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    Method and a device for monitoring a servo-control loop of an actuator system for actuating variable-geometry components of a turbojet
    3.
    发明授权
    Method and a device for monitoring a servo-control loop of an actuator system for actuating variable-geometry components of a turbojet 有权
    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。

    METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET
    5.
    发明申请
    METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET 有权
    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。

    AERONAUTICAL ENGINE WITH COOLING OF AN ELECTRIC STARTING DEVICE
    7.
    发明申请
    AERONAUTICAL ENGINE WITH COOLING OF AN ELECTRIC STARTING DEVICE 有权
    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。

    Acceleration limiter for turbojet engine
    8.
    发明授权
    Acceleration limiter for turbojet engine 失效
    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

    Aeronautical engine with cooling of an electric starting device
    9.
    发明授权
    Aeronautical engine with cooling of an electric starting device 有权
    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。

    Method and system for controlling a gas turbine and a gas turbine including such a system
    10.
    发明授权
    Method and system for controlling a gas turbine and a gas turbine including such a system 有权
    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。