CN201943863U - Intelligent ground start system of aero-engine - Google Patents
Intelligent ground start system of aero-engine Download PDFInfo
- Publication number
- CN201943863U CN201943863U CN2011200006279U CN201120000627U CN201943863U CN 201943863 U CN201943863 U CN 201943863U CN 2011200006279 U CN2011200006279 U CN 2011200006279U CN 201120000627 U CN201120000627 U CN 201120000627U CN 201943863 U CN201943863 U CN 201943863U
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- engine
- aeroengine
- digital controller
- igniter
- fuel pump
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- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The utility model relates to an intelligent ground start system of an aero-engine, which comprises a full-authority digital controller, a programmable power supply, an igniter, a start electromagnetic valve, a fuel pump, a start engine, an ignition plug, a start spray nozzle and a sensor; the full-authority digital controller is respectively connected with the programmable power supply, the igniter, the start electromagnetic valve and the fuel pump; the programmable power supply is further connected with the start engine; the start engine is connected to the aero-engine; the igniter is connected with the aero-engine through the ignition plug; the start electromagnetic valve is connected with the aero-engine through the start spray nozzle; the fuel pump is arranged on the aero-engine and is driven by the same to rotate; and the sensor is connected with the aero-engine, and transmits signals to the full-authority digital controller. In the intelligent ground start system of the aero-engine, the engine starting process is optimal through the digital control of the full-authority digital controller to all the systems, so that the start impact current and the start impact temperature of the engine are effectively reduced, and the engine starting process is safe and reliable.
Description
Technical field
The utility model relates to a kind of aeroengine ground intelligent starting system, can make aeroengine realize the ground intelligent starting, belongs to aeroengine starting technique field.
Background technique
The aeroengine rotating speed is referred to as starting process by zero process that increases to the slow train rotating speed.Ground electricity starting comprises following process: drive engine rotor with starter motor and accelerate to fire speed; The indoor fuel-air mixture of ignition combustion; Turbine produces power; Starter motor and turbine drive engine rotor jointly and quicken; Starter motor is thrown off, and turbine drives rotor and accelerates to idling rating.Figure 1 shows that the engine start hydrograph: abscissa is the time, and y coordinate is an engine speed, wherein 1 expression blowdown firing; 2 expression oil spout igniting; 3 expression acceleration modes; 4 expression steady states.As can be seen from the figure, the line that starts to work of motor is very tortuous, and the working method of each constituent element is closely related in its reason and the starting system.
Usually aeroengine electricity starting system constitutes schematic representation as shown in Figure 2.During engine start by the starter box that is built-in with the time relay in chronological order controlling resistance formula power-supply controller of electric and igniter, play moving electromagnetic valve and the work of mechanical type fuel controller, the mechanical type fuel controller is simultaneously in chronological order to start oil circuit and working connection fuel feeding.The effect of resistance type power-supply controller of electric is to change the resistance value of D.C. regulated power supply to the actuating motor loop, thereby change the current value of input actuating motor, realize the step starting of motor, in the process of resistance conversion, there is very big inrush current when but the problem of this method maximum is starting, the engine gear transmission system is produced very big impulsive load.Can not change after resistance in this starting system time relay and the power-supply controller of electric configures, be unfavorable for realizing the optimization starting of aeroengine.And the resistance in the resistance controller is lower and claimed accuracy is high, and difficulty of processing is bigger.This starting system does not have signal feedbacks such as rotating speed, temperature, can't form closed loop control.
The model utility content
The purpose of this utility model is to provide a kind of aeroengine ground intelligent starting system, so that aeroengine ground start intellectuality, make starting process reach optimization, by using full powers limit digital controller to programmable power supply, igniter, playing moving electromagnetic valve and fuel pump controls, limit digital controller to the engine start fire speed by the sensor-lodging full powers, igniter firing time, parameters such as start oil circuit supply time and start oil circuit fuel delivery are adjusted, the engine start process is realized closed loop control, realize the engine start process optimizing, shorten the starting time, increase motor working life.By using programmable power supply to realize the motor stepless starting, make not have inrush current in the starting process, avoided of the impact of big load to the engine gear transmission system.
The technical solution of the utility model is: a kind of aeroengine ground intelligent starting system specifically comprises: full powers limit digital controller 1, programmable power supply 2, igniter 3, a moving electromagnetic valve 4, fuel pump 5, actuating motor 6, ignition electric nozzle 7, pilot jet 8 and sensor 9 etc.Wherein, sensor specifically comprises: speed probe, temperature transducer, pressure transducer.Wherein, full powers limit digital controller links to each other with programmable power supply, igniter, a moving electromagnetic valve and fuel pump respectively, and programmable power supply further connects moving motor, and actuating motor is connected to aeroengine; Igniter links to each other with aeroengine by ignition electric nozzle; Playing moving electromagnetic valve links to each other with aeroengine by pilot jet; Fuel pump is installed on the aeroengine and drives rotation by motor; Sensor links to each other with aeroengine, and signal is transferred to full powers limit digital controller.Wherein, sensor transmissions comprises to the signal of full powers limit digital controller: engine rotational speed signal, fuel gas temperature signal, engine charge pressure signal and Engine Inlet Temperature signal.
Full powers limit digital controller sends activating signal to programmable power supply, programmable power supply strengthens the voltage of input actuating motor gradually, voltage rising electric current increases, the actuating motor rotating speed speeds, actuating motor drives engine rotation makes engine speed steadily rise according to the speed of setting, and realizes the stepless starting of motor.Fuel pump is installed on the motor and drives rotation by motor.
The control of full powers limit digital controller is judged engine speed by signals of rotational speed sensor, after engine speed rises to fire speed, full powers limit digital controller sends signal to igniter, a moving electromagnetic valve, fuel pump, and igniter, a moving electromagnetic valve and fuel pump are started working.Fuel pump is to start oil circuit 10 fuel feeding, ignition electric nozzle sends electrical spark after the igniter work, playing moving electromagnetic valve opens fuel oil in the start oil circuit of back and flows into pilot jet by solenoid valve and spray to motor through after the nozzle atomization, ignited by ignition electric nozzle point spark and to form starting flame, fuel pump is to working connection 11 fuel feeding simultaneously, fuel oil enters motor 12 backs by working connection and is ignited by starting flame, full powers limit digital controller control fuel pump increases the working connection fuel delivery, make that engine speed continues to rise, realize the engine start process.
Signal of sensor real-time judge engine charge pressure and the intake temperature of full powers limit digital controller by installing on motor during engine start, parameter is determined the start oil circuit fuel delivery of fuel pump thus.Full powers limits digital controller real-time judge engine speed and fuel gas temperature in the engine start process, Variation fuel pump working connection fuel delivery thus, thereby control engine speed climbing speed and avoid fuel gas temperature to exceed allowed band.If too slow overshoot scope of engine speed rising or the too high overshoot scope of fuel gas temperature in the starting process, full powers limit digital controller can stop starting process.
After engine speed reached the slow train rotating speed, full powers limit digital and electronic control system was sent stop signal to programmable power supply, closes igniter simultaneously and plays moving electromagnetic valve, and motor enters steady-working state.Wherein, described full powers limit digital controller, selecting model for use is the SKX-1 digital controller.
A kind of aeroengine ground intelligent of the utility model starting system, its advantage is:
1, uses full powers limit digital controller that programmable power supply, igniter, a moving electromagnetic valve and fuel pump are controlled,, realized the intelligent and starting process optimization of aeroengine ground start the starting process closed loop control.
2, use programmable power supply to realize the motor stepless starting, avoid of the impact of heavy current impact load, thereby effectively improve engine health and reliability engine driving system.
3, make programmable power supply can regulate the power output rule of starting power supply as required, match, effectively reduce the engine start time with full powers limit digital controller.
4, reduce the starting system constituent elements, use digital controller, improved starting system reliability and accuracy.
Description of drawings
Figure 1 shows that engine start hydrograph schematic representation
Figure 2 shows that aviation engines ground electricity starting system schematic representation in the prior art
Figure 3 shows that the utility model aeroengine ground intelligent starting system schematic representation
Figure 4 shows that full powers limit digital controller software flow pattern
1, full powers limits digital controller 2, programmable power supply 3, igniter 4, rise moving electromagnetic valve 5, fuel pump 6, actuating motor 7, ignition electric nozzle 8, pilot jet 9, sensor 10,11,12,
Specific implementation
Below in conjunction with accompanying drawing, the technical solution of the utility model is described further.
Aeroengine ground intelligent starting system constitutes schematic representation as shown in Figure 3.
Aeroengine ground intelligent starting system comprises full powers limit digital controller 1, programmable power supply 2, igniter 3, plays moving electromagnetic valve 4, fuel pump 5, actuating motor 6, ignition electric nozzle 7, pilot jet 8 and sensor 9 etc.Wherein, sensor 9 specifically comprises: speed probe, temperature transducer, pressure transducer.Wherein, full powers limit digital controller links to each other with programmable power supply, igniter, a moving electromagnetic valve and fuel pump respectively, and programmable power supply further connects moving motor, and actuating motor is connected to aeroengine; Igniter links to each other with aeroengine by ignition electric nozzle; Playing moving electromagnetic valve links to each other with aeroengine 12 by pilot jet; Fuel pump is installed on the aeroengine and drives rotation by motor; Sensor links to each other with aeroengine, and signal is transferred to full powers limit digital controller.Wherein, sensor transmissions comprises to the signal of full powers limit digital controller: engine rotational speed signal, fuel gas temperature signal, engine charge pressure signal and Engine Inlet Temperature signal.
Aeroengine ground start process is by the control of full powers limit digital controller, full powers limit digital controller sends activating signal to programmable power supply during ground start, programmable power supply strengthens the voltage of input actuating motor gradually with the PWM voltage regulating mode, voltage rising electric current increases, the actuating motor rotating speed speeds, actuating motor drives engine rotation makes engine speed steadily rise according to the speed of setting, and realizes the stepless starting of motor.Fuel pump is installed on the motor and drives rotation by motor.
As shown in Figure 4, aeroengine ground intelligent starting system of the present utility model, its concrete working procedure is as follows: the control of full powers limit digital controller is judged engine speed by signals of rotational speed sensor, after engine speed rises to fire speed, full powers limit digital controller sends signal to igniter, a moving electromagnetic valve, fuel pump, and igniter, a moving electromagnetic valve and fuel pump are started working.Fuel pump is to the start oil circuit fuel feeding, ignition electric nozzle sends electrical spark after the igniter work, playing moving electromagnetic valve opens fuel oils in the back start oil circuit 10 and flows into pilot jet by solenoid valve and spray to motor through after the nozzle atomization, ignited by ignition electric nozzle point spark and to form starting flame, fuel pump is to working connection 11 fuel feeding simultaneously, fuel oil is ignited by starting flame after entering motor by working connection, full powers limit digital controller control fuel pump increases the working connection fuel delivery, make that engine speed continues to rise, realize the engine start process.
Signal of sensor real-time judge engine charge pressure and the intake temperature of full powers limit digital controller by installing on motor during engine start, parameter is determined the start oil circuit fuel delivery of fuel pump thus.Full powers limits digital controller real-time judge engine speed and fuel gas temperature in the engine start process, Variation fuel pump working connection fuel delivery thus, thereby control engine speed climbing speed and avoid fuel gas temperature to exceed allowed band.If too slow overshoot scope of engine speed rising or the too high overshoot scope of fuel gas temperature in the starting process, full powers limit digital controller can stop starting process.
After engine speed reached the slow train rotating speed, full powers limit digital and electronic control system was sent stop signal to programmable power supply, closes igniter simultaneously and plays moving electromagnetic valve, and motor enters steady-working state.
Claims (3)
1. aeroengine ground intelligent starting system, it is characterized in that: this starting system specifically comprises: full powers limit digital controller, programmable power supply, igniter, play moving electromagnetic valve, fuel pump, actuating motor, ignition electric nozzle, pilot jet and sensor; Wherein, full powers limit digital controller links to each other with programmable power supply, igniter, a moving electromagnetic valve and fuel pump respectively, and programmable power supply further connects moving motor, and actuating motor is connected to aeroengine; Igniter links to each other with aeroengine by ignition electric nozzle; Playing moving electromagnetic valve links to each other with aeroengine by pilot jet; Fuel pump is installed on the aeroengine and drives rotation by motor; Sensor links to each other with aeroengine, and signal is transferred to full powers limit digital controller.
2. aeroengine ground intelligent starting system according to claim 1, it is characterized in that: sensor specifically comprises: speed probe, temperature transducer, pressure transducer.
3. aeroengine ground intelligent starting system according to claim 1 is characterized in that: sensor transmissions comprises to the signal of full powers limit digital controller: engine rotational speed signal, fuel gas temperature signal, engine charge pressure signal and Engine Inlet Temperature signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200006279U CN201943863U (en) | 2011-01-04 | 2011-01-04 | Intelligent ground start system of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200006279U CN201943863U (en) | 2011-01-04 | 2011-01-04 | Intelligent ground start system of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201943863U true CN201943863U (en) | 2011-08-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200006279U Expired - Fee Related CN201943863U (en) | 2011-01-04 | 2011-01-04 | Intelligent ground start system of aero-engine |
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| Country | Link |
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| CN (1) | CN201943863U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094739A (en) * | 2011-01-04 | 2011-06-15 | 北京航空航天大学 | Ground intelligent starting system for aero-engine |
| CN103713531A (en) * | 2013-12-06 | 2014-04-09 | 长安大学 | Control system of throat area of aeroengine tail nozzle |
| CN111502832A (en) * | 2020-04-24 | 2020-08-07 | 中科航星科技有限公司 | Ground starting device of turbojet engine |
-
2011
- 2011-01-04 CN CN2011200006279U patent/CN201943863U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094739A (en) * | 2011-01-04 | 2011-06-15 | 北京航空航天大学 | Ground intelligent starting system for aero-engine |
| CN103713531A (en) * | 2013-12-06 | 2014-04-09 | 长安大学 | Control system of throat area of aeroengine tail nozzle |
| CN103713531B (en) * | 2013-12-06 | 2016-05-18 | 长安大学 | A kind of aero-engine jet pipe throat opening area control system |
| CN111502832A (en) * | 2020-04-24 | 2020-08-07 | 中科航星科技有限公司 | Ground starting device of turbojet engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110824 Termination date: 20140104 |