CN109488461A - Mitigate the control system and method for the load of aero-engine cold-starting - Google Patents
Mitigate the control system and method for the load of aero-engine cold-starting Download PDFInfo
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- CN109488461A CN109488461A CN201811364159.6A CN201811364159A CN109488461A CN 109488461 A CN109488461 A CN 109488461A CN 201811364159 A CN201811364159 A CN 201811364159A CN 109488461 A CN109488461 A CN 109488461A
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- oil
- aero
- switch element
- oil temperature
- controlled switch
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Classifications
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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
- F02C7/06—Arrangements of bearings; Lubricating
Abstract
The invention discloses a kind of control systems of mitigation aero-engine cold-starting load, aero-engine includes fuel system, oil system and for oil system provide lubricating oil oil supply system, it includes the electric-controlled switch element for being set in oil supply system and being in normally off, for detecting the oil temperature sensor of oil temperature, for detecting the fuel temperature sensor of fuel oil temperature, for detecting the pressure sensor of aircraft flight height and for according to oil temperature sensor, the controller of the working condition of the testing result control electric-controlled switch element of at least one of fuel temperature sensor and pressure sensor three；Electric-controlled switch element, oil temperature sensor, fuel temperature sensor and pressure sensor are connect with controller.The control system and method for mitigation aero-engine cold-starting load of the invention, improve the success rate of aero-engine cold-starting, while shortening the time of aero-engine cold-starting.
Description
Technical field
The present invention relates to aero-engine cold-starting technical fields, particularly, it is low to be related to a kind of mitigation aero-engine
The control system and method for startup temperature load.
Background technique
Oil pump payload size is affected by temperature.At low ambient temperatures, lubricating oil viscosity increases, and causes oil pump by engine
The power demand that starting system is extracted becomes larger, and will lead to Aero-Engine Start acceleration variation in this way, even results in starting not
Success.Existing aero-engine does not account for the problem of how mitigating aero-engine cold-starting load.
Summary of the invention
It is existing to solve the present invention provides the control system and method for a kind of mitigation aero-engine cold-starting load
Aero-engine start that acceleration is poor or even the unsuccessful technical problem of starting in cold-starting.
According to an aspect of the present invention, a kind of control system of mitigation aero-engine cold-starting load, boat are provided
Empty engine include fuel system, oil system and for oil system provide lubricating oil oil supply system comprising be set to
In oil supply system and it is in the electric-controlled switch element of normally off, the oil temperature sensor for detecting oil temperature, is used for
Detect the fuel temperature sensor of fuel oil temperature, the pressure sensor for detecting aircraft flight height and for according to lubricating oil
The testing result of at least one of temperature sensor, fuel temperature sensor and pressure sensor three control electric-controlled switch element
Working condition controller；Electric-controlled switch element, oil temperature sensor, fuel temperature sensor and pressure sensor with
Controller connection.
Further, when oil temperature sensor detects oil temperature lower than setting value, or when fuel oil temperature passes
When sensor detects fuel oil temperature lower than setting value, or when pressure sensor detects that aircraft flight height is higher than setting value
When, controller controls electric-controlled switch element and opens.
Further, control system further includes connecting and being used for the velocity pick-up for detecting aero-engine revolving speed with controller
Device；When the velocity sensor detects the revolving speed of aero-engine higher than setting value, controller controls electric-controlled switch element
It closes.
Further, oil temperature sensor, fuel temperature sensor and pressure sensor are what aero-engine carried
Sensor.
Further, electric-controlled switch element is solenoid valve or motor-driven valve.
Further, electric-controlled switch element is motor-driven valve, and controller is used to be sensed according to velocity sensor and oil temperature
The lubricating oil input quantity of the testing result control electric-controlled switch element of device.
Further, controller includes memory module, comparison module and control module；According to different cunnings in memory module
Oil temperature range is preset with different lubricating oil input quantities；The oil temperature that comparison module detects oil temperature sensor
Value is compared with the oil temperature range stored in memory module, and exports feedback signal transmission to control according to comparison result
Module；Control module controls the lubricating oil input quantity of electric-controlled switch element according to the feedback signal.
Further, which further includes neural network module connected to the controller, and neural network module is used for basis
The control parameter of the testing result and electric-controlled switch element of velocity sensor and oil temperature sensor carry out deep learning with
Realize the intelligentized control method of electric-controlled switch element.
The present invention also provides a kind of control method of mitigation aero-engine cold-starting load, aero-engine includes combustion
Oil system, oil system and for oil system provide lubricating oil oil supply system, the control method the following steps are included:
Step S1: the electric-controlled switch element for being in normally off is set in oil supply system；
Step S2: at least one of oil temperature, fuel oil temperature and flying height three are detected；
Step S3: the working condition based on testing result control electric-controlled switch element.
Further, the control method is further comprising the steps of:
Step S4: when the revolving speed for detecting aero-engine is higher than setting value, control electric-controlled switch element is closed.
The invention has the following advantages:
The control system of mitigation aero-engine cold-starting load of the invention passes through according to velocity sensor and lubricating oil
The testing result control electric-controlled switch element of temperature sensor is opened, and is prevented oil pump oiling, is made the import of lubricating oil booster pump
Emptying prevents pressurization oil pump feed to oil system, the lubricating oil amount of oil system input is reduced, to reduce the totality of lubricating oil
Viscosity reduces influence of the oil viscosity to the accelerating ability of engine, improves the success rate of aero-engine cold-starting,
The time of aero-engine cold-starting is shortened simultaneously.
The control method of mitigation aero-engine cold-starting load of the invention, passes through the fuel feeding in aero-engine
One normally closed electric-controlled switch element, and the revolving speed based on the aero-engine detected and detection oil system are set in system
In oil temperature control electric-controlled switch element working condition, when aero-engine revolving speed be lower than setting value and oil temperature
When lower than setting value, control electric-controlled switch element is opened, and is prevented oil pump oiling, is vented the import of lubricating oil booster pump, is hindered
Only to oil system, the lubricating oil amount for reducing oil system input subtracts pressurization oil pump feed to reduce the overall viscosity of lubricating oil
Influence of the oil viscosity to the accelerating ability of engine is lacked, has improved the success rate of aero-engine cold-starting, contract simultaneously
The short time of aero-engine cold-starting.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the modular structure of the control system of the mitigation aero-engine cold-starting load of the preferred embodiment of the present invention
Schematic diagram.
Fig. 2 is the sub-modular structure schematic diagram of the controller in Fig. 1 of the preferred embodiment of the present invention.
Fig. 3 is the process signal of the control method of the mitigation aero-engine cold-starting load of the preferred embodiment of the present invention
Figure.
Marginal data:
11, electric-controlled switch element；12, fuel temperature sensor；13, oil temperature sensor；14, pressure sensor；15,
Velocity sensor；17, controller；18, neural network module；171, memory module；173, comparison module；175, control module.
Specific embodiment
The embodiment of the present invention is described in detail below in conjunction with attached drawing, but the present invention can be limited by following and
The multitude of different ways of covering is implemented.
As shown in Figure 1, the preferred embodiment of the present invention provides a kind of control of mitigation aero-engine cold-starting load
System is used to mitigate the starting duty of aero-engine at low ambient temperatures, to ensure aero-engine at low ambient temperatures
With good acceleration so as to smoothly starting.Aero-engine includes fuel system, oil system and is used for lubricating oil
System provides the oil supply system of lubricating oil, and fuel system and oil system are under same working environment.The mitigation aviation
The control system of engine cold-starting load includes the electric-controlled switch element for being set in oil supply system and being in normally off
11, the oil temperature sensor 13 for detecting oil temperature, 15 and of velocity sensor for detecting aero-engine revolving speed
For controlling the working condition of electric-controlled switch element 11 according to the testing result of velocity sensor 15 and oil temperature sensor 13
Controller 17, electric-controlled switch element 11, oil temperature sensor 13 and velocity sensor 15 are connect with controller 17.It can be with
Understand, the controller 17 is PLC or MCU.It is appreciated that the oil temperature sensor 13 can be aero-engine certainly
The sensor of band is also possible to subsequent be loaded in aero-engine.
The reduction of the viscosity with temperature of lubricating oil in aero-engine and increase, freezing point be -60 DEG C or so, work as aeroplane engine
When machine flying height is 12000 meters, atmospheric temperature is generally -56 DEG C, and aero-engine is under low temperature environment, at this time lubricating oil
Viscosity is larger, and the power demand for causing oil pump to extract from engine starting system becomes larger, so as to cause Aero-Engine Start
Acceleration is deteriorated, and even results in fail to start.Especially when atmospheric temperature is -25 DEG C or less deep colling, lubricating oil viscosity increases
Obviously, the Aero-Engine Start moment of resistance is caused to dramatically increase.According to the high and cold test data analyzer of aero-engine, in big temperature
Degree is respectively that the moment of resistance under the conditions of 15 DEG C and -24 DEG C has differed 10N*M, thus can by mitigate the load of oil system come
Reduce oil viscosity, and then mitigate the load of aero-engine cold-starting, be conducive to aero-engine under low temperature environment at
Function starts.And the load of oil pump is mainly determined by oil flow and pressure, when the lubricating oil amount of input is reduced, oil pump
Load is also reduced therewith, just reduces the overall viscosity of lubricating oil naturally.When velocity sensor 15 detects turning for aero-engine
When speed is lower than setting value, it is meant that the revolving speed of aero-engine at this time is not met by entry condition, needs to further speed up boat
The revolving speed of empty engine, and when oil temperature sensor 13 detects the oil temperature in oil system lower than setting value, meaning
Lubricating oil at this time viscosity it is larger, controller 17 controls electric-controlled switch element 11 and opens；Otherwise, controller 17 controls electric-controlled switch
Element 11 is closed.It is appreciated that the speed setting value of aero-engine, which represents aero-engine, has had enough revolving speeds
It can guarantee to start successfully.It is appreciated that the electric-controlled switch element 11 is solenoid valve or motor-driven valve, it is preferred to use electronic
Valve, controller 17 can control its lubricating oil input quantity by controlling the opening degree of motor-driven valve, to realize lubricating oil input quantity
Accurate adjusting.It is appreciated that is, velocity sensor 15 detects aero-engine after Aero-Engine Start success
Revolving speed is more than or equal to setting value, and controller 17 controls electric-controlled switch element 11 and closes, to keep oil supply system smooth
Ground supplements lubricating oil to oil system.
The control system of mitigation aero-engine cold-starting load of the invention passes through according to velocity sensor 15 and cunning
The testing result control electric-controlled switch element 11 of oil temperature sensor 13 is opened, and is prevented oil pump oiling, is made lubricating oil booster pump
Import emptying, prevent pressurization oil pump feed to oil system, the lubricating oil amount of oil system input reduced, to reduce lubricating oil
Overall viscosity, reduce influence of the oil viscosity to the accelerating ability of engine, improve aero-engine cold-starting
Success rate, while shortening the time of aero-engine cold-starting.
It is appreciated that preferably, it is described mitigate aero-engine cold-starting load control system further include with
Controller 17 connects and the fuel temperature sensor 12 for detecting fuel oil temperature, due to the fuel system and cunning of aero-engine
Oil system is under same working environment, therefore can obtain lubricating oil by detecting the fuel oil temperature of fuel system as reference
Temperature.Controller 17 controls electric-controlled switch element 11 according to the testing result of velocity sensor 15 and fuel temperature sensor 12 and beats
On or off is closed.The fuel temperature sensor 12 is the sensor carried in aero-engine, or is navigating for subsequent installation
On empty engine.In a preferred embodiment of the invention, oil temperature can directly be detected by oil temperature sensor 13,
Fuel oil temperature can also be detected by fuel temperature sensor 12 to obtain oil temperature indirectly, there are two types of selection schemes for tool, can
It is stronger by property.When oil temperature sensor 13 breaks down, lubricating oil temperature can not be directly detected by oil temperature sensor 13
Degree can also detect fuel oil temperature by fuel temperature sensor 12 to obtain oil temperature indirectly.
It is appreciated that preferably, it is described mitigate aero-engine cold-starting load control system further include with
Controller 17 connects and the pressure sensor 14 for detecting flying height, cunning can be calculated by detection flying height
Temperature environment locating for oil system to get arrive oil temperature.When oil temperature sensor 13 breaks down, 17 basis of controller
The testing result of pressure sensor 14 and velocity sensor 15 control electric-controlled switch element 11 turns on or off.The pressure passes
Sensor 14 is the sensor carried in aero-engine, or is subsequent installation in aero-engine.Of the invention preferred
In embodiment, oil temperature can directly be detected by oil temperature sensor 13, can also be examined by pressure sensor 14
Flying height is surveyed oil temperature is calculated, for tool there are two types of selection scheme, reliability is stronger.When oil temperature sensor 13 is sent out
When raw failure, oil temperature can not be directly detected by oil temperature sensor 13, can also be detected by pressure sensor 14
Flying height is calculated oil temperature.
It is appreciated that the oil temperature sensor 13, fuel temperature sensor 12 and 14 three of pressure sensor can be with
It exists simultaneously, as long as the oil temperature that oil temperature sensor 13 detects is detected lower than setting value, fuel temperature sensor 12
To fuel oil temperature be higher than in three conditions of setting value extremely lower than the flying height that setting value and pressure sensor 14 detect
A few condition is set up, and velocity sensor 15 detects the revolving speed of aero-engine also below setting value, and controller 17 is controlled
Electric-controlled switch element 11 processed is opened.It is further appreciated that the velocity sensor 15 can be omitted, because engine starts just
When, revolving speed is necessarily lower than setting value, and aero-engine when there is no need to using 15 pairs of velocity sensor startings turns
Speed is detected.
As shown in Fig. 2, the controller 17 includes memory module 171, comparison module 173 and control module 175, mould is stored
It is preset with different lubricating oil input quantities in block 171 according to different oil temperature ranges, comparison module 173 is by oil temperature
The oil temperature range stored in the oil temperature value that sensor 13 detects and memory module 171 is compared, and according to than
Feedback signal transmission is exported to control module 175 to result, control module 175 controls electric-controlled switch element according to the feedback signal
11 lubricating oil input quantity.Wherein, comparison module 173 is connect with memory module 171 and control module 175 respectively, comparison module 173
Also it is connect with oil temperature sensor 13 or fuel temperature sensor 12 or pressure sensor 14.When comparison module 173 compares out
When the oil temperature that oil temperature sensor 13 detects is fallen into a certain preset temperature range, comparison module 173 is i.e. from storage
Corresponding lubricating oil input quantity is read in module 171 and is transferred to control module 175, and control module 175 passes through control electric-controlled switch
The opening degree of element 11 adjusts corresponding lubricating oil input quantity.
It is appreciated that preferably, it is described mitigate aero-engine cold-starting load control system further include with
The neural network module 18 that controller 17 connects, neural network module 18 is by velocity sensor 15 and oil temperature sensor 13
Testing result and the control parameter of electric-controlled switch element 11 are used as basic data to carry out deep learning to realize electric-controlled switch member
11 intelligentized control method of part.Neural network module 18 is neuron chip.Neuron chip can be detected based on velocity sensor 15
To aero-engine the control of oil temperature and electric-controlled switch element 11 that detects of revolving speed, oil temperature sensor 13
Parameter carries out deep learning, to obtain optimal electric-controlled switch element based on different aero-engine revolving speeds and oil temperature
11 control parameter, and the optimization control parameter is transmitted to controller 17, controller 17 is according to the optimization control parameter to electricity
Control switch element 11 is controlled, to be precisely controlled the lubricating oil input quantity of electric-controlled switch element 11.The present invention passes through setting
Neural network module 18 with deep learning function configures to execute the optimization control parameter of electric-controlled switch element 11, realizes
Intelligentized control method does not need the participation of artificial experience, and regulation accuracy is higher, and at low ambient temperatures with aero-engine
Continuous starting, basic data constantly updates, and neural network module 18 is by the optimization control parameter that obtains after deep learning
It is more accurate, also it is more in line with the demand in big data processing epoch.
As shown in figure 3, another embodiment of the present invention also provides a kind of control of mitigation aero-engine cold-starting load
Method processed is used to mitigate the starting duty of aero-engine at low ambient temperatures, to ensure aero-engine in low temperature environment
Have good acceleration so as to smoothly start down, preferably mitigates aero-engine cold-starting using as described above
The control system of load.It is described mitigate aero-engine cold-starting load control method the following steps are included:
Step S1: the electric-controlled switch element for being in normally off is set in oil supply system；
Step S2: the oil temperature in the revolving speed and detection oil system of aero-engine is detected；
Step S3: the working condition based on the revolving speed detected and oil temperature control electric-controlled switch element.
It is appreciated that in step sl, electric-controlled switch element can control the lubricating oil that oil supply system inputs to oil system
Amount, electric-controlled switch element can be solenoid valve or electrically-controlled valve, it is contemplated that the precision of adjusting can choose electrically-controlled valve, if examined
Consider production cost selection solenoid valve.
It is appreciated that in step s 2, the revolving speed of aero-engine being detected especially by velocity sensor, utilizes lubricating oil
Temperature sensor detects the oil temperature in oil system.Wherein, velocity sensor and oil temperature sensor are all aviations
The included sensor of engine.When velocity sensor detects the revolving speed of aero-engine lower than setting value, and oil temperature
Sensor detects the oil temperature in oil system lower than setting value, and control electric-controlled switch element is opened, to reduce lubricating oil system
The lubricating oil input quantity of system reduces oil viscosity to the shadow of the accelerating ability of engine to reduce the overall viscosity of lubricating oil
It rings, so as to ensure that aero-engine at low ambient temperatures can be with Successful startup.If velocity sensor detects that aviation is sent out
The revolving speed of motivation is higher than setting value, then controls electric-controlled switch element and remain off；Or velocity sensor detects aviation
The revolving speed of engine is lower than setting value, but oil temperature sensor detects big oil temperature and is higher than setting value, also controls automatically controlled open
Element is closed to remain off.Fuel oil temperature also is detected using fuel temperature sensor in step s 2 or utilizes pressure sensing
Device detects the flying height of aircraft, and in step s3 according to the revolving speed of aero-engine and fuel oil temperature control electric-controlled switch member
The working condition of part, or according to the revolving speed of aero-engine and the working condition of flight altitude control electric-controlled switch element.That is,
At least one of oil temperature, fuel oil temperature and flying height three are detected in step s 2, and in step s3
The working condition of electric-controlled switch element is controlled according to the testing result of at least one of three.It is further appreciated that the step S2
In can not have to the revolving speed of detection aero-engine because aero-engine is in rigid starting, revolving speed is necessarily lower than setting
Value.
It is appreciated that in step s3, it is specific using controller come based on velocity sensor and oil temperature sensor
Testing result controls the working condition of electric-controlled switch element, and the controller is PLC or MCU.When oil temperature sensor is examined
When measuring oil temperature lower than setting value, perhaps when fuel temperature sensor detects fuel oil temperature lower than setting value or
When pressure sensor detects that aircraft flight height is higher than setting value, controller controls electric-controlled switch element and opens.Alternatively, making
For another kind selection, it can use neuron chip and match hop controller to control the working condition of electric-controlled switch element, neuron
Oil temperature that revolving speed, the oil temperature sensor for the aero-engine that chip is detected based on velocity sensor detect and
The control parameter of electric-controlled switch element carries out deep learning, to be obtained based on different aero-engine revolving speeds and oil temperature
The control parameter of optimal electric-controlled switch element, and the optimization control parameter is transmitted to controller, controller is best according to this
Control parameter controls electric-controlled switch element, to be precisely controlled the lubricating oil input quantity of electric-controlled switch element.By setting
The neuron chip with deep learning function is set to execute the configuration of the optimization control parameter of electric-controlled switch element, realizes intelligence
Change control, do not need the participation of artificial experience, regulation accuracy is higher, and at low ambient temperatures not with aero-engine
Disconnected to start, basic data is constantly updated, and neuron chip is more accurate by the optimization control parameter obtained after deep learning,
Also it is more in line with the demand in big data processing epoch.
It is appreciated that the control method for mitigating the load of aero-engine cold-starting is further comprising the steps of
Step S4: when the revolving speed for detecting aero-engine is higher than setting value, control electric-controlled switch element is closed, thus
Allow oil supply system that can inject lubricating oil to oil system.
The control method of mitigation aero-engine cold-starting load of the invention, passes through the fuel feeding in aero-engine
One normally closed electric-controlled switch element, and the revolving speed based on the aero-engine detected and detection oil system are set in system
In oil temperature control electric-controlled switch element working condition, when aero-engine revolving speed be lower than setting value and oil temperature
When lower than setting value, control electric-controlled switch element is opened, and is prevented oil pump oiling, is vented the import of lubricating oil booster pump, is hindered
Only to oil system, the lubricating oil amount for reducing oil system input subtracts pressurization oil pump feed to reduce the overall viscosity of lubricating oil
Influence of the oil viscosity to the accelerating ability of engine is lacked, has improved the success rate of aero-engine cold-starting, contract simultaneously
The short time of aero-engine cold-starting.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of control system for mitigating the load of aero-engine cold-starting, aero-engine includes fuel system, lubricating oil system
It unites and for providing the oil supply system of lubricating oil to oil system, which is characterized in that
It includes being set in oil supply system and being in the electric-controlled switch element (11) of normally off, for detecting oil temperature
Oil temperature sensor (13), the fuel temperature sensor (12) for detecting fuel oil temperature, for detecting aircraft flight height
Pressure sensor (14) and for according to oil temperature sensor (13), fuel temperature sensor (12) and pressure sensor
(14) controller (17) of the working condition of testing result control electric-controlled switch element (11) of at least one of three；
Electric-controlled switch element (11), oil temperature sensor (13), fuel temperature sensor (12) and pressure sensor (14) are equal
It is connect with controller (17).
2. control system as described in claim 1, which is characterized in that
When oil temperature sensor (13) detects oil temperature lower than setting value, or when fuel temperature sensor (12) are examined
When measuring fuel oil temperature lower than setting value, or when pressure sensor (14) detects that aircraft flight height is higher than setting value,
Controller (17) controls electric-controlled switch element (11) and opens.
3. control system as claimed in claim 2, which is characterized in that
The control system further includes the velocity sensor for connecting with controller (17) and be used to detect aero-engine revolving speed
(15)；
When the velocity sensor (15) detects the revolving speed of aero-engine higher than setting value, controller (17) control is automatically controlled
Switch element (11) is closed.
4. control system as described in claim 1, which is characterized in that
Oil temperature sensor (13), fuel temperature sensor (12) and pressure sensor (14) are the biography that aero-engine carries
Sensor.
5. control system as described in claim 1, which is characterized in that
Electric-controlled switch element (11) is solenoid valve or motor-driven valve.
6. control system as claimed in claim 5, which is characterized in that
Electric-controlled switch element (11) is motor-driven valve,
Controller (17) is used to open according to the control of the testing result of velocity sensor (15) and oil temperature sensor (13) is automatically controlled
Close the lubricating oil input quantity of element (11).
7. control system as claimed in claim 6, which is characterized in that
Controller (17) includes memory module (171), comparison module (173) and control module (175)；
Different lubricating oil input quantities is preset with according to different oil temperature ranges in memory module (171)；
The interior storage of oil temperature value and memory module (171) that comparison module (173) detects oil temperature sensor (13)
Oil temperature range be compared, and feedback signal transmission is exported to control module (175) according to comparison result；
Control module (175) controls the lubricating oil input quantity of electric-controlled switch element (11) according to the feedback signal.
8. control system as described in claim 1, which is characterized in that
The system further includes the neural network module (18) connecting with controller (17),
Neural network module (18) be used for according to the testing result of velocity sensor (15) and oil temperature sensor (13) and
The control parameter of electric-controlled switch element (11) carries out deep learning to realize the intelligentized control method of electric-controlled switch element (11).
9. a kind of control method for mitigating the load of aero-engine cold-starting, aero-engine includes fuel system, lubricating oil system
It unites and for providing the oil supply system of lubricating oil to oil system, which is characterized in that
The control method the following steps are included:
Step S1: the electric-controlled switch element for being in normally off is set in oil supply system；
Step S2: at least one of oil temperature, fuel oil temperature and flying height three are detected；
Step S3: the working condition based on testing result control electric-controlled switch element.
10. control method as claimed in claim 9, which is characterized in that
The control method is further comprising the steps of:
Step S4: when the revolving speed for detecting aero-engine is higher than setting value, control electric-controlled switch element is closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811364159.6A CN109488461B (en) | 2018-11-16 | 2018-11-16 | Control system and method for reducing low-temperature starting load of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811364159.6A CN109488461B (en) | 2018-11-16 | 2018-11-16 | Control system and method for reducing low-temperature starting load of aircraft engine |
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| CN109488461B CN109488461B (en) | 2020-11-27 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105041408A (en) * | 2015-08-13 | 2015-11-11 | 奇瑞汽车股份有限公司 | Control system for electronically-controlled engine oil pump of engine, and control method thereof |
| CN105351030A (en) * | 2015-10-08 | 2016-02-24 | 中国南方航空工业(集团)有限公司 | Control device for low-temperature starting of aircraft engine |
| CN108224049A (en) * | 2018-03-20 | 2018-06-29 | 宁波铭瑞中兴电子科技有限公司 | A kind of vehicle lubricates EFM Electronic Fuel Management |
-
2018
- 2018-11-16 CN CN201811364159.6A patent/CN109488461B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105041408A (en) * | 2015-08-13 | 2015-11-11 | 奇瑞汽车股份有限公司 | Control system for electronically-controlled engine oil pump of engine, and control method thereof |
| CN105351030A (en) * | 2015-10-08 | 2016-02-24 | 中国南方航空工业(集团)有限公司 | Control device for low-temperature starting of aircraft engine |
| CN108224049A (en) * | 2018-03-20 | 2018-06-29 | 宁波铭瑞中兴电子科技有限公司 | A kind of vehicle lubricates EFM Electronic Fuel Management |
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| CN109488461B (en) | 2020-11-27 |
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