Method of controlling aircraft engine capacitive ignition system

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises measuring time interval between reservoir capacitor discharge current sequential pulses that follows to ignition plug. Time interval exceeding preset magnitude allows deciding on ignition system integrity. Note here that measured is the time interval between discharge current pulses caused solely by commutation of power accumulated at reservoir capacitor that exceeds check magnitude.

EFFECT: higher validity of control, condition-based operation.

2 dwg

 

The invention relates to techniques for igniting combustible mixtures by means of an electric spark, in particular to a capacitive ignition units, and can be used to control the ignition system installed on the engine, including in the course of its run, as well as in the breaks between runs of aircraft engines.

There is a method of controlling a capacitive ignition system of jet engines, which consists in determining the presence of a plasma torch generated by the candle on the normalized distance from the working end of the candle inserted in the ignition device when working as part of the ignition system, thus moisten spark plug gap normalized quantity of liquid fuel, measure the ionization current of the plasma plume generated by the candle, compare the parameters of the ionization current from the reference and comparison results make a conclusion about the suitability of the ignition system [1].

The disadvantages of this method of control should include the impossibility of its application to control capacitive ignition systems installed on the engine.

There is also known a method of fault detection capacitor ignition system of a gas turbine engine [2], in which the failure is detected by the purge gas through the internal cavity of the candles and the connecting cable, the measurement of takarada storage capacitor and the pressure inside these cavities. In the end, a malfunction of the ignition system is judged by the appearance of a pulse of high pressure over the duration of the discharge current of the capacitor. Pulse pressure increase is characterized by the presence of a fault in the ignition system. This control method allows to detect a failure in the ignition system, such as during engine start and during health checks ignition system between runs of the engine. However, the lack of control failure in the ignition system described in the method of control not possible to check whether the output parameters of the ignition system requirements ensure ignition of the fuel mixture in the combustion chamber of the engine in a predetermined range of altitudes and flight speeds of the aircraft, pressure and ambient temperature.

For various types of aircraft engines ability capacitive ignition system to ensure ignition of the fuel mixture in the combustion chamber in predetermined start conditions, for example, gas turbine engine (ground altitude, start with the autorotation mode, anti-surge run) is characterized by the minimal energy stored at the storage capacitor of the ignition unit, which is switched to the spark plug, and a repetition rate of the spark discharge at the spark plug, generated when switching the stock is Noah at the storage capacitor energy to the spark plug, specified for each type of engine on the launch conditions. These parameters must meet a certain minimum value stored energy Qminand the minimum frequency of sparking at the spark fmin[3-5].

Thus, to monitor the health of the capacitive ignition systems you want to monitor the fact that the output parameters of the ignition system is stored on storage capacitor energy Q and the actual repetition rate of the spark discharge at the spark f - exceed the minimum allowable respectively Qminand fmin.

Partly these deficiencies in counterparts, deprived of the control method of the capacitive ignition system described in [6], which consists in the fact that when the capacitive ignition system measures the time between successively following pulses of discharge current caused by the periodic switching stored at the storage capacitor energy to the spark ignition, over this time the given time value is judged on the performance of the ignition system. The measurement of this time interval between successively the following bit current storage capacitor of the ignition unit, determining the repetition rate of the spark discharge in the spark gap of the spark plug, comparing it with the specified mA the maximum allowable time interval allows us to estimate the violation of the actual repetition rate of the spark discharge at the spark (frequency sparking) values are the minimum allowable frequencies sparking fmin. Closest to the claimed invention is the method described in [6], adopted for the prototype.

The disadvantage of this method of control ignition system, taken as a prototype, is that the decision about the health of the ignition system will only accept the fact of exceeding the actual repetition rate of the spark discharge at the spark above the minimum allowable, i.e. f over fmin. However, when reducing the breakdown voltage of the switching spark gap, with which the switching stored at the storage capacitor energy to the spark plug (typical diagram of the capacitive discharge circuit of the ignition system shown in figure 1) constant power Converter that converts the voltage of the unit plugs into the voltage used to charge a storage capacitor, the frequency of sparking at the spark plugs increases as the frequency of sparking at the spark plug, the power Converter, the breakdown voltage of the switching spark gap are connected in the following proportions:

where Cn- capacity storage capacitor ignition system;

UCR- the breakdown voltage of the switching spark gap;

P2- power Converter;

- Zap the hay at the storage capacitor energy Q, switched to the spark plug;

f is the repetition rate of the spark discharge at the spark.

In this case a reduction of the voltage UCRmay lead to a reduction in stored energy Q less Qminthat in turn leads to devoplment fuel mixture (failure of ignition of the combustion chamber) and, as consequence, to run the engine. The reduction of the breakdown voltage of the switching spark gap may be caused by different reasons: hidden manufacturing defects, detected only during operation, the influence of external conditions (e.g. radiation), malfunction of the control circuit when using managed arresters or solid-state high-voltage switches [7, 8]. When reducing the breakdown voltage of the switching spark gap repetition rate of the spark discharge at the spark increases, which will be identified as the operating state of the ignition system, while the actual value of the accumulated energy will not provide ignition of the fuel. Therefore, when the system checks the ignition between the start and during launch can be obtained false information for the output parameters of the ignition system specified, when this later when assessing the causes of newsplease fuel mixture will not be on ocena reliable information about the causes of the failure of starting the engine.

In addition, decrease stored at the storage capacitor energy Q less Qminor frequency f less than fmincan lead not only to run the engine, but also for its launch with a large delay in the ignition of the fuel mixture in the combustion chamber. This results in high flow fuel to the so-called "gun" runs [9] with a throw of pressure in the combustion chamber, which is due to the impact can damage engine components and elements of automatic control systems.

Thus, the use of technical solutions, implements the method according to the prototype, it is not possible to identify the condition of the ignition system, in which the urgent need to stop the running of the engine in order to prevent damage to the control equipment and the engine in the operating conditions and the process of its development and bench testing.

The problem solved by the claimed invention is to increase the reliability of monitoring the health capacitive ignition system engine aircraft.

The problem is solved by a method of controlling a capacitive ignition system of the aircraft engines, which consists in the fact that they measure the time interval between successively following pulses of discharge current storage capacitor on which the Assembly, caused only by switching stored at the storage capacitor energy that exceeds the reference value of energy, the measured time interval between these pulses of discharge current storage capacitor is compared with a preset time interval characterizing the minimum repetition rate of the spark discharge in the spark gap of the spark, the difference is judged on the performance of the ignition system.

New according to the invention is the fact that they measure the time interval between pulses of discharge current storage capacitor caused only by switching stored on the energy above the reference energy value, which is selected by the terms of the reliability run.

Measuring the time interval between pulses of discharge current storage capacitor caused only by switching stored at the storage capacitor energy larger than the specified reference value, allows to estimate the state (health) capacitive ignition system not only by the repetition rate of the spark discharges equal to

where tu- the time interval between successively the following pulses of the discharge current of the storage capacitor, but energy stocks the military at the storage capacitor Q.

The inventive method allows to measure only the repetition rate of the spark discharge at the spark plugs with the accumulated energy exceeds a preset reference value. Thus, when it is realized the possibility of control exceeding the required energy in units of ignition given value of Qminto exceed the frequency f of the distance of the spark discharge at the spark caused by switching on a candle stored energy Q more Qminf valuesmin. In that case, if the reference value of energy Qcounterand the minimum value of the frequency fmintake, respectively, the minimum value of the accumulated energy on the storage capacitor Assembly ignition Qminand the value of the repetition rate of the spark discharge at the spark plug, providing the necessary range of ignition of the combustion chamber and the specified starting characteristics of the engine pressure and temperature at ground running, altitude and speed of flight at high altitude launch, the application of the proposed control method can improve the accuracy of control status (health) of the ignition system. Check the status of the ignition system can be carried out during engine start-up, and between them runs. The application of the proposed method of control allows Soeur the time to detect parametric faults unit ignition leading to the release of stored energy in the storage capacitor, the repetition rate of the spark discharge at the spark plugs within the permissible limits, to exclude the so-called "gun" the engine starts and the associated disruption of equipment control systems, the integrity of the engines, to get more objective information in the study of the causes of failure of engine start-up, to reduce the costs of their development in the process of execution of works on the development of running aircraft engines on the design and development stage.

Figure 1 shows the typical circuit discharge circuit capacitive ignition system.

Figure 2 presents the device illustrating one embodiment of the proposed method of monitoring the health of the capacitive ignition systems of aircraft engines, in which the measurement of the accumulated energy on the storage capacitor is carried out by measuring the amplitude values of the discharge current of the storage capacitor.

The measured value of the information parameter is the amplitude of the discharge current, characterizing stored on the capacitor energy is compared with the value of the reference voltage corresponding to the reference energy value of Qcounter(Qmin).

A device that implements the proposed method of control, shown nafig, contains sensor 1 discharge current (for example, a current transformer)comparing device (comparator) 2, - unit control (reference) voltage amplitude of the discharge current 3, the measuring time interval (time between successive following pulses of discharge current) 4, the actuating element (e.g., relay) 5. In addition, figure 2 shows the voltage Converter 6, which converts the voltage into a high voltage used for charging storage capacitor 7, a rectifier 8, which is used for rectifying the output voltage of the Converter 6, switch, unmanaged discharger 9, the resistor galvanic coupling 10, the spark plug 11.

A device that implements the proposed method of control the capacitive ignition system works as follows. The supply voltage through a transformer 6 and the rectifier 8 charges the storage capacitor 7, which upon reaching its voltage equal to the breakdown voltage of the switching device 9, is discharged at the spark plug 11. The breakdown of a spark gap 9 switching actually stored on the storage capacitor energy equal to

on the spark plug.

At the discharge stored at the storage capacitor energy to light a candle in her spark between the generating system is fast spark discharge. The process of charge-discharge storage capacitor is periodically repeated with a frequency of

where P2- power Converter,

Q is stored at the storage capacitor energy.

When the cumulative discharge of the capacitor 7 on the spark plug 11 in the discharge circuit, the current flows in the form of a damped amplitude [10], the amplitude value is equal to:

where Im- peak value of the discharge current;

UCR- the breakdown voltage of the switching spark gap;

Lp- inductance circuit discharge circuit;

Rpactive resistance circuit discharge circuit.

From the formula it follows that the amplitude of the discharge current of the ignition system when the actual parameters of the discharge circuit unit ignition is determined by the capacity of the storage capacitor 7n, breakdown voltage switched spark gap 9 UCR. The capacity of the storage capacitor for each ignition unit has a certain value that may change within a certain range. The variation of the breakdown voltage unmanaged switching surge arresters can reach values of the voltage range of 2.4 to 3.4 kV [11].

For about the especiany reliable ignition of the fuel mixture in the combustion chamber of the engine is required, to

where Qcounterequal to Qminfmincorrespondingly control (minimal) value of energy stored on the storage capacitor, switched on the spark plug, the minimum repetition rate of the spark discharge at the spark sufficient for reliable ignition of the fuel mixture in the combustion chamber under all conditions of engine start.

Thus, there is a specific value of the minimum amplitude of the discharge current corresponding to Qcounter(Qmin). Control of excess of the actual amplitude of the discharge current during each switching stored at the storage capacitor energy above this minimum value of the amplitude of the discharge current allows to determine compliance ignition system requirements Q more Qcounter(more Qmin).

During the flow of discharge current in the secondary winding of the sensor 1 Indochinese voltage, in form similar to the form of the discharge current, and proportional to it. Therefore, from the sensor 1 to the input of comparator 2 (comparator) receives a voltage proportional to discharge current of the ignition unit, the peak value (amplitude of the first half-wave) related to the value stored at the storage capacitor energy. To the second input device is TBA compare 2 receives the reference voltage, corresponding to the value stored energy accumulating capacitor

where ΔQ provides the accepted margin of stored energy, providing a reliable ignition of the fuel mixture and ignition of the combustion chamber in the most severe starting conditions of the engine.

When exceeding the voltage value read from sensor 1, on the value of the DC voltage applied to the comparator 2 control knob value of the amplitude of the discharge current is 3, i.e. when the condition Q more Qcounter(more Qmin), at the output of the comparator 2, an impulse voltage. Sequentially following each other discharges storage capacitor caused by the switching stored at the storage capacitor energy Q more Qcounter(more Qmin)create at the output of the comparator 2, the sequence of voltage pulses. Measuring the time interval provides a comparison of the time between successively the following voltage pulses with a specified maximum time between these pulseswhich is inversely proportional to the repetition frequency of the discharge current when the sequential switching of the accumulated energy on the storage capacitor to the ignition plug 11.

Implementation the Oia such measuring time interval is not difficult and can be performed by various devices, for example, described in [12]. When the repetition rate of the spark discharge at the spark (consistently following pulses of discharge current storage capacitor with energy Q more Qcounter(more Qmin)) over the set of values of fmin(the time interval between pulses lessthe output meter time 4 you may receive the output voltage, providing the actuation element 5, such as a relay. The appearance of current in the circuits of the relay identifies the operation of the ignition system in normal mode, ensure reliable starting of the engine (Q more Qcounter(more Qmin)), f over fmin). In that case, if, for any reason, the breakdown voltage of the switching spark gap will decrease, which will lead to the failure conditions Q more Qcounter(more Qmin)), the maximum value of the voltage output of the sensor 1 becomes less than the voltage supplied to the comparator 2 control knob value of the amplitude of the discharge current 3. In this case, the output of comparator 2 in the time of flow of the discharge current in the device does not occur, the output voltage pulse and, accordingly, relay 5 will not output the signal indicating the normal operation mode (status) ignition system (Q more Qcounter(more Qmin), f over fmin). Similarly, the control device operates and decreasing the capacity of the storage capacitor, for any reason, the conditions to values, where Q is less than Qcounter(less than Qmin)). Decreasing the repetition rate of the spark discharge at the spark (the pulse repetition frequency of the discharge current of the storage capacitor caused by switching on a candle stored on the energy Q more Qcounter(more Qmin) at the output of the measuring time interval 4 does not receive a voltage, which eliminates the actuating element 5. In the absence of the output signal from element 5 can identify the failure of the ignition system (failure to Q more Qcounter(more Qmin)), f over fmin). The output signal of the control element 5 may be used in ACS when starting the aircraft engines in their control systems and diagnostics, telemetry.

Presents a description of the operation of the device that implements the proposed method of control system ignition aircraft engines, illustrates its advantages over the known analogues and prototype:

- greater informative value and reliability of control;

- the possibility of parametric control of compliance with output system parameters C is jihane: stored energy, the repetition rate of the spark discharge at the spark plugs, the requirements of engine starting.

The application of the proposed control method also eliminates the starting of the engine with a greater delay in ignition of the fuel in the combustion chamber (gun start), thereby to avoid damage to the control equipment of the engine and the engine at the location of the surge pressure, shock loads on the engine design of the aircraft.

It is obvious that other circuit designs that implement the proposed method of control the capacitive ignition system, for example, using direct measurement of the voltage at the storage capacitor to estimate excess nanoplasmas energy over a given value of Qcounter(Qmin) or by controlling the voltage winding of a feedback when using electronic converters flyback voltage for charge storage capacitor, by analogy with the use of this voltage winding to stabilize and control the value of the breakdown voltage controlled gaps [13].

The proposed control method can be successfully applied for the translation of ignition systems for on-condition maintenance, as it allows to identify the point in time at which to begin the processes of the change of basic parameters, determining the reliability of the launch of the combustion chamber of the engine, to avoid premature removal of aggregates and spark plugs on the development of a certain time in runs (inclusions hours operating time) with doing this on the actual condition of the ignition system. The inventive method allows to reduce logistics costs engine aircraft in operation of the ignition systems that meet the requirements of the market of accessories aircraft products.

Sources of information

1. RF patent for the invention №2338080, 10.11.2008,

2. Copyright certificate №1083716, the priority date of 02.02.1983,

3. Vassev, Waitwindow. Unsteady modes of operation of aircraft gas turbine engines, Meters: machinery, 1975, 216 S. (see s).

4. Mailbin, Bmoc, Waitwindow // Start of aircraft gas turbine engines // M: mechanical engineering, 1968 (see p.62).

5. Angleter. Measurement of minimum ignition energy in the jet carolinasaturday mixture. Combustion and Flame, No. 1, August 1976.

6. The ignition unit SC-44-3B. The technical installation manual G re.

7. Avenu, Anturasi. Capacitive ignition system of a new generation for modern and advanced GTD. Aerospace engineering and technology: collection of scientific papers. Issue 19. Heat engines and power plants. - arkov; state aerospace University "Kharkiv aviation Institute", 2000

8. Avenu, Ichneumon, Vingetting, Anturasi, Oaaov, Faithfully. Capacitive ignition system for modern and advanced GTD. Abstracts of international scientific conference "Engines of the XXI century", part II, CIAM, Moscow, 2000

9. Howcase, Restration. The reliability of aircraft engines. - M.: mechanical engineering, 1982

10. Vaalavuo. The ignition units. M: mechanical engineering, 1968 (see s).

11. The discharger R TO-ODOT-85.

12. Utica, Klenk. Semiconductor circuitry. The reference manual. TRANS. with it. - M.: Mir, 1982, 512 S. (see p.34, RIS).

13. RF patent for the invention №2106518, 10.03.1998,

The method of controlling a capacitive ignition system of the aircraft engines, which consists in the fact that they measure the time interval between successively following pulses of discharge current storage capacitor on a candle, over this time interval specified value judgments about the health of the ignition system, wherein the measured time interval between pulses of the discharge current is caused only by switching stored at the storage capacitor of the energy above the reference value.



 

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SUBSTANCE: invention relates to ICE spark failure identifier, vehicle with such identifier and method to identify ICE spark failure. ICE spark failure identifier comprises: turn position determination assembly, assembly to calculate rpm at singular turn angle or assembly to calculate angular speed at singular turn angles and assembly to identify spark failures. Assembly to identify spark failures reveals if ICE cylinders are subjected to spark failure conditions by procedures intended for identification of ICE spark failures. Procedures intended for identification of ICE spark failures comprise first and second procedures. First procedures are used in case ICE drive point (rpm Ne and torque Te) does not belong in rear section resonance region (s120). Second procedures are used in case ICE drive point (rpm Ne and torque Te) belong in rear section resonance region (s130). First procedures proceed from rpm irregularity at singular turn angle or angular speed irregularity at singular turn angles. Second procedures proceed from rpm irregularity at singular turn angle or angular speed irregularity at singular turn angles after filtration. Filtration is performed by HF filters. Vehicle comprises multi-cylinder ICE, rear part and spark failure identifier. Rear part is mounted on semi-axle side via damper. Spark failures are revealed by first or second procedure for rpm at singular turn angles.

EFFECT: higher accuracy and validity of determination.

35 cl, 20 dwg

FIELD: physics.

SUBSTANCE: method of determining test discharge parametres of capacitive ignition systems which consist of an ignition assembly, ignition cable and a spark plug, involves picking up a discharge current and voltage signal and determination of values of discharge parametres. The discharge current and voltage signal is picked up using analogue sensors. The current and voltage signals are picked up in auxiliary "short circuit" and "test load" modes, as well as in the main operation mode of the ignition system. Measurements are taken in digital form with given sampling frequency. Values of characteristic primary parametres are distinguished from measurement results. Values of intermediate parametres are determined for each assigned measurement mode using the obtained values of characteristic primary parametres. Values of test discharge parametres are determined using the obtained values of intermediate parametres.

EFFECT: possibility of measuring primary discharge parametres in digital form, picked up by analogue current and voltage sensors, more accurate measurement, obtaining information on efficiency of the spark plug and ignition system, discharge mode and energy factors and their change during operation or during an experiment.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: fuel mixture spark ignition method in the spark plug consists in ignition of fuel mixture with spark with the chosen required values of current force, length and duration of spark discharge. The required values of current force, length and duration of spark discharge are preliminarily chosen from conditions of required decrease of content of hazardous substances included in exhaust gases, decrease of fuel consumption and increase of ICE power.

EFFECT: providing complete fuel combustion in internal combustion engine, reducing the content of hazardous substances in exhaust gases, fuel consumption and increasing the engine power.

3 dwg

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