CN213870043U - Ignition accessory of aircraft engine - Google Patents
Ignition accessory of aircraft engine Download PDFInfo
- Publication number
- CN213870043U CN213870043U CN202023278942.6U CN202023278942U CN213870043U CN 213870043 U CN213870043 U CN 213870043U CN 202023278942 U CN202023278942 U CN 202023278942U CN 213870043 U CN213870043 U CN 213870043U
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- heating core
- flame
- aircraft engine
- evaporation cavity
- ignition
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Abstract
The utility model relates to an aeroengine ignition annex, include: the heating core is coaxially arranged in the cylinder shell in a penetrating way, and the heating core and the cylinder shell form an evaporation cavity; the fuel oil inlet pipe is arranged at one end of the evaporation cavity, and the other end of the evaporation cavity and the heating core form a flame outlet; the heating core is connected with a power line, and generates heat after being electrified to enable the fuel in the evaporation cavity to form steam to be ignited, and the ignited fuel forms flame to be sprayed out from the flame outlet. The utility model discloses the beneficial effect who reaches is: the electronic device is not interfered, and is not easy to extinguish, high in reliability and light in weight.
Description
Technical Field
The utility model relates to a wash technical field, especially an aeroengine ignition annex.
Background
The ignition device of the aircraft engine is mainly the same as the ignition mode of a household gas stove, such as HB 7783-.
The aircraft engine adopts a high-pressure ignition mode (also called an electronic ignition mode), ignition needs enough energy, and the conditions that the electronic equipment is greatly interfered by the ignition moment and is difficult to ignite exist.
In order to achieve ignition, a complex ignition (discharge) circuit must be designed independently, both capacitive and inductive ignition modes have the defect of large volume (capacitive ignition energy is in direct proportion to capacitance, larger energy requires a capacitor with larger volume and weight, and a heavier step-up transformer is also needed), inductive high-voltage discharge voltage is in direct proportion to energy, voltage needs to be increased, larger current at the moment of discharge is guaranteed, thicker enameled wires are needed to be wound for a plurality of turns, the volume is large, and the weight of an engine is increased.
When in ignition, the fuel can be ignited under enough nozzle fuel pressure, the position requirement of an igniter is very high, and the electronic spark ignition can be ignited only under the condition of relatively high oil-gas ratio precision. In addition, the ignition time is intermittent ignition, heat cannot be sustained, and a flameout phenomenon is easily generated under high-speed airflow in the combustion chamber after ignition. After the engine is shut down at high altitudes, a challenge is presented for reignition.
This company designs a novel ignition annex to aeroengine, becomes the mode of striking sparks that generates heat with the electron strike sparks, not only can avoid high-voltage pulse to electronic equipment's interference, is difficult for flame-out moreover, and stability is high, light in weight simultaneously.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art's shortcoming, provide an aeroengine ignition annex that does not cause the interference to electronic equipment, is difficult for putting out a fire, the reliability is high, light in weight.
The purpose of the utility model is realized through the following technical scheme: an aircraft engine ignition accessory comprising:
the heating core is coaxially arranged in the cylinder shell in a penetrating way, and the heating core and the cylinder shell form an evaporation cavity;
the fuel oil inlet pipe is arranged at one end of the evaporation cavity, and the other end of the evaporation cavity and the heating core form a flame outlet;
the heating core is connected with a power line, and generates heat after being electrified to enable the fuel in the evaporation cavity to form steam to be ignited, and the ignited fuel forms flame to be sprayed out from the flame outlet.
Furthermore, an air input pipe is arranged at one end of the fuel oil inlet pipe of the evaporation cavity. After the air input by the air input pipe is mixed with the fuel oil inlet pipe, stable flame can be provided.
Furthermore, one end of the cylinder shell is a closed end, the other end of the cylinder shell is a flame opening end, the fuel oil inlet pipe and the air input pipe are both arranged at the closed end, and the heating core extends out of the flame opening end.
Preferably, the aperture of the flame hole is gradually reduced from inside to outside. The flame is allowed to concentrate at the central jet, forming a concentrated flame beam.
Preferably, the heating core in the evaporation cavity is sleeved with a flood dragon blade, and the heating core and the flood dragon blade are flood dragon shafts. Allowing the air to mix thoroughly with the fuel.
Further, the aircraft engine ignition accessory is installed on a flame tube of the aircraft engine and is arranged close to the nozzle. Preferably, an aircraft engine ignition accessory is provided on the flame tube of the aircraft engine, which, when one nozzle is ignited, ignites the full-circle nozzle. That is, after one nozzle is ignited, the full ring is directly ignited through series combustion.
The utility model has the advantages of it is following:
(1) by utilizing the heating core, the fuel oil is evaporated and then ignited, and finally generated flame ignites the nozzle, so that compared with electronic ignition, instantaneous high-voltage discharge cannot be generated, and interference on electronic equipment cannot be caused; meanwhile, the voltage of a power supply required by the heating core is low, and a boosting device is not needed; the safety of the scheme is greatly improved;
(2) by arranging the air input pipe, fuel oil is mixed with air, the formed laminar combustion flame is very stable and is not easy to extinguish, the engine can be effectively prevented from extinguishing in the air, and the safety is further improved;
(3) the arrangement that the caliber of the flame hole is gradually reduced is beneficial to forming flame beams and ignition; the setting of flood dragon blade lets air and fuel intensive mixing, and the intensive heating.
Drawings
FIG. 1 is a schematic view of the present invention mounted on an engine flame tube;
FIG. 2 is a schematic structural view of the present invention;
in the figure: 1-heating core, 2-evaporation cavity, 3-fuel oil inlet pipe, 4-air input pipe and 5-power line.
Detailed Description
The invention will be further described with reference to the accompanying drawings, but the scope of the invention is not limited to the following description.
As shown in fig. 1, an aircraft engine ignition accessory is mounted on a flame tube of an aircraft engine and is arranged close to a nozzle; and an aircraft engine ignition accessory is arranged on a flame tube of the aircraft engine, and can ignite the full-ring nozzle after one nozzle is ignited. That is, after one nozzle is ignited, the full ring is directly ignited through series combustion.
In this scheme, as shown in fig. 2: comprises a heating core 1, a fuel oil inlet pipe 3 and a cylinder shell. Wherein, the heating core 1 is coaxially arranged in the cylinder shell in a penetrating way, and the heating core and the cylinder shell form an evaporation cavity 2; and the fuel oil inlet pipe 3 is arranged at one end of the evaporation cavity 2, the other end of the evaporation cavity 2 and the heating core 1 form a flame outlet, and the heating core 1 is also connected with the power line 5.
An air input pipe 4 is also arranged at the cylinder shell of the fuel oil inlet pipe 3.
During operation, power cord 5 is for generating heat core 1 circular telegram, can the flash evaporation partly fuel in evaporation chamber 2, high temperature generates heat the continuous heating of core and ignites down, becomes laminar flow combustion flame, laminar flow combustion flame is unstable, extinguishes very easily (just blowing out as if ordinary lighter), and advances the opposite side of oil pipe 3 at the fuel and let in the air and premix the boil-off gas of fuel, the flame after premixing is very stable, the oil gas after premixing can not blown out after generating heat core 1 and lighting, can realize reliable ignition.
It should be noted that the oil pipe is of great importance during the working process, the requirement of the ignition oil-gas ratio is very low, and the ignition reliability is better.
Preferably, the heating core 1 in the scheme is packaged by ceramic materials such as silicon nitride and the like, so that the durability of the heating core is ensured, and the temperature resistance of the heating core can reach 1400 ℃; it reaches a high temperature of over 400 degrees in a few seconds (it can reach bright red color in a few seconds), igniting the fuel. The fuel in the scheme is preferably aviation kerosene.
Preferably, the core of the power line 5 is made of copper, and the outer layer is made of high-temperature-resistant insulating material. And the cylinder shell of the evaporation cavity 2 is made of conductive metal and is connected with a power supply negative electrode, and the power supply negative electrode directly forms a current loop with the heating core through the cylinder shell.
In this embodiment, one end of the cylindrical shell is a closed end, the other end of the cylindrical shell is a flame opening end, the fuel inlet pipe 3 and the air inlet pipe 4 are both arranged at the closed end, and the heating core 1 extends out of the flame opening end.
In this embodiment, the aperture of the flame hole gradually decreases from inside to outside. The flame is allowed to concentrate at the central jet, forming a concentrated flame beam.
In this embodiment, the cover is equipped with the flood dragon blade on the core 1 that generates heat in the evaporation chamber 2, and the core 1 that generates heat and flood dragon blade are flood dragon axle form. Allowing the air to mix thoroughly with the fuel.
In addition, when the ignition accessory of the aero-engine is installed, the heating core 1 needs to be inserted into the flame tube.
The ignition step is as follows: firstly, a starting motor drives an engine to reach an ignition rotating speed, at the moment, gas with a certain flow velocity exists in an air input pipe of an ignition accessory of the aero-engine, an ignition nozzle of the engine and a fuel oil inlet pipe 3 supply oil simultaneously, the oil of the nozzle is ignited by igniting the oil of the fuel oil inlet pipe 2, an ignition switch of the ignition accessory of the aero-engine is closed, and the ignition is finished.
The above examples only represent preferred embodiments, and the description thereof is more specific and detailed, but not to be construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention.
Claims (6)
1. An aircraft engine ignition accessory, characterized by: the method comprises the following steps:
the heating core (1) is coaxially arranged in the cylinder shell in a penetrating way, and the heating core and the cylinder shell form an evaporation cavity (2);
the fuel oil inlet pipe (3) is arranged at one end of the evaporation cavity (2), and the other end of the evaporation cavity (2) and the heating core (1) form a flame outlet;
the heating core (1) is connected with a power line (5), and after the heating core is electrified, the heating core generates heat to enable fuel in the evaporation cavity (2) to form steam to be ignited, and the ignited fuel forms flame to be sprayed out from a flame outlet.
2. An aircraft engine ignition accessory according to claim 1, wherein: and an air input pipe (4) is also arranged at one end of the fuel oil inlet pipe (3) of the evaporation cavity (2).
3. An aircraft engine ignition accessory according to claim 2, wherein: one end of the cylinder shell is a closed end, the other end of the cylinder shell is a flame opening end, the fuel oil inlet pipe (3) and the air input pipe (4) are both arranged at the closed end, and the heating core (1) extends out of the flame opening end.
4. An aircraft engine ignition accessory according to claim 3, wherein: the caliber of the flame hole is gradually reduced from inside to outside.
5. An aircraft engine ignition accessory according to claim 4, wherein: the evaporation chamber (2) in generate heat core (1) on the cover be equipped with flood dragon blade, generate heat core (1) and flood dragon blade are flood dragon axle form.
6. An aircraft engine ignition accessory according to claim 4 or 5, wherein: the aircraft engine ignition accessory is installed on a flame tube of the aircraft engine and is arranged close to the nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023278942.6U CN213870043U (en) | 2020-12-31 | 2020-12-31 | Ignition accessory of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023278942.6U CN213870043U (en) | 2020-12-31 | 2020-12-31 | Ignition accessory of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213870043U true CN213870043U (en) | 2021-08-03 |
Family
ID=77045029
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023278942.6U Active CN213870043U (en) | 2020-12-31 | 2020-12-31 | Ignition accessory of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213870043U (en) |
-
2020
- 2020-12-31 CN CN202023278942.6U patent/CN213870043U/en active Active
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