CN213743698U - Aircraft engine ignition structure with atomizing nozzle - Google Patents
Aircraft engine ignition structure with atomizing nozzle Download PDFInfo
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- CN213743698U CN213743698U CN202022976715.4U CN202022976715U CN213743698U CN 213743698 U CN213743698 U CN 213743698U CN 202022976715 U CN202022976715 U CN 202022976715U CN 213743698 U CN213743698 U CN 213743698U
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- ignition
- oil pipe
- combustion chamber
- atomizer
- nozzle
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 51
- 230000005611 electricity Effects 0.000 claims abstract description 6
- 239000000523 sample Substances 0.000 claims description 20
- 230000006698 induction Effects 0.000 claims description 12
- 238000010438 heat treatment Methods 0.000 claims 1
- 239000000446 fuel Substances 0.000 abstract description 18
- 239000003921 oil Substances 0.000 description 46
- 230000001939 inductive effect Effects 0.000 description 8
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 239000002912 waste gas Substances 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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Abstract
The utility model relates to an engine ignition equipment technical field provides a take atomizer's aircraft engine ignition structure, including the combustion chamber, main oil pipe and ignition, main oil pipe and the inside intercommunication of combustion chamber, ignition is including ignition oil pipe, ignition head, ignition oil pipe and oil pump intercommunication, and inside ignition oil pipe's nozzle and the execution end of ignition head all stretched into the combustion chamber, the execution end accomplished the ignition with the nozzle cooperation, and ignition oil pipe shaft is connected with the solenoid valve, and atomizer is add to the nozzle, and atomizer is connected with the solenoid valve electricity. Through the technical scheme, the problems that fuel pressure is unstable and ignition success rate is unstable in the prior art, ignition time is wasted, and flameout of an engine can be caused are solved.
Description
Technical Field
The utility model relates to an engine ignition equipment technical field, it is specific, relate to a take atomizer's aircraft engine ignition structure.
Background
The combustion chamber is one of the core main components of the micro turbojet engine, is equivalent to the heart of the engine, and the combustion quality of the combustion chamber directly influences the performance level of the engine, so that the ignition structure of the combustion chamber is important; however, at present, most of ignition modes are that an oil pipe and a fire head directly touch the head for ignition, so that the defects of unstable fuel pressure and unstable ignition success rate exist, the ignition time is wasted, and the phenomenon of flameout of an engine can be caused; therefore, an ignition structure capable of improving the ignition success rate and stability is needed at present, and aiming at the problems, the prior art does not well solve the problems and brings troubles to the normal operation of the field.
SUMMERY OF THE UTILITY MODEL
The utility model provides a take atomizer's aircraft engine ignition structure has solved the fuel pressure instability in the correlation technique, and the shortcoming of ignition success rate is unstable, has wasted the ignition time, still can lead to the flameout problem of engine.
The technical scheme of the utility model as follows: the utility model provides a take atomizer's aircraft engine ignition structure, includes the combustion chamber, main oil pipe and ignition, main oil pipe with the inside intercommunication of combustion chamber, ignition includes ignition oil pipe, ignition head, ignition oil pipe and oil pump intercommunication, ignition oil pipe's nozzle with the execution end of ignition head all stretches into inside the combustion chamber, the execution end with the nozzle cooperation is accomplished and is igniteed, ignition oil pipe shaft is connected with the solenoid valve, atomizer is add to the nozzle, atomizer with the solenoid valve electricity is connected.
As a further technical scheme, the ignition device further comprises an adjusting mechanism, wherein the adjusting mechanism comprises an induction probe and a controller, the induction probe is electrically connected with the controller, the controller is arranged on the ignition oil pipe body, and the induction probe extends into the combustion chamber.
As a further technical scheme, a group of preheating pipes are vertically arranged in the combustion chamber in an array mode.
As a further technical scheme, the outer wall of the combustion chamber is provided with a round hole.
The utility model discloses a theory of operation does: the ignition oil pipe is communicated with the oil pump, the atomizing nozzle is additionally arranged at the oil injection port and is connected to the electromagnetic valve, the electromagnetic valve controls oil supply of the oil pump, when the motor starts ignition, the oil pump supplies oil, the oil is atomized and sprayed into the combustion chamber through the atomizing nozzle and is fully combusted near the execution end of the ignition head, the atomized fuel can quickly form flame to raise the temperature, and the fuel pressure is stabilized, so that the engine can be ignited more quickly and easily, and the power consumption and the ignition time are reduced; the ignition device is characterized by further comprising an adjusting mechanism, the adjusting mechanism comprises an induction probe and a controller, the induction probe is electrically connected with the controller, the controller is arranged on the ignition oil pipe body, the induction probe extends into the combustion chamber, the induction probe can sense the temperature in the combustion chamber at any time and transmit signals to the controller, the controller receives feedback temperature signals of the induction probe and controls the temperature in the combustion chamber by automatically adjusting the atomized fuel injection quantity; a group of preheating pipes are vertically arranged in the combustion chamber in an array manner, the interior of the combustion chamber is preheated before ignition, and fuel oil sprayed into an engine is preheated to realize combustion with higher efficiency; the outer wall of the combustion chamber is provided with a round hole for discharging waste gas generated after the fuel is combusted, so that the circulation of air is ensured, and the fuel is fully combusted.
The utility model has the advantages that: through the atomizer that the nozzle was add, can form flame fast and make the temperature rise, stabilized fuel pressure, the engine ignition is quick and easy more from this, has reduced the ignition power consumption and time.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
FIG. 1 is a schematic view of the ignition structure of the present invention;
FIG. 2 is a view showing the internal structure of the combustion chamber of the present invention;
FIG. 3 is a top view of the combustion chamber of the present invention;
FIG. 4 is an isometric view of the combustion chamber of the present invention;
FIG. 5 is a schematic diagram of the distribution of the preheating tubes of the present invention;
in the figure:
1. the device comprises a combustion chamber, 2, a main oil pipe, 3, an ignition oil pipe, 4, an ignition head, 5, an oil pump, 6, an electromagnetic valve, 7, an atomization nozzle, 8, an induction probe, 9, a controller, 10, a preheating pipe, 11 and a circular hole.
Detailed Description
The utility model provides a take atomizer's aircraft engine ignition structure, includes combustion chamber 1, main oil pipe 2 and ignition, main oil pipe 2 with 1 inside intercommunication in combustion chamber, ignition includes ignition oil pipe 3, ignition head 4, ignition oil pipe 3 and oil pump 5 intercommunication, ignition oil pipe 3's nozzle with the execution end of ignition head 4 all stretches into 1 inside the combustion chamber, the execution end with the ignition is accomplished in the nozzle cooperation, 3 shafts of ignition oil pipe are connected with solenoid valve 6, atomizer 7 is add to the nozzle, atomizer 7 with solenoid valve 6 electricity is connected.
The technical solutions in the embodiments of the present invention will be described clearly and completely below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive work, are related to the scope of the present invention.
As shown in fig. 1 to 5, this embodiment provides an aircraft engine ignition structure with an atomizer, including a combustion chamber 1, a main oil pipe 2 and an ignition device, the main oil pipe 2 is communicated with the inside of the combustion chamber 1, the ignition device includes an ignition oil pipe 3 and an ignition head 4, the ignition oil pipe 3 is communicated with an oil pump 5, an oil jet of the ignition oil pipe 3 and an execution end of the ignition head 4 both extend into the inside of the combustion chamber 1, the execution end is matched with the oil jet to complete ignition, a pipe body of the ignition oil pipe 3 is connected with an electromagnetic valve 6, the atomizer 7 is additionally arranged at the oil jet, and the atomizer 7 is electrically connected with the electromagnetic valve 6.
In this embodiment, main oil pipe 2 and the inside intercommunication of combustion chamber 1, be used for providing the fuel for combustion chamber 1 after the ignition, the nozzle of ignition oil pipe 3 and the execution end of ignition head 4 all stretch into combustion chamber 1 inside and both corresponding settings, ignition oil pipe 3 and oil pump 5 intercommunication, atomizer 7 has been add in nozzle department, atomizer 7 is connected to solenoid valve 6, solenoid valve 6 control oil pump 5 fuel feeding, when the motor starts the ignition, oil pump 5 fuel feeding, fluid sprays into combustion chamber 1 through atomizer 7 atomizing, fully burn near the execution end of ignition head 4, can form flame fast through the fuel of atomizing and make the temperature rise, fuel pressure has been stabilized, it is more quick and easy to ignite by this engine, the power consumption and the time of igniting have been reduced.
As shown in fig. 1, further, it also includes,
still include adjustment mechanism, adjustment mechanism includes inductive probe 8 and controller 9, inductive probe 8 with controller 9 electricity is connected, 3 pipe shafts of ignition oil pipe are located to controller 9, inductive probe 8 stretches into inside the combustion chamber 1.
In this embodiment, still include adjustment mechanism, adjustment mechanism includes inductive probe 8 and controller 9, inductive probe 8 with controller 9 electricity is connected, and 3 pipe shafts on the ignition oil pipe are located to controller 9, and inductive probe 8 stretches into inside the combustion chamber 1, inductive probe 8 can perceive the temperature in the combustion chamber 1 at any time to give controller 9 with signal transmission, controller 9 receives inductive probe 8's feedback temperature signal, controls the temperature in the combustion chamber 1 through automatically regulated atomizing fuel injection quantity.
As shown in fig. 2, 4 and 5, further, it also includes,
a group of preheating pipes 10 are vertically arranged in the combustion chamber 1 in an array manner.
In this embodiment, a group of preheating pipes 10 is vertically arranged in the combustion chamber 1 in an array manner, and the interior of the combustion chamber 1 is preheated before ignition, so that fuel injected into the engine is preheated, and combustion with higher efficiency is achieved.
As shown in fig. 1 to 2 and 4, further, it includes,
the outer wall of the combustion chamber 1 is provided with a round hole 11.
In this embodiment, the outer wall of the combustion chamber 1 is provided with a circular hole 11 for discharging the waste gas generated after the fuel is combusted, so as to ensure the circulation of air and fully combust the fuel.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The utility model provides a take atomizer's aircraft engine ignition structure, includes combustion chamber (1), main oil pipe (2) and ignition, main oil pipe (2) with the inside intercommunication of combustion chamber (1), ignition includes ignition oil pipe (3), ignition head (4), ignition oil pipe (3) and oil pump (5) intercommunication, the nozzle of ignition oil pipe (3) with the execution end of ignition head (4) all stretches into inside combustion chamber (1), the execution end with the nozzle cooperation is accomplished and is igniteed, a serial communication port, ignition oil pipe (3) shaft is connected with solenoid valve (6), nozzle addes atomizer (7), atomizer (7) with solenoid valve (6) electricity is connected.
2. The aircraft engine ignition structure with the atomizer according to claim 1, further comprising an adjustment mechanism, wherein the adjustment mechanism comprises an induction probe (8) and a controller (9), the induction probe (8) is electrically connected to the controller (9), the controller (9) is disposed on a tube body of the ignition oil tube (3), and the induction probe (8) extends into the combustion chamber (1).
3. Aircraft engine ignition structure with atomising nozzles as in claim 1, characterised by the fact that a series of pre-heating tubes (10) are erected in the combustion chamber (1).
4. Aircraft engine ignition structure with atomising nozzle according to claim 1 characterised in that the outer wall of the combustion chamber (1) is provided with a circular hole (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022976715.4U CN213743698U (en) | 2020-12-08 | 2020-12-08 | Aircraft engine ignition structure with atomizing nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022976715.4U CN213743698U (en) | 2020-12-08 | 2020-12-08 | Aircraft engine ignition structure with atomizing nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213743698U true CN213743698U (en) | 2021-07-20 |
Family
ID=76834428
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022976715.4U Active CN213743698U (en) | 2020-12-08 | 2020-12-08 | Aircraft engine ignition structure with atomizing nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213743698U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493162A (en) * | 2022-09-13 | 2022-12-20 | 保定市玄云涡喷动力设备研发有限公司 | Ignition device of engine |
-
2020
- 2020-12-08 CN CN202022976715.4U patent/CN213743698U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115493162A (en) * | 2022-09-13 | 2022-12-20 | 保定市玄云涡喷动力设备研发有限公司 | Ignition device of engine |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 66 Jianye East Road, Gaokai District, Baoding City, Hebei Province, 071000 Patentee after: BAODING XUANYUN TURBOJET POWER EQUIPMENT R&D CO.,LTD. Country or region after: China Address before: Block a, building 3, Zhongguancun innovation base, No. 369, Huiyang street, Baoding City, Hebei Province, 071000 Patentee before: BAODING XUANYUN TURBOJET POWER EQUIPMENT R&D CO.,LTD. Country or region before: China |