公开(公告)号：US20130204468A1

公开(公告)日：2013-08-08

申请号：US13737042

申请日：2013-01-09

申请人： EUROCOPTER

发明人： Emmanuel Camhi

IPC分类号： G06F17/00

CPC分类号： G06F17/00 ,  F02C9/00 ,  F05D2220/329 ,  F05D2260/80 ,  F05D2260/821 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/332 ,  F05D2270/335 ,  F05D2270/803 ,  G05B23/0283 ,  G07C5/0816

摘要： A method of performing a health check of at least one turbine engine (3). During a development step (STP0), the installation losses (1) are quantified for a plurality of test values for a reduced speed of rotation (Ng′) of a gas generator (4) of the engine. During an acquisition step (STP1), the speed of rotation of said gas generator (4) is increased until said engine develops a maximum power, and then the speed of rotation of the gas generator (4) is decreased until the reduced speed of rotation (Ng′) reaches a test value. The aircraft is stabilized and at least one monitoring value is acquired. During an evaluation step (STP2) of evaluating the health check, at least one operating margin is determined by using a monitoring value and the effects of mounting the engine in an airplane.

摘要翻译： 一种执行至少一个涡轮发动机（3）的健康检查的方法。 在开发步骤（STP0）期间，为发动机的气体发生器（4）的降低的转速（Ng'）的多个测试值量化安装损耗（1）。 在采集步骤（STP1）期间，所述气体发生器（4）的旋转速度增加，直到发动机产生最大功率，然后降低气体发生器（4）的旋转速度，直到降低的转速 （Ng'）达到测试值。 飞机稳定，获得至少一个监控值。 在评估健康检查的评估步骤（STP2）期间，通过使用监测值和将发动机安装在飞机中的效果来确定至少一个操作裕度。

公开(公告)号：US20130199204A1

公开(公告)日：2013-08-08

申请号：US13737260

申请日：2013-01-09

申请人： EUROCOPTER

发明人： Emmanuel Camhi ,  Guido Borchers

IPC分类号： F02C7/00

CPC分类号： F02C7/00 ,  F02C9/00 ,  F05D2220/329 ,  F05D2260/80 ,  F05D2260/821 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/332 ,  F05D2270/335 ,  F05D2270/803 ,  G05B23/0221

摘要： A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter is verified by acquiring a measurement signal, by performing first filtering of each signal by a high-pass filter over a long first duration (TPS1) and by verifying that a first amplitude (A1) of the signal filtered in this way does not exceed a first threshold defined by the manufacturer, by performing second filtering of each signal by a high-pass filter over a short second duration (TPS2) in parallel with said first filtering by a high-pass filter, and by verifying that a second amplitude (A2) of the signal filtered in this way does not exceed a second threshold defined by the manufacturer, the second duration (TPS2) being less than the first duration (TPS1), and the second amplitude (A2) being less than the first amplitude (A1).

摘要翻译： 一种自动执行发动机健康检查以检查飞机的至少一个涡轮发动机的健康状况的方法。 在飞行中，通过获取测量信号，通过在长的第一持续时间（TPS1）上通过高通滤波器对每个信号进行第一滤波并且通过验证第一幅度（A1）来验证至少一个监视参数的稳定性， 以这种方式滤波的信号不超过制造商定义的第一阈值，通过在短秒级持续时间（TPS2）上与高通滤波器并行地对每个信号进行第二滤波，与高通 滤波器，并且通过验证以这种方式滤波的信号的第二幅度（A2）不超过制造商定义的第二阈值，第二持续时间（TPS2）小于第一持续时间（TPS1），第二幅度 （A2）小于第一振幅（A1）。

公开(公告)号：US08666568B2

公开(公告)日：2014-03-04

申请号：US13737042

申请日：2013-01-09

申请人： Eurocopter

发明人： Emmanuel Camhi

IPC分类号： G06F7/00 ,  G05D1/00 ,  B64C27/00 ,  B64C25/00 ,  F02C3/04 ,  F02C7/00

CPC分类号： G06F17/00 ,  F02C9/00 ,  F05D2220/329 ,  F05D2260/80 ,  F05D2260/821 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/332 ,  F05D2270/335 ,  F05D2270/803 ,  G05B23/0283 ,  G07C5/0816

摘要： A method of performing a health check of at least one turbine engine (3). During a development step (STP0), the installation losses (1) are quantified for a plurality of test values for a reduced speed of rotation (Ng′) of a gas generator (4) of the engine. During an acquisition step (STP1), the speed of rotation of said gas generator (4) is increased until said engine develops a maximum power, and then the speed of rotation of the gas generator (4) is decreased until the reduced speed of rotation (Ng′) reaches a test value. The aircraft is stabilized and at least one monitoring value is acquired. During an evaluation step (STP2) of evaluating the health check, at least one operating margin is determined by using a monitoring value and the effects of mounting the engine in an airplane.

摘要翻译： 一种执行至少一个涡轮发动机（3）的健康检查的方法。 在开发步骤（STP0）期间，为发动机的气体发生器（4）的降低的转速（Ng'）的多个测试值量化安装损耗（1）。 在采集步骤（STP1）期间，所述气体发生器（4）的旋转速度增加，直到发动机产生最大功率，然后降低气体发生器（4）的旋转速度，直到降低的转速 （Ng'）达到测试值。 飞机稳定，获得至少一个监控值。 在评估健康检查的评估步骤（STP2）期间，通过使用监测值和将发动机安装在飞机中的效果来确定至少一个操作裕度。

公开(公告)号：US20130203021A1

公开(公告)日：2013-08-08

申请号：US13741751

申请日：2013-01-15

申请人： EUROCOPTER

发明人： Southdary Beaud ,  Emmanuel Camhi

IPC分类号： G09B5/00

CPC分类号： G09B5/00 ,  G09B9/18 ,  G09B9/46

摘要： A method of failure simulation for an aircraft (7) having a power plant (10) with at least two turbine engines (11, 12), together the two engines develop an overall power, each engine (11, 12) being capable of delivering at least one contingency power in order to compensate for a total failure of other engines (11, 12). The device serves during a failure simulation to modify the overall power delivered by the power plant, with this modification being performed with the help of first adjustment means (20). Second adjustment means (30) serve to modify also the difference between the minimum power obtained during the simulated failure and the stabilized overall power, and also the time between said failure stabilizing on said overall power.

摘要翻译： 一种具有具有至少两个涡轮发动机（11,12）的动力装置（10）的飞行器（7）的故障模拟方法，两个发动机一起开发整体动力，每个发动机（11,12）能够输送 至少一个应急能力以补偿其他发动机（11,12）的完全故障。 该设备在故障模拟期间服务以修改发电厂提供的整体功率，借助于第一调整装置（20）来执行该修改。 第二调整装置（30）还用于修改在模拟故障期间获得的最小功率与稳定的总功率之间的差异，以及所述故障稳定在所述总功率之间的时间。