• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a system for igniting a turbomachine, said system comprising a spark plug having a so-called excitation terminal and a so-called return terminal, an excitation device of the spark plug connected to the excitation terminal of the spark plug, the return terminal being, a use, connected to a structure of the equipotential reference turbomachine, the exciter device being, in use, connected to a control line and to a power supply source providing a signal of excitation to the spark plug on receipt of an excitation signal on the control line, the ignition system comprising a control device comprising a current sensor, a voltage sensor, a first comparator receiving as input a signal generated by the voltage sensor, a second comparator receiving as input a signal generated by the current sensor, and a microcontroller receiving the output of the two comparators, the first comparator being configured to compare the value of the amplitude of the signal generated by the voltage sensor with a first reference value and the second comparator being configured to compare the value of the signal generated by the current sensor with a second reference value , the microcontroller implementing an AND logic gate whose output is a signal indicative of a malfunction of the ignition system if the value of the amplitude of the signal generated by the current sensor is less than the second reference value then the value of the amplitude of the signal generated by the voltage sensor is greater than the first reference value.
    公开号:FR3072762A1
    申请号:FR1759950
    申请日:2017-10-23
    公开日:2019-04-26
    发明作者:Richard Ambroise；Xavier COLLAS
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    LIGHTING SYSTEM OF AN AIRCRAFT TURBOMACHINE
    The present invention relates to an ignition system of an aircraft turbomachine.
    An ignition system of a turbomachine comprises a spark plug arranged in a combustion chamber of the turbomachine and a spark exciter device which in particular comprises an electronic energy storage device and a control circuit in order to release the accumulated energy towards the candle.
    A spark plug exciter device is connected to the turbomachine control unit (FADEC type: Full Authority Digital Engine Control or control and regulation computer for the turbomachine) which ensures the operation of the turbomachine, and in particular the management of the excitement of the candle. In principle, the turbomachine control unit is configured to provide an activation signal to the control circuit of the exciter device, thereby releasing the accumulated energy to the spark plug.
    Ground maintenance teams control the operation of the ignition system of an aircraft turbomachine by conducting, during regularly scheduled inspections, electrical tests of the components of said system. Such operations are long to implement because they require manipulations in order to have access to the various components of the ignition system.
    One of the objectives of the present invention is to facilitate the detection of failure of the ignition system.
    The invention aims to meet this need and relates to an ignition system of a turbomachine, said system comprising a spark plug having a so-called excitation terminal and a so-called return terminal, an exciter device for the connected spark plug to the spark plug excitation terminal, the return terminal being, in use, connected to a structure of the turbomachine forming equipotential reference, the exciter device being, in use, connected to a control line and to a source of power supply providing an excitation signal to the spark plug on receipt of an excitation signal on the control line, the ignition system comprising a control device comprising a current sensor, a voltage sensor, a first comparator receiving as input a signal generated by the voltage sensor, a second comparator receiving as input a signal generated by the current sensor, and a microc ontroller receiving the output of the two comparators, the first comparator being configured to compare the value of the amplitude of the signal generated by the voltage sensor with a first reference value and the second comparator being configured to compare the value of the signal generated by the current sensor at a second reference value, the microcontroller implementing an AND logic gate, the output of which is a signal indicating a malfunction of the ignition system if the value of the amplitude of the signal generated by the current sensor is less than the second reference value while the value of the amplitude of the signal generated by the voltage sensor is greater than the first reference value.
    The integration of such a control device into an ignition system makes it possible to obtain a state of health of the latter more easily.
    The invention also relates to a method for detecting a malfunction of the ignition system of a turbomachine implemented by a control device, said ignition system comprising a spark plug having a so-called excitation terminal and a so-called return terminal, a spark plug excitation device connected to the spark plug excitation terminal, the return terminal being, in use, connected to a structure of the turbomachine forming equipotential reference, the exciter device being, in use , connected to a control line and to a power source supplying an excitation signal to the spark plug on receipt of an excitation signal on the control line, the control device comprising a current sensor, a voltage sensor, a first comparator connected to the voltage sensor, a second comparator connected to the current sensor, and a microcontroller receiving the at the output of the two comparators, the method comprising the following steps of:
    measurement of a voltage by the voltage sensor, said sensor generating an image signal of said voltage;
    measurement of a current by the current sensor, said sensor generating an image signal of said current;
    comparison, by the first comparator, of the amplitude of the signal generated by the voltage sensor with a first reference value;
    comparison, by the second comparator, of the amplitude of the signal generated by the current sensor with a second reference value;
    monitoring, by the microcontroller, of the state of the output signal of the first comparator and of the state of the output signal of the second comparator;
    generation, by the microcontroller, of a signal indicating a malfunction of the ignition system if the value of the amplitude of the signal generated by the current sensor is less than the second reference value while the value of the amplitude of the signal generated by the voltage sensor is greater than the first reference value.
    The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
    FIG. 1 represents an aircraft comprising a turbomachine with which is associated an ignition system according to an embodiment of the invention;
    FIG. 2 represents an electrical diagram of the ignition system according to an embodiment of the invention, the ignition system comprising a device for controlling the operation of said system;
    Figure 3 is a diagram showing the steps implemented by the control device to control the operation of an ignition system according to the invention;
    Figure 4 is an intensity-difference curve of potentials showing the nominal electrical profile of a spark plug of the ignition system shown in Figure 2; and Figure 5 is a view similar to Figure 2 showing an electrical diagram of the ignition system according to another embodiment of the invention.
    In connection with FIGS. 1 and 2, an aircraft A comprises a turbomachine 1 and a turbomachine control unit 2 (of the FADEC type) for controlling and monitoring the operation of the turbomachine 1 and which can be arranged in the turbomachine or in alternative, in the aircraft. The turbomachine 1 is associated with at least one ignition system 10 (generally two) connected to the control unit 2 ensuring the ignition of the air-fuel mixture present in the combustion chamber 20 of the turbomachine.
    Each ignition system 10 comprises, an exciter device 11 connected to a source of electrical power 5 of the aircraft and to a structure of the turbomachine 6 (for example a metal chassis) forming an equipotential reference, and a spark plug ignition 12 arranged in the combustion chamber 20 of the turbomachine.
    The spark plug 12 comprises a so-called excitation terminal 12a and a so-called return terminal 12b. The excitation terminal 12a is connected to the exciter device 11 via an electrical connection 13, and the return terminal 12b is connected to the structure of the turbomachine 6 via an electrical connection 14.
    In an exemplary embodiment in which the exciter device 11 is with capacitive technology, the power supply source 5 of the aircraft is a voltage source (alternating or direct) and the exciter device 11 comprises:
    • a circuit 5a (made via transistors) to transform the voltage source 5 into an alternating current source (circuit 5a is shown diagrammatically by a current source in the figures) • a switching device 1 lb (for example of the switch type with characteristic in i / V or of solid state switch type) • an accumulator capacitor 11a one terminal of which is connected to the circuit 5a and to the excitation terminal 12a of the spark plug 12 and another terminal is connected to the structure of the turbomachine 6 via the switching device 1 lb.
    The switching device 1 lb is connected to the control unit 2 by means of a control line 2a, via which, by sending an activation signal S_Cmd, the control unit 2 can trigger the switching device 1 lb (trigger = opening of the switching device) so that the accumulator capacitor 1 la discharges in the spark plug 12 and that the latter produces sparks in response to the discharge of the capacitor 1 la.
    In known manner, the exciter device 11 of an ignition system 10 of a turbomachine is dimensioned to generate, in nominal operation, voltages of the order of 4000 to 6000 Volts for maximum intensities of the order of 1200 amps.
    According to the invention, the ignition system 10 further comprises a device 20 for controlling the ignition system 10, the function of which is to check, when an excitation voltage is supplied by the exciter device 11, the proper functioning of the ignition system 10.
    In relation to FIG. 2 in which the control device 20 is of the analog-digital type, said device comprises a voltage sensor 21, a current sensor 22, an analog comparator C1 (for example an operational amplifier) receiving a signal V_Img (V) of the voltage sensor 21, an analog comparator C2 (for example an operational amplifier) receiving a signal V_Img (i) of the current sensor 22, a microcontroller 24 and analog-digital converters 25,26 where each converter is connected at the output of a comparators C1, C2, between the latter and the microcontroller 24. The sensors 21, 22 are dimensioned to provide an admissible output voltage for the analog-digital converters 25, 26 (typically of the order of 0 to 5.5V, see 3.3V) and comparators Cl, C2.
    The voltage / current sensors 21, 22 that the control device comprises are of technologies adapted to withstand voltages and current supplied by the exciter device 11, as well as to withstand large variations in temperature (large variation in temperature during a flight due to variations in altitude). By way of example, as shown in FIG. 2, the current sensor 22 is a shunt 22a arranged arranged between the spark plug 12 and the structure of the turbomachine 6, while the voltage sensor 21 is for example a transformer voltage 21a of inductive type arranged between the exciter device 11 and the spark plug 12. Other type of sensors could be suitable, for example a resistive divider for the voltage sensor or a Hall effect sensor for the current sensor.
    The current sensor as the voltage sensor generates a voltage whose amplitude is, respectively, the image of the value of the current V_img (i) in the downlink 14 and the image of the voltage V_img (V) in the uplink 13.
    The first comparator C1 receives, as inputs, the signal V_img (V) generated by the voltage sensor 21 and a signal supplied by a DC voltage generator Glet whose amplitude forms a first reference value Refl. The first comparator C1 is configured to emit a signal of non-zero voltage if the amplitude of the signal V_img (V) is greater than the first reference value Refl, or of zero voltage otherwise. The analog to digital converter 25 receives the output signal from the first comparator C1 and converts it into a digital signal.
    The second comparator C2 receives, as inputs, the signal V_img (i) generated by the current sensor 22 and a signal supplied by a DC voltage generator G2 and whose amplitude forms a second reference value Ref2. The second comparator C2 is configured to send a non-zero voltage signal if the amplitude of the signal V_img (i) is less than the second reference value Ref2, or of zero voltage otherwise. The analog-to-digital converter 26 receives the output signal from the second comparator C2 and converts it into a digital signal.
    The microcontroller 24 receives the output signals from the two comparators, converted into digital signals by the analog-digital converters 25, 26 in this case where the comparators are analog. The microcontroller 24 is of the central unit type comprising a processor and memories in which instructions / logic are recorded (for example logic gate programming) which must be implemented by the processor during the operation of the microcontroller 24.
    The microcontroller 24 implements, for example, an AND logic gate 34 receiving as inputs the output signals of the comparators C1, C2, converted into digital signals by the analog-digital converters 25, 26. The AND logic gate generates a boolean signal S_Alert which forms the output signal of the microcontroller. The signal S_Alert is an indicator signal:
    indicator of good operation (signal S_Alert set to 0) of the ignition system 10 if the value of the amplitude of the signal V_img (i) generated by the current sensor 22 is greater than the second reference value Ref2 when the value of the amplitude of the signal V_img (V) generated by the voltage sensor 21 is greater than the first reference value Ref2;
    indicator of a malfunction (signal S_Alert set to 1) of the ignition system 10 if the value of the amplitude of the signal V_img (i) generated by the current sensor 22 is less than the second reference value Ref2 when the value the amplitude of the signal V_img (V) generated by the voltage sensor 21 is greater than the first reference value Refl.
    The signal S_Alert emitted by the microcontroller 24 is for example sent to the control unit 2 for processing and display of a status of the ignition system 10 on a dedicated display (not shown) to alert the maintenance teams on the ground.
    With reference to FIG. 3, the method for detecting a malfunction of the ignition system 10 implemented by the control device 20 therefore comprises the following steps:
    - El: measurement of a voltage by the voltage sensor 21, said sensor generating a signal V_img (V) image of said voltage;
    - E2: measurement of a current by the current sensor 22, said sensor generating a signal V_img (i) image of said current;
    - E3: comparison, by the first comparator C1, of the amplitude of the signal V_img (V) with the first reference value Refl;
    - E4: comparison, by the second comparator C2, of the amplitude of the signal V_img (i) with the second reference value Ref2;
    - E5: monitoring, by the microcontroller 24, of the state of the output signal of the first comparator C1 and of the state of the output signal of the second comparator C2;
    - E6: generation / emission of a signal S_Alert indicating a malfunction of the ignition system 10 if the value of the amplitude of the signal V_img (i) generated by the current sensor 22 is less than the second reference value Ref2 while the value of the amplitude of the image signal V_img (V) generated by the voltage sensor 21 is greater than the first reference value Refl.
    By taking the numerical values given above, the control device 20 is, for example, configured to alert of a malfunction of the ignition system 10 if the intensity consumed by the spark plug is less than 50 A for a voltage of excitation provided by the exciter device greater than 700 V. Thus, the first reference value Refl of the comparator is chosen so as to be representative of a voltage of approximately 700 Volts and the second reference value Ref2 is chosen so as to be representative of an intensity of about 50 Amps.
    Preferably (not shown in the figures), the measurement assembly also includes a conditioner circuit and a low-pass filter arranged between each sensor and the comparator associated with said sensor in order to put the signal generated by the sensor into a usable form.
    With reference to FIG. 4, the principle of detection of a malfunction of the ignition system 10 implemented by the control device 20 consists in determining an operating point (intensity-potential) of the spark plug 12 and in comparing it. to the nominal electrical profile of the latter (see curve 40). The control device 20 is configured to emit the signal S_Alert alert indicator of a malfunction of the ignition system in the event that the spark plug operating point is too far from the nominal electrical profile 40.
    The control device 20 thus checks the consumption by the spark plug 12 of the energy released by the exciter device 11 and issues an alert indicative of a malfunction of the ignition system 10 if the analysis of electrical signals taken from the spark plug 12 demonstrates that the level of energy consumed by spark plug 12 is below a certain threshold.
    An operating point of the spark plug which is too far away (zone 1 in FIG. 4) from the nominal electrical profile (zone 2 and curve 40) can reveal a degradation of the spark plug 12, but also of the exciter device 11, of the electrical connections. 13,14, as well as the environment of the ignition system 10 (problem in the combustion chamber for example).
    The integration of such a control device 20 into an ignition system 20 allows ground maintenance teams to control the operation of the latter more easily.
    It will be noted that the voltage 21 or current 22 sensor can each be either arranged between the exciter device 11 and the spark plug 12 or between the spark plug 12 and the structure of the aircraft 6.
    In a second embodiment, and in relation to FIG. 5, the first comparator C1 and the second comparator C2 are produced via adequate programming of the microcontroller 24. The reference values Refl and Ref2 are also programmed in the microcontroller 24. The current sensor 22 and voltage sensor 21 are directly connected to the microcontroller and the sensors are dimensioned to provide an admissible output voltage for the microcontroller 24 (of the order of 4 to 6 Volts, see 3.3 Volts for certain microcontrollers) .
    The microcontroller 24 implements, for example, an AND logic gate 34 receiving as input the output signals from the comparators C1, C2. The AND logic gate generates a boolean signal S_Alert which forms the output signal of the microcontroller. The signal S_Alert is a signal:
    indicator of a malfunction (signal S_Alert set to 1) of the ignition system 10 if the value of the amplitude of the signal V_img (i) generated by the current sensor 22 is less than the second reference value Ref2 when the value the amplitude of the signal V_img (V) generated by the voltage sensor 21 is greater than the first reference value Refl.
    Preferably (not shown in the figures), a conditioner circuit and a low pass filter are arranged between each sensor 21, 22 and the microcontroller 24 in order to put the image signal generated by the sensor 21, 22 in a form that can be used by the microcontroller 24.
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1) Ignition system (10) of a turbomachine (1), said system comprising a spark plug (12) having a so-called excitation terminal (12a) and a so-called return terminal (12b), a device spark plug exciter (11) connected to the excitation terminal (12a) of the spark plug (12), the return terminal (12b) being, in use, connected to a structure of the turbomachine (6) forming equipotential reference, the exciter device (11) being, in use, connected to a control line (2a) and to an electrical power source (5) providing an excitation signal to the spark plug upon receipt of an excitation signal (S_Cmd) on the control line (2a), characterized in that the ignition system (10) comprises a control device (20) comprising a current sensor (22), a voltage sensor (21), a first comparator (Cl) receiving as input a signal (S_Img (V)) generated by the voltage sensor, a second comparator receiving as input a signal (S_Img (i)) generated by the current sensor, and a microcontroller (24) receiving the output of the two comparators (Cl, C2), the first comparator (Cl) being configured to compare the value of l amplitude of the signal (S_Img (V)) generated by the voltage sensor (21) to a first reference value (Refl) and the second comparator (C2) being configured to compare the value of the signal (S_Img (i)) by the current sensor (22) at a second reference value (Ref2), the microcontroller (24) implementing an AND logic gate whose output is a signal (S_Alert) indicating a malfunction of the ignition system ( 10) if the value of the amplitude of the signal (S_Img (i)) generated by the current sensor (22) is less than the second reference value (Ref2) while the value of the amplitude of the signal (S_Img ( V)) generated by the voltage sensor (21) is greater than the first reference value ence (Refl).
    [2" id="c-fr-0002]
    2) Ignition system (10) according to claim 1, characterized in that the current sensor (22) comprises a shunt (22a).
    [3" id="c-fr-0003]
    3) Ignition system (10) according to any one of claims 1 to 2, characterized in that the voltage sensor (21) comprises a voltage transformer (21a).
    [4" id="c-fr-0004]
    4) Ignition system (10) according to any one of claims 1 to 3, characterized in that the first and the second comparators (Cl, C2) are analog, the microcontroller (24) is connected to the output of each the first comparator (Cl) and the second comparator (C2) via an analog-to-digital converter (25,26).
    [5" id="c-fr-0005]
    5) Ignition system (10) according to any one of claims 1 to 3, characterized in that the first and the second comparator (Cl, C2) are digital and produced by programming the microcontroller (24).
    [6" id="c-fr-0006]
    6) Method for detecting a malfunction of the ignition system (10) of a turbomachine (1) implemented by a control device (20), said ignition system comprising a spark plug (12) having a so-called excitation terminal (12a) and a so-called return terminal (12b), a spark plug exciting device (11) connected to the excitation terminal (12a) of the spark plug (12), the return terminal (12b) being, in use, connected to a structure of the turbomachine (6) forming equipotential reference, the exciter device (11) being, in use, connected to a control line (2a) and to a power supply source (5) supplying an excitation signal to the spark plug on receipt of an excitation signal (S_Cmd) on the control line (2a), the control device (20) comprising a current sensor (22), a voltage sensor (21), a first comparator (Cl) connected to the voltage sensor, a second comp arator (C2) connected to the current sensor, and a microcontroller (24) receiving the output of the two comparators (C1, C2), characterized in that the method comprises the following steps of:
    measurement of a voltage (El) by the voltage sensor (21), said sensor generating a signal (V_img (V)) image of said voltage;
    measurement of a current (E2) by the current sensor (22), said sensor generating a signal (V_img (i)) image of said current;
    comparison (E3), by the first comparator (Cl), of the amplitude of the signal (V_img (V)) generated by the voltage sensor (21) with a first reference value (Refl);
    comparison (E4), by the second comparator (C2), of the amplitude of the signal (V_img (i)) generated by the current sensor (22) with a second reference value (Ref2);
    monitoring (E5), by the microcontroller (24), of the state of the output signal of the first comparator (Cl) and of the state of the output signal of the second comparator (C2);
    generation (E6), by the microcontroller, of a signal (S_Alert) indicator of a malfunction of the ignition system (10) if the value of the amplitude of the signal (S_Img (i)) generated by the current sensor (22) is less than the second reference value (Ref2) while the signal amplitude value (S_Img (V)) generated by the voltage sensor (21) is greater than the first reference value (Refl ).
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    同族专利:
    公开号 | 公开日
    EP3473836B1|2020-07-08|
    CN109695508B|2021-04-23|
    US20190120199A1|2019-04-25|
    CN109695508A|2019-04-30|
    FR3072762B1|2019-11-08|
    US10697420B2|2020-06-30|
    EP3473836A1|2019-04-24|
    引用文献:
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    法律状态:
    2018-10-22| PLFP| Fee payment|Year of fee payment: 2 |
    2019-04-26| PLSC| Search report ready|Effective date: 20190426 |
    2019-10-28| PLFP| Fee payment|Year of fee payment: 3 |
    2021-07-09| ST| Notification of lapse|Effective date: 20210605 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1759950|2017-10-23|
    FR1759950A|FR3072762B1|2017-10-23|2017-10-23|AIRCRAFT TURBOMACHINE IGNITION SYSTEM|FR1759950A| FR3072762B1|2017-10-23|2017-10-23|AIRCRAFT TURBOMACHINE IGNITION SYSTEM|
    EP18197111.0A| EP3473836B1|2017-10-23|2018-09-27|Ignition system of an aircraft turbine engine|
    CN201811194096.4A| CN109695508B|2017-10-23|2018-10-12|Ignition system for an aircraft turbine engine and method for detecting a fault in such an ignition system|
    US16/161,941| US10697420B2|2017-10-23|2018-10-16|Ignition system of an aircraft turbine engine|
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