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公开(公告)号：US09897517B2
公开(公告)日：2018-02-20
申请号：US14432878
申请日：2013-09-27
Applicant: SNECMA
Inventor： Cedrik Djelassi
CPC classification number: G01M15/14 , F01D21/003 , F02C9/28 , F05D2260/80 , F05D2260/81 , F05D2260/821 , F05D2270/335 , F05D2270/44 , G01L5/133 , G05B17/02
Abstract: A method for monitoring a thrust fault of a turbofan during a modification of the thrust setting of the turbofan, the method including a step of processing the thrust setting via a filtering function and a transient-phase model such as to obtain a modelled thrust, a step of comparing the modelled thrust to the actual thrust such as to determine a thrust difference, a step of comparing the thrust difference to an alarm threshold; and a step of emitting an alarm in the event of exceeding the alarm threshold, wherein at a given iteration, in which the prior modelled thrust is known, the transient-phase model provides a time constant in accordance with the prior modelled thrust, and the filtering function provides a modelled thrust in accordance with the time constant obtained, the prior modelled thrust and the thrust setting.
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公开(公告)号：US20150219528A1
公开(公告)日：2015-08-06
申请号：US14432878
申请日：2013-09-27
Applicant: SNECMA
Inventor： Cedrik Djelassi
CPC classification number: G01M15/14 , F01D21/003 , F02C9/28 , F05D2260/80 , F05D2260/81 , F05D2260/821 , F05D2270/335 , F05D2270/44 , G01L5/133 , G05B17/02
Abstract: A method for monitoring a thrust fault of a turbofan during a modification of the thrust setting of the turbofan, the method including a step of processing the thrust setting via a filtering function and a transient-phase model such as to obtain a modelled thrust, a step of comparing the modelled thrust to the actual thrust such as to determine a thrust difference, a step of comparing the thrust difference to an alarm threshold; and a step of emitting an alarm in the event of exceeding the alarm threshold, wherein at a given iteration, in which the prior modelled thrust is known, the transient-phase model provides a time constant in accordance with the prior modelled thrust, and the filtering function provides a modelled thrust in accordance with the time constant obtained, the prior modelled thrust and the thrust setting.
Abstract translation: 一种用于在涡轮风扇的推力设定的修改期间监测涡轮风扇的推力故障的方法，所述方法包括通过过滤功能处理推力设定的步骤和瞬态相位模型，以获得建模推力， 将建模推力与实际推力进行比较以确定推力差的步骤，将推力差与报警阈值进行比较的步骤; 以及在超过警报阈值的情况下发出警报的步骤，其中在已知的已知建模推力的给定迭代中，瞬态相位模型根据先前的推荐推力提供时间常数，并且 过滤功能根据所获得的时间常数，先验模型推力和推力设定提供模型推力。
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公开(公告)号：US20140257667A1
公开(公告)日：2014-09-11
申请号：US14200130
申请日：2014-03-07
Applicant: SNECMA
Inventor： Florent NOBELEN , Cedrik Djelassi
IPC: B64D31/12
Abstract: A method of synchronizing engines of an airplane in accordance with at least one activation logic (10, 10′) defining a deactivated state (20), a primed state (22), and at least one activated state (16, 18), and comprising: passing (32) synchronization from the deactivated state to the primed state when a pilot of the airplane issues an activation order; passing (36) synchronization from the primed state to the activated state when at least certain safety and/or activation conditions are satisfied; and passing (24, 34) synchronization from the activated or primed state to the deactivated state when the pilot issues a deactivation order or whenever at least some of the safety conditions are not satisfied.
Abstract translation: 根据限定停用状态（20），起动状态（22）和至少一个激活状态（16,18）的至少一个激活逻辑（10,10'）来同步飞机引擎的方法，以及 包括：当飞机的飞行员发出激活命令时，将（32）同步从停用状态传递到起动状态; 当满足至少某些安全和/或激活条件时，将（36）同步从引发状态传递到激活状态; 以及当所述飞行员发出停用命令时或者当至少一些所述安全条件不满足时，将（24,34）同步从所述激活或引发状态传递到所述停用状态。
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公开(公告)号：US10036330B2
公开(公告)日：2018-07-31
申请号：US14910825
申请日：2014-07-30
Applicant: SNECMA
Inventor： Cedrik Djelassi
IPC: F02C9/26 , G05B11/01 , G05B19/404 , G05B19/416 , B64D27/16 , B64D31/06
CPC classification number: F02C9/263 , B64D27/16 , B64D31/06 , F05D2220/323 , F05D2270/021 , G05B11/01 , G05B19/404 , G05B19/416
Abstract: This module (5) serves to filter a raw setpoint (N1_CMD_OP) for a corrector network (6) in a system (20) for regulating an engine. It comprises: a module (54) for detecting a filtering condition for filtering said raw setpoint; and means for supplying said corrector network with a filtered setpoint (N1_CMD_LIM) instead of said raw setpoint when the filtering condition is detected.
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公开(公告)号：US09790807B2
公开(公告)日：2017-10-17
申请号：US14396230
申请日：2013-04-26
Applicant: SNECMA
Inventor： Cecile Valerie Marie Cointe , Michael Dinsart , Cedrik Djelassi , Bruno Robert Gaully
CPC classification number: F01D21/003 , F01D21/14 , F02C9/28 , F02C9/46 , F02C9/48
Abstract: An aircraft turbine engine including at least one spool rotating at speed N1 and a monitoring system including: a regulating module including at least one regulation measurement channel to obtain a measurement of the speed N1 and a mechanism to compare the obtained speed measurement with a thrust setpoint to provide a thrust status; and a module for engaging a protection function of UHT or ATTCS type of the turbine engine. The turbine engine further includes a system for protection against overspeed to prevent ejection of high-energy debris outside the turbine engine, the protection system including at least one overspeed measurement channel to obtain an overspeed of the rotating spool of the turbine engine. The engagement module compares at least one overspeed obtained with at least one reference speed defined according to the protection function to be engaged, to engage the protection function according to results of the comparison.
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Patent Agency Ranking
公开(公告)号：US09415877B2
公开(公告)日：2016-08-16
申请号：US14200130
申请日：2014-03-07
Applicant: SNECMA
Inventor： Florent Nobelen , Cedrik Djelassi
Abstract: A method of synchronizing engines of an airplane in accordance with at least one activation logic (10, 10′) defining a deactivated state (20), a primed state (22), and at least one activated state (16, 18), and comprising: passing (32) synchronization from the deactivated state to the primed state when a pilot of the airplane issues an activation order; passing (36) synchronization from the primed state to the activated state when at least certain safety and/or activation conditions are satisfied; and passing (24, 34) synchronization from the activated or primed state to the deactivated state when the pilot issues a deactivation order or whenever at least some of the safety conditions are not satisfied.
Abstract translation: 根据限定停用状态（20），起始状态（22）和至少一个激活状态（16,18）的至少一个激活逻辑（10,10'）来同步飞机引擎的方法，以及 包括：当飞机的飞行员发出激活命令时，将（32）同步从停用状态传递到起动状态; 当满足至少某些安全和/或激活条件时，将（36）同步从引发状态传递到激活状态; 以及当所述飞行员发出停用命令时或者当至少一些所述安全条件不满足时，将（24,34）同步从所述激活或引发状态传递到所述停用状态。
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公开(公告)号：US09470604B2
公开(公告)日：2016-10-18
申请号：US14299392
申请日：2014-06-09
Applicant: SNECMA
Inventor： Christophe Javelot , Mohamed Boutaleb , Cedrik Djelassi , Victor Henry
CPC classification number: G01M15/042 , F01D21/20 , F02C7/232 , F02C9/46 , F05D2260/83 , Y02T50/671
Abstract: A method of testing an engine fuel supply cutoff valve includes: detecting a fuel supply cutoff command; commanding to close the fuel supply cutoff valve; commanding to hold the fuel metering valve in the open position for a predetermined time; commanding to close the fuel metering valve after the predetermined time; measuring an engine operating parameter during performance of the previous steps; and comparing the measured parameter with a predetermined threshold, so as to determine whether or not the engine operating parameter corresponds to an engine fuel supply cutoff by normal operation of the fuel supply cutoff valve.
Abstract translation: 一种测试发动机燃料供应截止阀的方法包括：检测燃料供应切断命令; 指示关闭燃油供应截止阀; 指示将燃料计量阀保持在打开位置预定时间; 指示在预定时间后关闭燃油计量阀; 在执行前述步骤期间测量发动机操作参数; 以及将测量的参数与预定阈值进行比较，以便通过燃料供应截止阀的正常操作来确定发动机操作参数是否对应于发动机燃料供应切断。
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8.发明申请公开(公告)号：US20150152790A1
公开(公告)日：2015-06-04
申请号：US14409822
申请日：2013-06-20
Applicant: SNECMA
Inventor： Christophe Javelot , Cedrik Djelassi , Bruno Robert Gaully , Ismail Sylla
IPC: F02C9/26
Abstract: A method of adjusting a fuel flow rate in a turbine engine propelling an aircraft, including: obtaining a first estimate of a flow rate of fuel injected into a combustion chamber of the turbine engine propelling an aircraft and as delivered by a fuel metering device of the turbine engine; obtaining a second estimate of the fuel flow rate, which second estimate is more accurate than the first estimate for at least one range of fuel flow rate values and being delivered by an estimator device having a flow meter; and adjusting the fuel flow rate threshold value with help of a difference evaluated between the first estimate and the second estimate, the threshold value being for use in an open loop for regulating the turbine engine.
Abstract translation: 一种调节在推动飞行器的涡轮发动机中的燃料流量的方法，包括：获得喷射到涡轮发动机的燃烧室中的燃料的流速的第一估计，该涡轮发动机推进飞行器并且由燃料计量装置 涡轮发动机; 获得所述燃料流量的第二估计，所述第二估计比所述燃料流量值的至少一个范围的所述第一估计更准确，并且由具有流量计的估计装置递送; 以及借助于在所述第一估计和所述第二估计之间评估的差异来调整所述燃料流量阈值，所述阈值用于调节所述涡轮发动机的开环。
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公开(公告)号：US10465613B2
公开(公告)日：2019-11-05
申请号：US14786477
申请日：2014-04-22
Applicant: SNECMA
Inventor： Cedrik Djelassi
Abstract: During a stage (E0) of starting the turbine engine, the method of the invention comprises: an open-loop generating step (E10) of generating a fuel flow rate command (WF_OL) from at least one pre-established relationship; and a closed-loop monitoring step (E20-E30) of monitoring at least one operating parameter of the turbine engine selected from: a rate of acceleration (dN2/dt) of a compressor of the turbine engine; and a temperature (EGT) at the outlet from a turbine of the turbine engine; this monitoring step comprising maintaining (E30) the operating parameter in a determined range of values by using at least one corrector network (R1, R2, R3) associated with the parameter and suitable for delivering a signal for correcting the open-loop generated fuel flow rate command so as to maintain the operating parameter in the determined range of values.
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公开(公告)号：US20150142353A1
公开(公告)日：2015-05-21
申请号：US14409091
申请日：2013-06-24
Applicant: SNECMA
Inventor： Vincent Cabret , Cedrik Djelassi
CPC classification number: G01R17/00 , G01D5/2291 , G01D18/00 , G01R19/0084
Abstract: A method for monitoring an LVDT sensor including two secondary circuits, the method including: calculating the difference between voltages at terminals of one of the secondary circuits at a given instant and at a previous instant; calculating the difference between voltages at terminals of the other one of the secondary circuits at the given instant and at the previous instant; calculating the sum of the two differences calculated; modifying an indicator according to a distance to zero of the previously calculated sum; and comparing the indicator with at least one predetermined threshold.
Abstract translation: 一种用于监视包括两个二次电路的LVDT传感器的方法，所述方法包括：在给定时刻和之前时刻计算一个次级电路的端子处的电压差; 计算在给定时刻和之前时刻的另一个次级电路的端子处的电压差; 计算两个差异的总和; 根据先前计算的总和的距离修改指示符; 以及将所述指示符与至少一个预定阈值进行比较。
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