Masse , Aziz Sif , Benjamin Pierre Lamoureux
IPC分类号： G05B23/02 , F02C9/00
CPC分类号： F02C9/00 , G05B23/02 , G05B23/0221
摘要： A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature.
摘要翻译：一种监控伺服控制回路的方法，包括：从伺服控制回路的运行数据估计监控参数; 从监测参数中获取指标; 从至少一些指标的值确定至少一个签名; 以及根据所述至少一个确定的签名来检测和定位影响所述伺服控制回路的劣化。

5. 发明授权

US08857150B2 Monitoring of a high-pressure pump in a turbine engine fuel supply circuit 有权
标题翻译：监测涡轮发动机燃油供应回路中的高压泵
公开(公告)号：US08857150B2
公开(公告)日：2014-10-14
申请号：US12742953
申请日：2008-11-18
申请人： Christian Aurousseau , Jonathan Benitah , Xavier Flandrois , Jean-Remi Masse , Mickael Sauzedde , Franck Godel , Julien Maille
发明人： Christian Aurousseau , Jonathan Benitah , Xavier Flandrois , Jean-Remi Masse , Mickael Sauzedde , Franck Godel , Julien Maille
IPC分类号： F02C7/22 , G01M15/14 , F02C9/26 , F02C9/44 , F02C7/236 , F02C9/28
CPC分类号： F02C7/236 , F02C9/263 , F02C9/28 , F02C9/44 , F05D2260/80 , F05D2270/092 , F05D2270/304
摘要： A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold.
摘要翻译：一种用于通过检测安装在燃料流量调节阀的出口侧的加压和截止阀的开度来监测涡轮机燃料供应回路中的高压泵的装置和方法，通过测量与该燃料流量调节阀对应的涡轮机的旋转速度打开加压和截止阀，并且通过监测转速值的变化，以在测量值转速达到预定阈值时提出更换高压泵。

6. 发明申请

US20100257867A1 MONITORING OF A HIGH-PRESSURE PUMP IN A TURBINE ENGINE FUEL SUPPLY CIRCUIT 有权
标题翻译：涡轮发动机燃油供应电路中的高压泵的监测
公开(公告)号：US20100257867A1
公开(公告)日：2010-10-14
申请号：US12742953
申请日：2008-11-18
申请人： Christian Aurousseau , Jonathan Benitah , Xavier Flandrois , Jean-Remi Masse , Mickael Sauzedde , Franck Godel , Julien Maille
发明人： Christian Aurousseau , Jonathan Benitah , Xavier Flandrois , Jean-Remi Masse , Mickael Sauzedde , Franck Godel , Julien Maille
IPC分类号： F02C7/00 , G01M15/14
CPC分类号： F02C7/236 , F02C9/263 , F02C9/28 , F02C9/44 , F05D2260/80 , F05D2270/092 , F05D2270/304
摘要： A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold.
摘要翻译：一种用于通过检测安装在燃料流量调节阀的出口侧的加压和截止阀的开度来监测涡轮机燃料供应回路中的高压泵的装置和方法，通过测量与该燃料流量调节阀对应的涡轮机的旋转速度打开加压和截止阀，并且通过监测转速值的变化，以在测量值转速达到预定阈值时提出更换高压泵。

7. 发明申请

US20110296846A1 AERONAUTICAL ENGINE WITH COOLING OF AN ELECTRIC STARTING DEVICE 有权
标题翻译：具有电动起动装置冷却的航空发动机
公开(公告)号：US20110296846A1
公开(公告)日：2011-12-08
申请号：US13201553
申请日：2010-01-15
申请人： Christian Aurousseau
发明人： Christian Aurousseau
IPC分类号： F02C7/268
CPC分类号： F02C7/275 , F02C7/14 , F02C7/236 , Y02T50/671 , Y02T50/675
摘要： An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump.
摘要翻译：一种航空发动机，包括燃料泵送装置，其包括高压燃料泵，该高压燃料泵包括连接到低压燃料管道的入口和连接到用于供给高压燃料的主回路的出口，启动发动机的电气装置以及冷却电动起动装置连接到泵送装置，以确保燃料循环冷却。冷却装置由泵提供燃料，该泵包括连接到泵送装置的入口，位于高压泵的上游，并且由独立于高压泵的电动机驱动。

8. 发明授权

US4476675A Acceleration limiter for turbojet engine 失效
标题翻译：涡轮喷气发动机加速限制器
公开(公告)号：US4476675A
公开(公告)日：1984-10-16
申请号：US355662
申请日：1982-03-08
申请人： Christian Aurousseau , Pierre P. L. Odeyer
发明人： Christian Aurousseau , Pierre P. L. Odeyer
IPC分类号： F02C9/26 , F02C9/28
CPC分类号： F02C9/26
摘要： An acceleration limiter is disclosed which includes a hydraulic accumulator (10) with a piston (10a), a spring, (10d) and a chamber 10b) for receiving the pressure Pi residing in the fuel supply circuit (3) from a point P1 in the supply circuit (3) located upstream from the injectors (2). Another chamber (10c) of the accumulator (10) is connected by a tube (11) to the outlet of the compressor (1a). This limiter makes it possible to absorb peaks in fuel flow resulting from sharp maneuvers on the throttle level with the same effectiveness despite variations in Pi, in particular with the altitude of the airplane.
摘要翻译：公开了一种加速限制器，其包括具有活塞（10a），弹簧（10d）和腔室10b的液压蓄能器（10），用于从点P1处接收驻留在燃料供应回路（3）中的压力Pi 所述供应电路（3）位于所述喷射器（2）的上游。蓄能器（10）的另一个室（10c）通过管（11）连接到压缩机（1a）的出口。该限制器可以吸收峰值，尽管Pi的变化，特别是与飞机的高度有差异

9. 发明授权

US09394832B2 Aeronautical engine with cooling of an electric starting device 有权
标题翻译：具有电动起动装置冷却的航空发动机
公开(公告)号：US09394832B2
公开(公告)日：2016-07-19
申请号：US13201553
申请日：2010-01-15
申请人： Christian Aurousseau
发明人： Christian Aurousseau
IPC分类号： F02C7/275 , F02C7/236 , F02C7/14
CPC分类号： F02C7/275 , F02C7/14 , F02C7/236 , Y02T50/671 , Y02T50/675
摘要： An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump.
摘要翻译：一种航空发动机，包括燃料泵送装置，其包括高压燃料泵，该高压燃料泵包括连接到低压燃料管道的入口和连接到用于供给高压燃料的主回路的出口，启动发动机的电气装置以及冷却电动起动装置连接到泵送装置，以确保燃料循环冷却。冷却装置由泵提供燃料，该泵包括连接到泵送装置的入口，位于高压泵的上游，并且由独立于高压泵的电动机驱动。

10. 发明授权

US08762025B2 Method and system for controlling a gas turbine and a gas turbine including such a system 有权
标题翻译：包括这种系统的燃气轮机和燃气轮机的控制方法和系统
公开(公告)号：US08762025B2
公开(公告)日：2014-06-24
申请号：US13201788
申请日：2010-01-15
申请人： Christian Aurousseau
发明人： Christian Aurousseau
IPC分类号： F02C9/54 , F01D17/16 , F02C9/26
CPC分类号： F02C9/52 , F02C9/54 , F05D2270/101 , Y02T50/671
摘要： A method for controlling a gas turbine including a compressor assembly including at least one variable geometry portion, a combustion chamber, and a turbine assembly. The method generates a flow rate setpoint value for fuel to be fed to the combustion chamber as a function of a desired speed of the gas turbine, computes threshold values for maintaining the fuel flow setpoint value in a given range, the threshold values depending on a thermodynamic state of the gas turbine, and controls the position of the variable geometry portion by controlling an actuator as a function of the difference between position information representative of the instantaneous position and setpoint position information. The threshold values are automatically adjusted by computation in real time as a function of the instantaneous position information of the variable geometry portion or of the difference between this position information and the setpoint position information.
摘要翻译：一种用于控制燃气轮机的方法，包括包括至少一个可变几何部分，燃烧室和涡轮组件的压缩机组件。该方法根据燃气轮机的期望速度产生要供给到燃烧室的燃料的流量设定值，计算用于将燃料流量设定值维持在给定范围内的阈值，阈值取决于并且通过根据表示瞬时位置和设定点位置信息的位置信息之间的差异来控制致动器来控制可变几何形状部分的位置。根据可变几何部分的瞬时位置信息或该位置信息与设定点位置信息之间的差异，实时计算自动调整阈值。

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