CN114893300A - Small turbofan engine reference pressure parameter fault judgment method and redundancy control method - Google Patents
Small turbofan engine reference pressure parameter fault judgment method and redundancy control method Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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Abstract
The invention provides a fault judgment method and a redundancy control method for a reference pressure parameter of a small turbofan engine, which are used for making a reasonable fault judgment strategy for the important control parameter of the small turbofan engine used by an unmanned aerial vehicle, namely the total pressure behind an air compressor, so as to judge fault information in real time and accurately; the engine performance parameters obtained through engine mathematical modeling are used for calculating the total pressure of the air compressor by utilizing parameters such as engine inlet parameters, rotating speed and total temperature after the fan under the condition that the total pressure of the air compressor of the engine is not credible, so that the redundancy is carried out by replacing the original sensor acquisition parameters, the normal flight of the unmanned aerial vehicle is ensured, and the working reliability is improved.
Description
Technical Field
The invention relates to the technical field of small turbofan engines, in particular to a fault judgment method and a redundancy control method for a reference pressure parameter of a small turbofan engine.
Background
The total pressure behind the compressor of the turbofan engine is an important control parameter of the engine, and the actual working parameter of the engine is obtained by a total pressure measuring device arranged behind the compressor and is converted into the control parameter through A/D (analog quantity/digital quantity). The method is used as a calculation basis for oil supply regulation in a relatively common oil-gas ratio control law of the engine. If the signal fails, this means that the fuel supply cannot be adjusted accurately, with serious consequences. Therefore, under the condition that the rear total pressure of the compressor of the engine has a problem, timely and accurate judgment is needed, and the rear total pressure of the compressor of the engine is replaced through parameter analysis.
The parameter analysis method is used for analyzing the pressure, the temperature and the like in an engine airflow channel through other working parameters of the engine, such as the engine rotating speed, the air state at the inlet of the engine and the like, and comprises the total pressure behind the air compressor.
Aircraft engines typically have redundancy for important engine control signals, with hardware redundancy being more used. However, due to the limitations of size, weight, cost, etc., small turbofan engines are often not suitable for hardware redundancy.
Disclosure of Invention
In view of the above, the invention provides a fault information judgment method and a redundancy control method for a reference pressure parameter of a small turbofan engine, which can judge fault information accurately in real time and realize redundancy control.
A method for judging fault of reference pressure parameters of a small turbofan engine comprises the following steps:
and (3) judging whether the total pressure U3TD signal of the air flow after the compressor of the engine is normal or not according to the following criteria between the preparation of starting the engine and the successful starting:
when the total pressure voltage U3TD of the back airflow of the engine compressor continuously exceeds the set upper limit or the set lower limit for 3 times, the total pressure U3TD of the back airflow of the engine compressor is considered to be abnormal;
after the engine is started successfully and the engine is stopped, judging whether the total pressure U3TD signal of the air flow behind the compressor of the engine is normal according to the following criteria:
when the acceleration control is controlled for 3 continuous periods, judging that the sensor is in fault, namely the total pressure U3TD signal of the back airflow of the compressor of the engine is abnormal;
when the deceleration control is controlled for 3 continuous periods, the sensor is considered to be in fault, namely the total pressure U3TD signal of the air flow behind the compressor of the engine is abnormal.
Preferably, the calculation formula of the total pressure voltage quantity of the back airflow of the compressor of the engine, namely the total pressure voltage quantity U3TD, of the upper limit U3TD _ max and the lower limit U3TD _ min is as follows:
U3TD_max＝(0.85-0.03×H/1000)V；
U3TD_min＝(0.45-0.03×H/1000)V；
where H is the starting height.
A method for controlling redundancy of reference pressure parameters of a small turbofan engine comprises the following steps:
and (3) judging whether the total pressure U3TD signal of the air flow after the compressor of the engine is normal or not according to the following criteria between the preparation of starting the engine and the successful start of the engine:
when the total pressure voltage U3TD of the back airflow of the engine compressor continuously exceeds the set upper limit or the set lower limit for 3 times, the total pressure U3TD of the back airflow of the engine compressor is considered to be abnormal;
after the engine is started successfully and the engine is stopped, judging whether the total pressure U3TD signal of the air flow behind the compressor of the engine is normal according to the following criteria:
when the acceleration control is controlled for 3 continuous periods, judging that the sensor is in fault, namely the total pressure U3TD signal of the back airflow of the compressor of the engine is abnormal;
when the deceleration control is controlled for 3 continuous periods to obtain the control right, the sensor is considered to be in fault, namely the total pressure U3TD signal of the back airflow of the compressor of the engine is abnormal;
using an engine model performance simulation mathematical model, calculating engine performance data by using input air pressure height H, Mach number Ma, engine accelerator control voltage Uy, engine high-pressure rotor rotating speed nh and engine fan-pressing rear total temperature voltage U6TD, and storing the engine performance data into a performance data table;
after the total pressure U3TD signal of the air flow of the engine compressor is judged to be abnormal, if the current situation is before the engine is started successfully, redundant control is not carried out, and the task flow is terminated;
and if the current situation is that the engine is successfully started, stopping using the current collected total pressure U3TD of the air flow of the air compressor of the engine, and interpolating from the performance data table to obtain the value of the total pressure U3TD of the air flow of the air compressor of the engine according to the current received air pressure height H, Mach number Ma, engine accelerator control voltage Uy and the rotating speed nh of a high-pressure rotor of the engine to participate in control calculation.
Preferably, the calculation formula of the total pressure voltage quantity of the back airflow of the compressor of the engine, namely the total pressure voltage quantity U3TD, of the upper limit U3TD _ max and the lower limit U3TD _ min is as follows:
U3TD_max＝(0.85-0.03×H/1000)V；
U3TD_min＝(0.45-0.03×H/1000)V；
where H is the starting height.
Preferably, after the engine performance data is calculated, the engine test data is used to correct the engine performance data and stored in the performance data table.
Preferably, the Mach number Ma ranges from 0 to 0.9 when engine performance data are calculated.
Preferably, the value range of the air pressure height H is 0-13 km when the engine performance data are calculated.
Preferably, when the engine performance data is calculated, the value range of the engine throttle control voltage Uy is 1V-16V.
The invention has the following beneficial effects:
the invention provides a fault judgment method and a redundancy control method for a parameter of a small turbofan engine parameter, which are used by an unmanned aerial vehicle, and are used for making a reasonable fault judgment strategy for the important control parameter of the small turbofan engine, namely the total pressure behind a gas compressor, so as to judge fault information in real time and accurately;
the engine performance parameters obtained through engine mathematical modeling are used for calculating the total pressure of the air compressor by utilizing parameters such as engine inlet parameters, rotating speed and total temperature after the fan under the condition that the total pressure of the air compressor of the engine is not credible, so that the redundancy is carried out by replacing the original sensor acquisition parameters, the normal flight of the unmanned aerial vehicle is ensured, and the working reliability is improved.
Drawings
FIG. 1 is a flow chart of Pt3 fault determination and redundancy control according to the present invention;
FIG. 2 is a diagram illustrating the verification effect of the method of the present invention.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The parameter symbols used in the present invention are defined as follows:
P t3 representing the total pressure of the air flow after the compressor of the engine, and the unit is kilopascal (kPa); u3TD represents the total pressure voltage quantity of the air flow after the compressor of the engine, and the unit is volt (V); tt13 represents the total temperature after the engine fan in kelvin (K); u6TD represents the total temperature voltage after the engine presses the fan, and the unit is volt (V); uy represents engine throttle control voltage, corresponding to thrust, in volts (V); nh represents the rotating speed of a high-pressure rotor of the engine, and the unit is revolutions per minute (r/min); h represents barometric altitude in kilometers (km); ma represents Mach number, and the ratio of the flight speed to the local sound speed is a dimensionless parameter.
The method mainly comprises the following steps:
1) timing of action of the inventive method
After the engine is powered on and before the engine is stopped, the control period is started to participate in the control according to the oil-gas ratio control law.
2) Method for judging total pressure signal fault behind engine compressor
On the basis of control characteristic analysis and fault data analysis of an oil-gas ratio control rule, fault reporting criteria of a rear total pressure Pt3 sensor of the gas compressor are formulated according to different working stages.
The engine work flow is engine ready start → start success → engine stop.
The Pt3 sensor fault criterion is based on the following criteria between preparation for starting and successful starting:
anomaly criterion 1: and judging that the U3TD (Pt3) continuously exceeds the upper limit or the lower limit for 3 times, namely is greater than or equal to U3TD _ max or is less than or equal to the lower limit U3TD _ min, and considering that the U3TD (Pt3) signal is abnormal. Wherein U3TD _ max and U3TD _ min are functions of the air pressure height H at the starting moment, and are calculated according to the following formula:
U3TD_max＝(0.85-0.03*H/1000)V；
U3TD_min＝(0.45-0.03*H/1000)V。
wherein H is the starting height (air pressure height), and H is more than or equal to 0 and less than or equal to 5000 m.
After the engine is stopped after the start is successful, the judgment criterion of the Pt3 sensor is as follows:
anomaly criterion 2: when the acceleration control is controlled for 3 consecutive cycles (i.e. a warning line due to too high a fuel-air ratio is triggered, meaning Pt3 is abnormally high), the sensor is considered to be faulty.
Anomaly criterion 3: when the deceleration control is controlled for 3 continuous cycles to obtain the control right (namely, a warning line caused by the low fuel-air ratio is triggered, which means that Pt3 is abnormally low), the U3TD signal is judged to be abnormal.
3) Redundancy method after engine speed signal fault
The redundancy scheme adopted is: an engine performance data table is obtained by calculation using an engine model performance simulation program (the program includes mathematical models of the main components of the engine), and is corrected using engine test data. The performance data sheet includes the inlet condition parameters H, Ma, Uy, nh, U6 TD. Based on the consideration of factors such as precision influence, common range, memory data table size and the like, the value range of the Mach number is determined to be 0-0.9, the height value is 0-13 km, the Uy range is 1V-16V, the engine performance data is calculated in the range, and the engine performance data is arranged in the memory of the digital engine controller in a data table mode.
After judging that the Pt3 signal is invalid, adopting different redundancy measures according to the working stage of the engine:
before the engine is started successfully, if the Pt3 sensor reports, the rotating speed and the air pressure are measured. Temperature and the like are changed violently, and the engine is easily damaged due to over-temperature, over-rotation and the like in the starting process of the engine caused by improper oil-gas ratio caused by untimely response, so that the process is not redundant, and emergency treatment is adopted to terminate a task flow.
After the engine is started successfully, the current U3TD collected by the AD is stopped, and U3TD is obtained by interpolation from the engine performance data sheet according to the currently received H, Ma and the actual throttle control voltage Uy calculated through nh and U6TD, and participates in control calculation.
The test verification effect is shown in fig. 2, it can be seen from the figure that when the fault code jump is 4, the consistency is good after the substitution for simulating the fault of U3TD, the calculated deviation can ensure the normal work of the engine, and for the unmanned aerial vehicle, the thrust control error is within the allowable range. As can be seen, the verification effect meets the requirements.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A method for judging fault of reference pressure parameters of a small turbofan engine is characterized by comprising the following steps:
and (3) judging whether the total pressure U3TD signal of the air flow after the compressor of the engine is normal or not according to the following criteria between the preparation of starting the engine and the successful start of the engine:
when the total pressure voltage U3TD of the back airflow of the engine compressor continuously exceeds the set upper limit or the set lower limit for 3 times, the total pressure U3TD of the back airflow of the engine compressor is considered to be abnormal;
after the engine is started successfully and the engine is stopped, judging whether the total pressure U3TD signal of the air flow behind the compressor of the engine is normal according to the following criteria:
when the acceleration control is controlled for 3 continuous periods, judging that the sensor is in fault, namely the total pressure U3TD signal of the back airflow of the compressor of the engine is abnormal;
when the deceleration control is controlled for 3 continuous periods, the sensor is considered to be in fault, namely the total pressure U3TD signal of the air flow behind the compressor of the engine is abnormal.
2. The method for determining the reference pressure parameter of the small turbofan engine according to claim 1, wherein the calculation formula of the total pressure voltage of the air flow after the compressor of the engine U3TD with the set upper limit U3TD _ max and the set lower limit U3TD _ min is as follows:
U3TD_max＝(0.85-0.03×H/1000)V；
U3TD_min＝(0.45-0.03×H/1000)V；
where H is the starting height.
3. A method for controlling redundancy of reference pressure parameters of a small turbofan engine is characterized by comprising the following steps:
and (3) judging whether the total pressure U3TD signal of the air flow after the compressor of the engine is normal or not according to the following criteria between the preparation of starting the engine and the successful start of the engine:
when the total pressure voltage U3TD of the back airflow of the engine compressor continuously exceeds the set upper limit or the set lower limit for 3 times, the total pressure U3TD of the back airflow of the engine compressor is considered to be abnormal;
after the engine is started successfully and the engine is stopped, judging whether the total pressure U3TD signal of the air flow behind the compressor of the engine is normal according to the following criteria:
when the acceleration control is controlled for 3 continuous periods, judging that the sensor is in fault, namely the total pressure U3TD signal of the back airflow of the compressor of the engine is abnormal;
when the deceleration control is controlled for 3 continuous periods to obtain the control right, the sensor is considered to be in fault, namely the total pressure U3TD signal of the back airflow of the compressor of the engine is abnormal;
using an engine model performance simulation mathematical model, calculating engine performance data by using input air pressure height H, Mach number Ma, engine accelerator control voltage Uy, engine high-pressure rotor rotating speed nh and engine fan-pressing rear total temperature voltage U6TD, and storing the engine performance data into a performance data table;
after the judgment that the total pressure U3TD signal of the air flow behind the air compressor of the engine is abnormal, if the current situation is before the engine is started successfully, the redundancy control is not carried out, and the task flow is terminated;
and if the current situation is that the engine is started successfully, stopping using the current collected total pressure U3TD of the air flow behind the air compressor of the engine, and performing interpolation from the performance data table to obtain the value of the total pressure U3TD of the air flow behind the air compressor of the engine according to the current received air pressure height H, Mach number Ma, engine accelerator control voltage Uy and the rotating speed nh of a high-pressure rotor of the engine to participate in control calculation.
4. The method for redundantly controlling the reference pressure parameter of the small turbofan engine according to claim 3, wherein the set upper limit U3TD _ max and the set lower limit U3TD _ min of the total pressure voltage quantity U3TD of the air flow after the compressor of the engine are calculated according to the following formula:
U3TD_max＝(0.85-0.03×H/1000)V；
U3TD_min＝(0.45-0.03×H/1000)V；
where H is the starting height.
5. A method of redundantly controlling a variable pressure parameter of a small turbofan engine according to claim 3 wherein after calculating the engine performance data, the engine performance data is corrected using engine test data and stored in the performance data table.
6. The method for redundantly controlling the parametric pressure parameter of the small turbofan engine according to claim 3, wherein a Mach number Ma ranges from 0 to 0.9 when engine performance data are calculated.
7. The method for redundantly controlling the parametric control pressure parameter of the small turbofan engine according to claim 6, wherein when the engine performance data is calculated, the air pressure height H ranges from 0 km to 13 km.
8. The method for redundantly controlling the parameter of the reference pressure of the small turbofan engine according to claim 6 or 7, wherein when the engine performance data is calculated, the engine throttle control voltage Uy ranges from 1V to 16V.
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