CN114893300B - Parameter control pressure parameter judging method and redundancy control method for small turbofan engine - Google Patents
Parameter control pressure parameter judging method and redundancy control method for small turbofan engine Download PDFInfo
- Publication number
- CN114893300B CN114893300B CN202210393843.7A CN202210393843A CN114893300B CN 114893300 B CN114893300 B CN 114893300B CN 202210393843 A CN202210393843 A CN 202210393843A CN 114893300 B CN114893300 B CN 114893300B
- Authority
- CN
- China
- Prior art keywords
- engine
- u3td
- compressor
- control
- pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The invention provides a parameter control pressure parameter judging method and a redundancy control method for a small turbofan engine, which are used for judging important control parameters of the small turbofan engine used by an unmanned aerial vehicle, namely a reasonable judging strategy for total compression after a compressor, so as to accurately judge fault information in real time; and under the condition that the total pressure of an engine compressor is unreliable, the total pressure of the compressor is calculated by using parameters such as an engine inlet parameter, a rotating speed, a total temperature after a fan and the like to replace the acquisition parameters of the original sensor to carry out redundancy, so that 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 parameter control pressure parameter judging method and a redundancy control method of a small turbofan engine.
Background
The total pressure after 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 after the compressor and is converted into a control parameter through A/D (analog/digital). The oil-gas ratio control law of the relatively common engine is used as a calculation basis for oil supply adjustment. In case of a malfunction of the signal, this means that the oil supply adjustment cannot be performed accurately, with serious consequences. Therefore, under the condition that the problem always appears after the compressor of the engine, the judgment needs to be timely and accurately carried out, and the problem needs to be replaced through parameter analysis.
The parameter analysis method is to analyze the pressure, temperature and the like in an air flow channel of the engine, including the total pressure after the air compressor, through other working parameters of the engine, such as the engine speed, the engine inlet air state and the like.
Aeroengines typically have redundant engine control signals, and hardware redundancy is often used. However, the small turbofan engine is often unsuitable for hardware redundancy due to size, weight, cost, and other factors.
Disclosure of Invention
In view of the above, the invention provides a parameter and control pressure parameter judging method and a redundancy control method for a small turbofan engine, which can accurately judge fault information in real time and realize redundancy control.
A method for judging the parameter of the control pressure of a small turbofan engine comprises the following steps:
and judging whether the total air flow pressure U3TD signal after the compressor of the engine is normal or not according to the following criteria between the preparation of the engine and the starting success:
when the total pressure voltage U3TD of the air flow behind the engine compressor exceeds the set upper limit or the set lower limit for 3 times continuously, the signal of the total pressure voltage U3TD of the air flow behind the engine compressor is considered to be abnormal;
after the engine is started successfully, until the engine is stopped, judging whether the total air flow voltage U3TD signal of the engine compressor is normal or not according to the following criteria:
when the control right is obtained by continuous 3-period acceleration control, the sensor is considered to be faulty, namely the total pressure U3TD signal of the airflow after the engine compressor is abnormal;
and when the control right is obtained by continuous 3-period deceleration control, the sensor is considered to be faulty, namely the total pressure U3TD signal of the airflow after the engine compressor is abnormal.
Preferably, the calculation formulas of the set upper limit U3td_max and the set lower limit U3td_min of the total pressure voltage amount U3TD of the air flow after the compressor of the engine are 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 parameter redundancy control method for a parameter control pressure of a small turbofan engine comprises the following steps:
and judging whether the total air flow pressure U3TD signal after the compressor of the engine is normal or not according to the following criteria between the preparation of the engine and the starting success:
when the total pressure voltage U3TD of the air flow behind the engine compressor exceeds the set upper limit or the set lower limit for 3 times continuously, the signal of the total pressure voltage U3TD of the air flow behind the engine compressor is considered to be abnormal;
after the engine is started successfully, until the engine is stopped, judging whether the total air flow voltage U3TD signal of the engine compressor is normal or not according to the following criteria:
when the control right is obtained by continuous 3-period acceleration control, the sensor is considered to be faulty, namely the total pressure U3TD signal of the airflow after the engine compressor is abnormal;
when the control right is obtained by continuous 3-period deceleration control, the sensor is considered to be faulty, namely the total pressure U3TD signal of the airflow after the engine compressor is abnormal;
calculating engine performance data by using an engine model performance simulation mathematical model and utilizing the input air pressure height H, mach number Ma, engine throttle control voltage Uy, engine high-voltage rotor rotating speed nh and total temperature voltage U6TD after an engine fan, and storing the engine performance data into a performance data table;
after judging that the total air flow voltage U3TD signal after the engine compressor is abnormal, if the current state is that the engine is successfully started, redundant control is not performed, and the task flow is terminated;
if the current engine is successfully started, stopping using the current collected total pressure voltage U3TD of the air flow after the engine air compressor, and interpolating from a performance data table according to the current received pressure height H, mach number Ma, engine accelerator control voltage Uy and engine high-pressure rotor rotating speed nh to obtain the value of the total pressure voltage U3TD of the air flow after the engine air compressor, thereby participating in control calculation.
Preferably, the calculation formulas of the set upper limit U3td_max and the set lower limit U3td_min of the total pressure voltage amount U3TD of the air flow after the compressor of the engine are 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 then stored in the performance data table.
Preferably, the Mach number Ma is in the range of 0 to 0.9 when calculating the engine performance data.
Preferably, when calculating engine performance data, the range of the air pressure height H is 0-13 km.
Preferably, when calculating engine performance data, the range of the engine throttle control voltage Uy is 1V-16V.
The invention has the following beneficial effects:
the invention provides a parameter control pressure parameter judging method and a redundancy control method for a small turbofan engine, which are used for judging important control parameters of the small turbofan engine used by an unmanned aerial vehicle, namely a reasonable judging strategy for total compression after a compressor, so as to accurately judge fault information in real time;
and under the condition that the total pressure of an engine compressor is unreliable, the total pressure of the compressor is calculated by using parameters such as an engine inlet parameter, a rotating speed, a total temperature after a fan and the like to replace the acquisition parameters of the original sensor to carry out redundancy, so that the normal flight of the unmanned aerial vehicle is ensured, and the working reliability is improved.
Drawings
FIG. 1 is a Pt3 determination and redundancy control flow chart of the present invention;
FIG. 2 is a diagram showing the verification effect of the method of the present invention.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The reference symbols used in the present invention are defined as follows:
P t3 representation ofThe total pressure of the rear air flow of the compressor of the engine is kilopascals (kPa); u3TD represents the total pressure voltage of the air flow after the compressor of the engine, and the unit is V; tt13 represents the total temperature after the engine fan in Kelvin (K); u6TD represents the total temperature and voltage quantity after the engine presses the fan, and the unit is V; uy represents the engine throttle control voltage, corresponding to thrust, in volts (V); nh represents the rotation speed of the high-pressure rotor of the engine, and the unit is revolutions per minute (r/min); h represents the pressure altitude in kilometers (km); ma represents Mach number, and the ratio of the flying speed to the local sonic velocity is a dimensionless parameter.
The method mainly comprises the following steps:
1) The method of the invention is used for acting at the moment
After the engine is electrified to before the engine is stopped, the engine starts to participate in the control period according to the oil-gas ratio control law.
2) Method for judging faults of total pressure signals after engine gas compressor
On the basis of control characteristic analysis and fault data analysis of the oil-gas ratio control law, the fault reporting criterion of the total pressure Pt3 sensor after the gas compressor is formulated according to different working stages.
The engine work flow is to prepare the engine for starting, starting successfully, and stopping the engine.
The Pt3 sensor judgment criteria are based on the following between the preparation of the start and the success of the start:
abnormality criterion 1: and judging that the U3TD (Pt 3) exceeds the upper limit or the lower limit for 3 times continuously, namely, the U3TD_max is more than or equal to the U3TD_max or the U3TD_min is less than or equal to the lower limit, and considering that the U3TD (Pt 3) signal is abnormal. Wherein, U3TD_max and U3TD_min are functions of the starting time air pressure height H, 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), H is more than or equal to 0 and less than or equal to 5000m.
After the starting is successful, the engine is stopped, and the judgment criterion of the Pt3 sensor is as follows:
abnormality criterion 2: when the acceleration control gains control (i.e., triggers a guard line due to too high an air-fuel ratio, meaning Pt3 is abnormally high) for 3 consecutive cycles, the sensor is considered to be faulty.
Abnormality criterion 3: when the continuous 3-cycle deceleration control obtains control authority (namely, triggers a warning line caused by the too low oil-gas ratio, which means that Pt3 is abnormally low), the U3TD signal is judged to be abnormal.
3) Redundancy method after engine rotating speed signal failure
The redundancy scheme adopted is as follows: an engine performance data table is calculated using an engine model performance simulation program (which contains a mathematical model of the engine's main components) and corrected using engine test data. The performance data table includes inlet condition parameters H, ma, uy, nh, U TD. Based on the factors such as precision influence, common range, memory data table size and the like, the Mach number value range is determined to be 0-0.9, the height value is 0-13 km, the Uy range is 1V-16V, engine performance data are calculated in the ranges, and the engine performance data are set in the memory of the engine digital controller in a data table mode.
After judging that the Pt3 signal fails, 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 used at the moment. The temperature and the like are changed severely, and the engine is easily damaged due to overtemperature, overturning and the like in the starting process of the engine caused by improper oil-gas ratio due to untimely response, so that the process is not redundant, emergency treatment is adopted, and the task flow is terminated.
After the engine is successfully started, the current U3TD acquired by the AD is stopped, and the U3TD is obtained by interpolation from an engine performance data sheet according to the currently received H, ma and the actual throttle control voltage Uy calculated through nh and U6TD to participate in control calculation.
The test verification effect is shown in fig. 2, and when the fault code is jumped to be 4, the consistency is better after the fault code is replaced by the simulation U3TD, the calculation deviation can ensure the normal operation of the engine, and the thrust control error is in the allowable range for the unmanned aerial vehicle. As can be seen, the verification effect meets the requirements.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A parameter redundancy control method for a parameter control pressure of a small turbofan engine is characterized by comprising the following steps:
and judging whether the total air flow pressure U3TD signal after the compressor of the engine is normal or not according to the following criteria between the preparation of the engine and the starting success:
when the total pressure voltage U3TD of the air flow behind the engine compressor exceeds the set upper limit U3TD_max or the set lower limit U3TD_min for 3 times continuously, the signal of the total pressure voltage U3TD of the air flow behind the engine compressor is considered to be abnormal;
after the engine is started successfully, until the engine is stopped, judging whether the total air flow voltage U3TD signal of the engine compressor is normal or not according to the following criteria:
when the control right is obtained by continuous 3-period acceleration control, the sensor is considered to be faulty, namely the total pressure U3TD signal of the airflow after the engine compressor is abnormal;
when the control right is obtained by continuous 3-period deceleration control, the sensor is considered to be faulty, namely the total pressure U3TD signal of the airflow after the engine compressor is abnormal;
calculating engine performance data by using an engine model performance simulation program and utilizing the input air pressure height H, mach number Ma, engine throttle control voltage Uy, engine high-voltage rotor rotating speed nh and total temperature voltage quantity U6TD behind an engine fan, correcting the engine performance data by using engine test data after calculating the engine performance data, and storing the engine performance data into a performance data table;
after judging that the total air flow voltage U3TD signal after the engine compressor is abnormal, if the current state is that the engine is successfully started, redundant control is not performed, and the task flow is terminated;
if the current engine is successfully started, stopping using the current collected total pressure voltage U3TD of the air flow after the engine air compressor, and interpolating from a performance data table according to the current received pressure height H, mach number Ma, engine accelerator control voltage Uy and engine high-pressure rotor rotating speed nh to obtain the value of the total pressure voltage U3TD of the air flow after the engine air compressor, thereby participating in control calculation.
2. The method for controlling redundancy of parameters of control pressure parameters of a small turbofan engine as claimed in claim 1, wherein the calculation formulas of the set upper limit u3td_max and the set lower limit u3td_min of the total pressure voltage amount U3TD of the air flow after the compressor of the engine are:
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. The method for controlling redundancy of parameter control pressure of small turbofan engine as claimed in claim 1, wherein the mach number Ma is in the range of 0-0.9 when calculating engine performance data.
4. A method for controlling redundancy of parameter of controlling pressure of small turbofan engine as claimed in claim 3, wherein the range of air pressure height H is 0-13 km when calculating engine performance data.
5. The method for controlling the redundancy of parameter control pressure of a small turbofan engine as claimed in claim 3 or 4, wherein the range of the throttle control voltage Uy of the engine is 1V-16V when calculating the engine performance data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210393843.7A CN114893300B (en) | 2022-04-14 | 2022-04-14 | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210393843.7A CN114893300B (en) | 2022-04-14 | 2022-04-14 | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114893300A CN114893300A (en) | 2022-08-12 |
| CN114893300B true CN114893300B (en) | 2023-10-13 |
Family
ID=82718230
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210393843.7A Active CN114893300B (en) | 2022-04-14 | 2022-04-14 | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114893300B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4765133A (en) * | 1986-12-08 | 1988-08-23 | United Technologies Corporation | Fuel control with smooth mode transition |
| JPH03258928A (en) * | 1990-03-06 | 1991-11-19 | Toyota Motor Corp | Fuel control device for gas turbine engine |
| CN102459822A (en) * | 2009-06-10 | 2012-05-16 | 斯奈克玛 | Method for testing the protection chain of a turbine engine against overspeed upon starting |
| CN203499824U (en) * | 2013-07-24 | 2014-03-26 | 长安大学 | Control system capable of digging acceleration potential of aircraft engine |
| CN108168900A (en) * | 2017-11-22 | 2018-06-15 | 北京动力机械研究所 | Meet the unmanned plane control method for starting machine width envelope thrust requirements |
| JP2018189032A (en) * | 2017-05-09 | 2018-11-29 | トヨタ自動車株式会社 | Motor assist gas turbine engine |
| CN110657032A (en) * | 2019-10-08 | 2020-01-07 | 中国航发沈阳发动机研究所 | Method for determining flow control rule of boosting total fuel oil |
| CN111648992A (en) * | 2020-06-02 | 2020-09-11 | 上海工业自动化仪表研究院有限公司 | Gas turbine compressor fault identification early warning method |
| CN112832910A (en) * | 2020-11-04 | 2021-05-25 | 北京动力机械研究所 | Method for identifying air flameout and secondary starting success of turbofan engine |
| CN113899559A (en) * | 2021-11-23 | 2022-01-07 | 中国航发沈阳发动机研究所 | Reconstruction method and device for failure of total air inlet temperature of aero-engine |
| CN114320613A (en) * | 2021-12-16 | 2022-04-12 | 北京航空航天大学 | Engine mode conversion determination method and device, engine and aircraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006226157A (en) * | 2005-02-16 | 2006-08-31 | Honda Motor Co Ltd | Method and device for failure diagnosis of atmospheric pressure sensor |
| JP4890095B2 (en) * | 2006-05-19 | 2012-03-07 | 株式会社Ｉｈｉ | Stall sign detection device and method, and engine control system |
| US20190271608A1 (en) * | 2018-03-01 | 2019-09-05 | GM Global Technology Operations LLC | Method to estimate compressor inlet pressure for a turbocharger |
-
2022
- 2022-04-14 CN CN202210393843.7A patent/CN114893300B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4765133A (en) * | 1986-12-08 | 1988-08-23 | United Technologies Corporation | Fuel control with smooth mode transition |
| JPH03258928A (en) * | 1990-03-06 | 1991-11-19 | Toyota Motor Corp | Fuel control device for gas turbine engine |
| CN102459822A (en) * | 2009-06-10 | 2012-05-16 | 斯奈克玛 | Method for testing the protection chain of a turbine engine against overspeed upon starting |
| CN203499824U (en) * | 2013-07-24 | 2014-03-26 | 长安大学 | Control system capable of digging acceleration potential of aircraft engine |
| JP2018189032A (en) * | 2017-05-09 | 2018-11-29 | トヨタ自動車株式会社 | Motor assist gas turbine engine |
| CN108168900A (en) * | 2017-11-22 | 2018-06-15 | 北京动力机械研究所 | Meet the unmanned plane control method for starting machine width envelope thrust requirements |
| CN110657032A (en) * | 2019-10-08 | 2020-01-07 | 中国航发沈阳发动机研究所 | Method for determining flow control rule of boosting total fuel oil |
| CN111648992A (en) * | 2020-06-02 | 2020-09-11 | 上海工业自动化仪表研究院有限公司 | Gas turbine compressor fault identification early warning method |
| CN112832910A (en) * | 2020-11-04 | 2021-05-25 | 北京动力机械研究所 | Method for identifying air flameout and secondary starting success of turbofan engine |
| CN113899559A (en) * | 2021-11-23 | 2022-01-07 | 中国航发沈阳发动机研究所 | Reconstruction method and device for failure of total air inlet temperature of aero-engine |
| CN114320613A (en) * | 2021-12-16 | 2022-04-12 | 北京航空航天大学 | Engine mode conversion determination method and device, engine and aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 涡扇发动机高空起动模型研究;周文祥;航空动力学报;第22卷(第8期);第1384-1390页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114893300A (en) | 2022-08-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4622808A (en) | Surge/stall cessation detection system | |
| CN100458122C (en) | Methods and apparatus for assessing gas turbine damage | |
| US7246024B2 (en) | Sensor malfunction detection system for gas-turbine engine | |
| US7246495B2 (en) | Control system for gas-turbine engine | |
| US4437303A (en) | Fuel control system for a gas turbine engine | |
| EP3287609B1 (en) | Turbofan shaft break detection system and method | |
| GB2436366A (en) | Monitoring Gas Turbine Engines | |
| US4528812A (en) | Fuel control system for a gas turbine engine | |
| EP0092425B1 (en) | Gas turbine engine fuel control | |
| KR20160140703A (en) | Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device | |
| US20210372295A1 (en) | Turbine engine operational testing | |
| US10551818B2 (en) | Fault detection methods and systems | |
| US20050234689A1 (en) | One-engine-inoperative training method and system | |
| US2882615A (en) | Apparatus for simulating turbo-jet aircraft engine operation | |
| CN114893300B (en) | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine | |
| JPS63150436A (en) | Device and method of controlling gas turbine engine | |
| CA3053265A1 (en) | Monitoring servo valve filter elements | |
| US9828106B2 (en) | Aircraft gas turbine propulsion engine control without aircraft total air temperature sensors | |
| US20240003300A1 (en) | In-flight engine re-start | |
| EP1837506A2 (en) | Monitoring gas turbine engines | |
| JPS63150435A (en) | Device and method of controlling gas turbine engine | |
| US11225882B2 (en) | Method and apparatus for determining a present value based on previously obtained values of a measured variable of a gas turbine engine and/or a thermodynamic process | |
| KR101757492B1 (en) | Non-flame-out test for the combustion chamber of a turbine engine | |
| CN114893301B (en) | Parameter control temperature parameter judging method and redundancy control method for small turbofan engine | |
| EP3712737B1 (en) | Signal response monitoring for turbine engines |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |