CN201925074U - Air start system of aircraft engine against air stalling - Google Patents
Air start system of aircraft engine against air stalling Download PDFInfo
- Publication number
- CN201925074U CN201925074U CN201120000537XU CN201120000537U CN201925074U CN 201925074 U CN201925074 U CN 201925074U CN 201120000537X U CN201120000537X U CN 201120000537XU CN 201120000537 U CN201120000537 U CN 201120000537U CN 201925074 U CN201925074 U CN 201925074U
- Authority
- CN
- China
- Prior art keywords
- aeroengine
- electromagnetic valve
- digital controller
- airstart
- igniter
- 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.)
- Expired - Fee Related
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Abstract
The utility model relates to an air start system of an aircraft engine against air stalling, which comprises a full authority digital controller, an igniter, a start electromagnetic valve, a fuel pump, an ignition plug, a start nozzle and a sensor. The full authority digital controller is connected with the igniter, the start electromagnetic valve and the fuel pump and then sends signals to the same, the fuel pump is connected with the start electromagnetic valve via a start fuel channel, and is connected with an aircraft engine via a main fuel channel, the start electromagnetic valve is further connected with the start nozzle further, the start nozzle is connected with the aircraft engine simultaneously, the igniter is further connected with the ignition plug which is connected with the aircraft engine simultaneously, and the sensor is connected with the aircraft engine and transmits signals to the full authority digital controller. The air start system has the advantages of monitoring actively, enhancing timeliness of control, increasing the success rate of air start of the engine, strengthening safety and reliability of the airplane and adapting to high-altitude unmanned aerial vehicles.
Description
Technical field
The utility model relates to a kind of aeroengine experience and starts the airstart system, is specifically related to a kind of experience that makes the flame-out back of aeroengine realize promptly putting out promptly in the air and starts airstart, belongs 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 utility model has solved the problems referred to above, makes that starting process is carried out automatically in the engine air, has guaranteed the success rate of motor in high height airstart, has improved the Security and the reliability of aircraft to a great extent.
The model utility content
The purpose of this utility model 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 utility model 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 utility model 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 utility model 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 utility model 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 the utility model aeroengine meets with starting airstart system schematic.
Figure 2 shows that the utility model full powers limit digital controller meets with the starting software flow pattern.
Concrete label is as follows among the figure: 1, authority digital controller 2, igniter 3, a moving electromagnetic valve
4, fuel pump 5, ignition electric nozzle 6, pilot jet 7, sensor 8, start oil circuit
9, working connection 10, aeroengine.
Embodiment
Below in conjunction with accompanying drawing, the technical solution of the utility model is described further.
As shown in Figure 1, a kind of aeroengine of the utility model meets with starting airstart system, comprises full powers limit digital controller 1, igniter 2, plays moving electromagnetic valve 3, fuel pump 4, ignition electric nozzle 5, pilot jet 6 and sensor 7 (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 utility model meets with starting airstart system, its airstart process is as follows: full powers limit digital controller sends signal to igniter 1, a moving electromagnetic valve 3, fuel pump 4, and igniter 2, a moving electromagnetic valve 3 and fuel pump 4 are started working.Fuel pump 4 is to start oil circuit 8 fuel feeding, igniter 2 work back ignition electric nozzles 5 send electrical spark, playing moving electromagnetic valve 3 opens fuel oils in the back start oil circuit 8 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 4 is to working connection 9 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 motor 10 rotating speeds continue 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; 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 |
|---|---|---|---|
| CN201120000537XU CN201925074U (en) | 2011-01-04 | 2011-01-04 | Air start system of aircraft engine against air stalling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120000537XU CN201925074U (en) | 2011-01-04 | 2011-01-04 | Air start system of aircraft engine against air stalling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201925074U true CN201925074U (en) | 2011-08-10 |
Family
ID=44428926
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120000537XU Expired - Fee Related CN201925074U (en) | 2011-01-04 | 2011-01-04 | Air start system of aircraft engine against air stalling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201925074U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10598095B2 (en) | 2016-10-11 | 2020-03-24 | Unison Industries, Llc | Integrated starter for aerial vehicle |
-
2011
- 2011-01-04 CN CN201120000537XU patent/CN201925074U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10598095B2 (en) | 2016-10-11 | 2020-03-24 | Unison Industries, Llc | Integrated starter for aerial vehicle |
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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: 20110810 Termination date: 20140104 |