CN102072063A - Encounter-starting airstart system of aircraft engine - Google Patents
Encounter-starting airstart system of aircraft engine Download PDFInfo
- Publication number
- CN102072063A CN102072063A CN2011100003203A CN201110000320A CN102072063A CN 102072063 A CN102072063 A CN 102072063A CN 2011100003203 A CN2011100003203 A CN 2011100003203A CN 201110000320 A CN201110000320 A CN 201110000320A CN 102072063 A CN102072063 A CN 102072063A
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- airstart
- aeroengine
- digital controller
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- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention relates to an encounter-starting airstart system of an aircraft engine, specifically comprising a full-authority digital controller, an igniter, a starting solenoid valve, a fuel pump, an igniter plug, a starting nozzle and a sensor, wherein the full-authority digital controller is connected with the igniter, the starting solenoid valve and the fuel pump to send a signal thereto; the fuel pump is connected with the starting solenoid valve via a starting fuel line and is simultaneously connected with the aircraft engine via a main fuel line; the starting solenoid valve is further connected with the starting nozzle connected with the aircraft engine; the igniter is further connected with the igniter plug connected with the aircraft engine; and the sensor is connected with the aircraft engine and sends the signal to the full-authority digital controller. The encounter-starting airstart system has the advantages of actively monitoring to strengthen control timeliness, improving the success rate for the airstart of the engine, increasing the safety and the reliability of an airplane and being favourable to use unmanned aerial vehicles.
Description
Technical field
The present invention relates to a kind of aeroengine experience and start the airstart system, be specifically related to a kind of experience that makes the flame-out back of aeroengine realize promptly putting out promptly in the air and start airstart, belong to aeroengine airstart technical field.
Background technique
Aeroengine airstart is designed to guarantee that aircraft flight safety plays an important role.Usually aeroengine adopts the mechanical type fuel controller, the flame-out need judged according to engine parameter by pilot or ground controller in the engine air, after stopping working in the judgement engine air, assign the airstart instruction by pilot or ground controller, this moment, engine speed and internal engine temperature reduced a lot, and this process need long period.
The invention solves the problems referred to above, make that starting process is carried out automatically in the engine air, guaranteed the success rate of motor, improved the Security and the reliability of aircraft to a great extent in high height airstart.
Summary of the invention
[0003] the object of the present invention is to provide a kind of aeroengine to meet with starting airstart system, so that starting process is carried out automatically in the engine air.
A kind of aeroengine of the present invention meets with starting airstart system, it is by motor full powers limit digital controller, after the monitoring of engine combustion room temperature is found that the firing chamber is flame-out, oil supply system controlled immediately by digital controller and ignition system carries out motor airstart, guaranteed the success rate of motor, improved the Security and the reliability of aircraft to a great extent in high height airstart.The experience that the present invention uses full powers to limit digital controller to realize that aeroengine is promptly put out is promptly started the airstart working method, guarantees the success rate of motor airstart.
A kind of aeroengine of the present invention meets with starting airstart system, and technological scheme is: this starting system specifically comprises: full powers limit digital controller, igniter, a moving electromagnetic valve, fuel pump, ignition electric nozzle, pilot jet and sensor etc.Wherein, sensor specifically comprises: speed probe, temperature transducer, pressure transducer.Wherein, full powers limit digital controller is connected with igniter, a moving electromagnetic valve and fuel pump, sends signal to it; Fuel pump is connected with a moving electromagnetic valve by start oil circuit, is connected with aeroengine by working connection simultaneously; Play moving electromagnetic valve and further be connected with pilot jet, pilot jet connects aeroengine simultaneously; Igniter further is connected with ignition electric nozzle, and ignition electric nozzle connects aeroengine simultaneously; Sensor is connected 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.
Wherein, described full powers limit digital controller, selecting model for use is the SKX-1 digital controller.
A kind of aeroengine of the present invention meets with starting airstart system, and its advantage is: (1) is monitoring initiatively, has strengthened the ageing of control; (2) improve the success rate of motor airstart, increased the Security and the reliability of aircraft; (3) help the use of high-altitude unmanned plane.
Description of drawings
Figure 1 shows that aeroengine of the present invention meets with starting airstart system schematic.
Figure 2 shows that full powers limit digital controller of the present invention meets with the starting software flow pattern.
Embodiment
Below in conjunction with accompanying drawing, technological scheme of the present invention is described further.
As shown in Figure 1, a kind of aeroengine of the present invention meets with starting airstart system, comprises full powers limit digital controller, igniter, plays moving electromagnetic valve, fuel pump, ignition electric nozzle, pilot jet and rotating speed, temperature, pressure transducer etc.
Aeroengine meets with starting airstart process by the control of full powers limit digital controller, and selecting model for use is the SKX-1 digital controller.Digital controller is according to after flame-out in fuel gas temperature sensor signal and the engine speed judgement engine air, and digital controller is carried out the airstart program immediately.
As shown in Figure 2, a kind of aeroengine of the present invention meets with starting airstart system, its airstart process is as follows: 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 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 the working connection 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 limits digital controller by installing on motor during motor airstart, start oil circuit fuel delivery when parameter is determined the airstart 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.
Aeroengine meets with the starting air starting method and has utilized the interior surplus temperature of the just flame-out after-burner of motor, make aircraft keep higher flying height, engine chamber carries out motor airstart more smoothly when keeping higher temperature, improve the success rate of motor airstart.
Claims (3)
1. an aeroengine meets with starting airstart system, and it is characterized in that: this starting system specifically comprises: full powers limit digital controller, igniter, a moving electromagnetic valve, fuel pump, ignition electric nozzle, pilot jet and sensor; Wherein, full powers limit digital controller is connected with igniter, a moving electromagnetic valve and fuel pump, sends signal to it; Fuel pump is connected with a moving electromagnetic valve by start oil circuit, is connected with aeroengine by working connection simultaneously; Play moving electromagnetic valve and further be connected with pilot jet, pilot jet connects aeroengine simultaneously; Igniter further is connected with ignition electric nozzle, and ignition electric nozzle connects aeroengine simultaneously; Sensor is connected with aeroengine, and signal is transferred to full powers limit digital controller.
2. aeroengine according to claim 1 meets with starting airstart system, and it is characterized in that: described sensor specifically comprises: speed probe, temperature transducer, pressure transducer.
3. aeroengine according to claim 1 meets with starting airstart system, it 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 |
|---|---|---|---|
| CN2011100003203A CN102072063A (en) | 2011-01-04 | 2011-01-04 | Encounter-starting airstart system of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100003203A CN102072063A (en) | 2011-01-04 | 2011-01-04 | Encounter-starting airstart system of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102072063A true CN102072063A (en) | 2011-05-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100003203A Pending CN102072063A (en) | 2011-01-04 | 2011-01-04 | Encounter-starting airstart system of aircraft engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN102072063A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043715A (en) * | 2016-05-27 | 2016-10-26 | 襄阳宏伟航空器有限责任公司 | In-flight auto-ignition control method of engine of unmanned aerial vehicle |
| 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 |
Citations (5)
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| US20060137357A1 (en) * | 2004-12-23 | 2006-06-29 | Kudrna Richard R | Variable rate ignition |
| US20070234734A1 (en) * | 2004-11-23 | 2007-10-11 | Honeywell International, Inc. | System and method for turbine engine startup profile characterization |
| CN101392689A (en) * | 2008-11-05 | 2009-03-25 | 北京航空航天大学 | Control device of microminiature turbojet and starting control method thereof |
| CN101713970A (en) * | 2008-09-30 | 2010-05-26 | 通用电气公司 | Method and systems for restarting a flight control system |
| CN101806251A (en) * | 2010-03-25 | 2010-08-18 | 北京航空航天大学 | Starting control device of micro gas turbine and starting control method |
-
2011
- 2011-01-04 CN CN2011100003203A patent/CN102072063A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070234734A1 (en) * | 2004-11-23 | 2007-10-11 | Honeywell International, Inc. | System and method for turbine engine startup profile characterization |
| US20060137357A1 (en) * | 2004-12-23 | 2006-06-29 | Kudrna Richard R | Variable rate ignition |
| CN101713970A (en) * | 2008-09-30 | 2010-05-26 | 通用电气公司 | Method and systems for restarting a flight control system |
| CN101392689A (en) * | 2008-11-05 | 2009-03-25 | 北京航空航天大学 | Control device of microminiature turbojet and starting control method thereof |
| CN101806251A (en) * | 2010-03-25 | 2010-08-18 | 北京航空航天大学 | Starting control device of micro gas turbine and starting control method |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043715A (en) * | 2016-05-27 | 2016-10-26 | 襄阳宏伟航空器有限责任公司 | In-flight auto-ignition control method of engine of unmanned aerial vehicle |
| CN106043715B (en) * | 2016-05-27 | 2018-03-27 | 襄阳宏伟航空器有限责任公司 | A kind of aerial method for controlling automatic ignition of unmanned vehicle engine |
| 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 |
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Application publication date: 20110525 |