CN112963249A - High-energy igniter for aviation - Google Patents
High-energy igniter for aviation Download PDFInfo
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- CN112963249A CN112963249A CN202110134755.0A CN202110134755A CN112963249A CN 112963249 A CN112963249 A CN 112963249A CN 202110134755 A CN202110134755 A CN 202110134755A CN 112963249 A CN112963249 A CN 112963249A
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- energy igniter
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The invention is suitable for the technical field of engines, in particular to a high-energy igniter for aviation, which comprises a high-energy igniter main body; the high-energy igniter main body utilizes an electronic switch to adopt an automatic frequency stabilizing circuit to stabilize the spark frequency output by the igniter, adopts an R-S trigger and an oscillator to form a pulse width modulator to control energy storage energy, and adopts a silicon controlled switch control circuit to control the conduction of high voltage electricity; a circuit in the high-energy igniter main body is provided with a high-voltage rectifier, a capacitor, an interrupter and an induction coil; the ignition energy of the engine is improved, the adaptation degree of the engine to the lean mixture is improved, the service life is long, the reliability is high, the cost is low, the use is convenient, the size is small, the ignition energy is large, the requirement of high spark energy required by the aeroengine can be met, the use is safe, the size is small, the low-voltage high-frequency ignition success rate is high, the environment adaptation capability is strong, and the automatic ignition device is suitable for the automatic ignition of the aeroengine in various complex environments.
Description
Technical Field
The invention relates to the technical field of engines, in particular to an aviation high-energy igniter.
Background
The traditional gasoline engine igniter has limited electric spark energy and cannot ignite combustible mixed gas with larger proportion of air and gasoline, so that the traditional gasoline engine igniter has the defects of high energy consumption and serious tail gas pollution.
The transistor igniters used recently, although greatly improving the ignition capability of the igniter, have made their use in aircraft engines difficult due to the following problems; namely, the initial electric signal is weak, and needs to be amplified for many times by a complex circuit, so that once a fault is difficult to remove; elements with poor heat resistance such as germanium tubes and the like are adopted, so that the high-temperature working environment of the aircraft engine is not suitable; 3. the traditional igniter which can be used on a light engine has less number and extremely high cost; the traditional high-energy igniter mostly adopts high voltage and high frequency, and the change of the environmental (air pressure, temperature and humidity) conditions influences the change of the breakdown voltage (namely the ignition voltage) of the electric spark; in particular, high-voltage electric spark devices require high insulation (withstand voltage strength) of equipment, and when the ignition environment is poor or the ignition device is contaminated, the withstand voltage is lowered, and the ignition function is easily lost due to breakdown leakage. Therefore, the high-energy igniter device for aviation has important significance for improving the ignition reliability of the combustion device of the industrial furnace using heavy oil or residual oil.
Disclosure of Invention
The invention aims to provide a high-energy igniter for aviation, which solves the problems in the prior art; in order to achieve the purpose, the invention provides the following technical scheme:
an aviation high-energy igniter comprises a high-energy igniter main body;
the high-energy igniter comprises a high-energy igniter body, and is characterized in that an automatic frequency stabilizing circuit, a pulse width modulation circuit, a direct current conversion circuit, a high-voltage circuit, a charging circuit and a discharging circuit which are sequentially connected in series are arranged in the high-energy igniter body, and low voltage is converted into high voltage by the automatic frequency stabilizing circuit, the pulse width modulation circuit, the direct current conversion circuit, the high-voltage circuit, the charging circuit and the discharging circuit;
a silicon controlled switch control circuit is connected between the pulse width modulation circuit and the discharge circuit;
the high-energy igniter main body utilizes an electronic switch to adopt an automatic frequency stabilizing circuit to stabilize the spark frequency output by the igniter, adopts an R-S trigger and an oscillator to form a pulse width modulator to control energy storage energy, and adopts a silicon controlled switch control circuit to control the conduction of high voltage electricity;
a circuit in the high-energy igniter main body is provided with a high-voltage rectifier, a capacitor, an interrupter and an induction coil; the low-voltage direct current is changed into pulsating high-voltage electricity after the common work of the interrupter and the induction coil, and then the energy storage capacitor is charged through the high-voltage rectifier; when the voltage in the capacitor reaches the breakdown value of the sealed discharge gap, the end face of the ignition nozzle discharges to generate electric sparks;
the high-energy igniter main body is connected with an electric nozzle and a cable; the high-energy igniter main body converts low voltage of 12V direct current into high voltage required by the electric nozzle, the electric nozzle and the high-energy igniter main body work together to generate electric sparks to ignite the starting nozzle to atomize oil-gas mixture, and the cable is used for electrically connecting the high-energy igniter main body and the electric nozzle to complete transmission of high-voltage electric energy.
Furthermore, the ignition energy of the engine is obviously improved, the adaptation degree of the engine to the lean mixture is improved, the analog circuit is converted into a digital circuit, the high-temperature high-frequency ignition device is suitable for the high-temperature and low-temperature complex working environment of the aircraft engine, has the advantages of long service life, high reliability, low cost, convenience in use, small size and large ignition energy, and can also meet the requirement of the aircraft engine on high spark energy.
In the high-energy igniter for aviation of the invention: the electric nozzle is a semiconductor ignition electric nozzle; and the cable is a high voltage ignition cable.
In the high-energy igniter for aviation of the invention: the high-energy igniter is characterized in that a shell is arranged on the high-energy igniter main body, and a field excitation plate is arranged in the shell.
Further scheme: and an excitation tank cover is arranged on the shell outside the excitation plate.
Further scheme: the shell is additionally provided with a socket, and the socket is installed on the shell through screws. The optimized screw is a round head screw.
Preferably: the joint of the screw and the shell is sleeved with a nut which is fixed by utilizing the screw thread of the nut, and the joint of the nut and the shell is sleeved with a gasket.
Preferably: the socket is sleeved with a threaded cap, and a wave-shaped spring washer and a copper disc are sleeved between the threaded cap and the socket.
Further scheme: the shell is provided with a plurality of fixed blades, and the fixed blades are provided with fastening nuts fixed through hollow rivets.
In the high-energy igniter for aviation of the invention: the high-energy igniter main body is made of light metal materials.
Compared with the prior art, the high-energy igniter for aviation comprises a high-energy igniter main body; the high-energy igniter main body utilizes an electronic switch to adopt an automatic frequency stabilizing circuit to stabilize the spark frequency output by the igniter, adopts an R-S trigger and an oscillator to form a pulse width modulator to control energy storage energy, and adopts a silicon controlled switch control circuit to control the conduction of high voltage electricity; a circuit in the high-energy igniter main body is provided with a high-voltage rectifier, a capacitor, an interrupter and an induction coil; the low-voltage direct current is changed into pulsating high-voltage electricity after the common work of the interrupter and the induction coil, and then the energy storage capacitor is charged through the high-voltage rectifier; when the voltage in the capacitor reaches the breakdown value of the sealed discharge gap, the end face of the ignition nozzle discharges to generate electric sparks; the high-energy igniter main body is connected with an electric nozzle and a cable; the high-energy igniter main body converts low voltage of input 12V direct current into high voltage required by the electric nozzle, the electric nozzle and the high-energy igniter main body work together and are used for generating electric sparks to ignite a starting nozzle to atomize oil-gas mixed gas, and the cable is used for electrically connecting the high-energy igniter main body and the electric nozzle to finish transmission of high-voltage electric energy; the ignition energy of the engine is obviously improved, the adaptation degree of the engine to the lean mixture is improved, an analog circuit is converted into a digital circuit, the ignition energy-saving high-energy ignition device is suitable for the high-temperature and low-temperature complex working environment of the aero-engine, has the advantages of long service life, high reliability, low cost, convenience in use, small size and large ignition energy, and can meet the requirement of the aero-engine for high spark energy.
Drawings
FIG. 1 is a schematic diagram of an aircraft high energy igniter of the invention.
FIG. 2 is a block diagram of the electrical circuit connections for the high energy aviation igniter of the invention.
Fig. 3 is a circuit diagram of the high-energy igniter for aviation of the invention.
In the figure: 1-an excitation plate; 2-a socket; 3-excitation case cover; 4-wave spring washer; 5-round head screws; 6-a gasket; 7-a nut; 8-a captive nut; 9-hollow rivet; 10-copper disk.
Detailed Description
The technical solution of the present invention will be described in further detail with reference to specific embodiments. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In one embodiment of the present invention, as shown in fig. 1-3, an aircraft high energy igniter includes a high energy igniter body; the high-energy igniter comprises a high-energy igniter body, and is characterized in that an automatic frequency stabilizing circuit, a pulse width modulation circuit, a direct current conversion circuit, a high-voltage circuit, a charging circuit and a discharging circuit which are sequentially connected in series are arranged in the high-energy igniter body, and low voltage is converted into high voltage by the automatic frequency stabilizing circuit, the pulse width modulation circuit, the direct current conversion circuit, the high-voltage circuit, the charging circuit and the discharging circuit; a silicon controlled switch control circuit is connected between the pulse width modulation circuit and the discharge circuit;
the high-energy igniter main body utilizes an electronic switch to adopt an automatic frequency stabilizing circuit to stabilize the spark frequency output by the igniter, adopts an R-S trigger and an oscillator to form a pulse width modulator to control energy storage energy, and adopts a silicon controlled switch control circuit to control the conduction of high voltage electricity; a circuit in the high-energy igniter main body is provided with a high-voltage rectifier, a capacitor, an interrupter and an induction coil; the low-voltage direct current is changed into pulsating high-voltage electricity after the common work of the interrupter and the induction coil, and then the energy storage capacitor is charged through the high-voltage rectifier; when the voltage in the capacitor reaches the breakdown value of the sealed discharge gap, the end face of the ignition nozzle discharges to generate electric sparks; the high-energy igniter main body is connected with an electric nozzle and a cable; the high-energy igniter main body converts low voltage of 12V direct current into high voltage required by the electric nozzle, the electric nozzle and the high-energy igniter main body work together to generate electric sparks to ignite the starting nozzle to atomize oil-gas mixture, and the cable is used for electrically connecting the high-energy igniter main body and the electric nozzle to complete transmission of high-voltage electric energy.
As shown in fig. 3, the choke inductive coil can prolong the discharge time, and the discharge resistor is used to limit the maximum energy storage value of the energy storage capacitor and ensure that the energy stored in the capacitor is completely released within 1min after the system is disconnected; the safety resistor is used for ensuring that the high-voltage wire can work safely even if the high-voltage wire is disconnected or insulated; converting 12V low voltage provided by an ECU power supply of the engine into high voltage capable of breaking down an electrode gap of a spark plug; meanwhile, the ignition time can be automatically and manually adjusted; the capacitor is used for reducing contact sparks of the breaker and increasing the secondary voltage of the ignition coil; in addition, the additional resistor short-circuit device is used for short-circuit the additional resistor during starting, increasing the primary current of the ignition coil and enhancing the spark jump energy of the spark plug during starting, the working voltage of the aviation high-energy igniter is 8-28V, and as long as the working voltage is higher than 10V, the ignition frequency is not influenced by the voltage and the 2-3 times of spark frequency ignition per second is always kept.
In the embodiment of the invention, the ignition energy of the engine is obviously improved, the adaptation degree of the engine to the lean mixture is improved, the analog circuit is converted into the digital circuit, the high-low temperature complex working environment of the aircraft engine is suitable, the service life is long, the reliability is high, the cost is low, the use is convenient, the volume is small, the ignition energy is large, and the requirement of the aircraft engine for high spark energy can be met.
In the embodiment of the invention, as shown in fig. 1, the electric nozzle is a semiconductor ignition electric nozzle; and the cable is a high voltage ignition cable; the high-energy igniter main body is made of a light metal material; the high-energy igniter is characterized in that a shell is arranged on the high-energy igniter main body, and a field excitation plate 1 is arranged in the shell.
An excitation tank cover 3 is arranged on the outer shell outside the excitation plate 1; the socket 2 is additionally arranged on the shell, and the socket 2 is arranged on the shell through a screw; the optimized screw is a round head screw 5. The housing is provided with a plurality of fixed blades on which are provided tie nuts 8 secured by blind rivets 9.
The joint of the screw and the shell is sleeved with a nut 7 and is fixed by the nut 7 through threads, and the joint of the nut 7 and the shell is sleeved with a gasket 6. The socket 2 is sleeved with a threaded cap, and a wave spring gasket 4 and a copper disc 10 are sleeved between the threaded cap and the socket 2.
The invention relates to an aviation high-energy igniter, which comprises a high-energy igniter main body; the high-energy igniter main body utilizes an electronic switch to adopt an automatic frequency stabilizing circuit to stabilize the spark frequency output by the igniter, adopts an R-S trigger and an oscillator to form a pulse width modulator to control energy storage energy, and adopts a silicon controlled switch control circuit to control the conduction of high voltage electricity; a circuit in the high-energy igniter main body is provided with a high-voltage rectifier, a capacitor, an interrupter and an induction coil; the low-voltage direct current is changed into pulsating high-voltage electricity after the common work of the interrupter and the induction coil, and then the energy storage capacitor is charged through the high-voltage rectifier; when the voltage in the capacitor reaches the breakdown value of the sealed discharge gap, the end face of the ignition nozzle discharges to generate electric sparks; the high-energy igniter main body is connected with an electric nozzle and a cable; the high-energy igniter main body converts low voltage of input 12V direct current into high voltage required by the electric nozzle, the electric nozzle and the high-energy igniter main body work together and are used for generating electric sparks to ignite a starting nozzle to atomize oil-gas mixed gas, and the cable is used for electrically connecting the high-energy igniter main body and the electric nozzle to finish transmission of high-voltage electric energy; the ignition energy of the engine is obviously improved, the adaptation degree of the engine to the lean mixture is improved, an analog circuit is converted into a digital circuit, the ignition energy-saving high-energy ignition device is suitable for the high-temperature and low-temperature complex working environment of the aero-engine, has the advantages of long service life, high reliability, low cost, convenience in use, small size and large ignition energy, and can meet the requirement of the aero-engine for high spark energy.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (9)
1. A high-energy igniter for aviation is characterized in that,
comprises a high energy igniter main body;
the high-energy igniter comprises a high-energy igniter body, and is characterized in that an automatic frequency stabilizing circuit, a pulse width modulation circuit, a direct current conversion circuit, a high-voltage circuit, a charging circuit and a discharging circuit which are sequentially connected in series are arranged in the high-energy igniter body, and low voltage is converted into high voltage by the automatic frequency stabilizing circuit, the pulse width modulation circuit, the direct current conversion circuit, the high-voltage circuit, the charging circuit and the discharging circuit;
a silicon controlled switch control circuit is connected between the pulse width modulation circuit and the discharge circuit;
the high-energy igniter main body utilizes an electronic switch to adopt an automatic frequency stabilizing circuit to stabilize the spark frequency output by the igniter, adopts an R-S trigger and an oscillator to form a pulse width modulator to control energy storage energy, and adopts a silicon controlled switch control circuit to control the conduction of high voltage electricity;
a circuit in the high-energy igniter main body is provided with a high-voltage rectifier, a capacitor, an interrupter and an induction coil; the low-voltage direct current is changed into pulsating high-voltage electricity after the common work of the interrupter and the induction coil, and then the energy storage capacitor is charged through the high-voltage rectifier; when the voltage in the capacitor reaches the breakdown value of the sealed discharge gap, the end face of the ignition nozzle discharges to generate electric sparks;
the high-energy igniter main body is connected with an electric nozzle and a cable; the high-energy igniter main body converts low voltage of 12V direct current into high voltage required by the electric nozzle, the electric nozzle and the high-energy igniter main body work together to generate electric sparks to ignite the starting nozzle to atomize oil-gas mixture, and the cable is used for electrically connecting the high-energy igniter main body and the electric nozzle to complete transmission of high-voltage electric energy.
2. The aeronautical high-energy igniter according to claim 1, wherein the electric nozzle is a semiconductor ignition electric nozzle; and the cable is a high voltage ignition cable.
3. The high-energy igniter for aviation according to claim 1, wherein the high-energy igniter body is provided with a housing, and a field plate is mounted inside the housing.
4. The high-energy igniter for aviation according to claim 3, wherein a field case cover is mounted on the housing outside the field plate.
5. The high-energy igniter for aviation according to claim 3, wherein the housing is provided with a socket, and the socket is mounted on the housing by screws.
6. The high-energy igniter for the aviation according to claim 5, wherein a nut is sleeved at the joint of the screw and the shell and is fixed by the screw thread of the nut, and a gasket is sleeved at the joint of the nut and the shell.
7. The high-energy igniter for aviation according to claim 5, wherein the socket is sleeved with a threaded cap, and a wave spring washer and a copper disc are sleeved between the threaded cap and the socket.
8. The high energy igniter of claim 3, wherein the housing is provided with a plurality of fixing blades, and the fixing blades are provided with fastening nuts fixed by means of hollow rivets.
9. The high-energy igniter for aviation according to any one of claims 1 to 8, wherein the high-energy igniter body is made of a light metal material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110134755.0A CN112963249A (en) | 2021-01-29 | 2021-01-29 | High-energy igniter for aviation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110134755.0A CN112963249A (en) | 2021-01-29 | 2021-01-29 | High-energy igniter for aviation |
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| CN112963249A true CN112963249A (en) | 2021-06-15 |
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| CN202110134755.0A Pending CN112963249A (en) | 2021-01-29 | 2021-01-29 | High-energy igniter for aviation |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113958416A (en) * | 2021-11-11 | 2022-01-21 | 四川泛华航空仪表电器有限公司 | High-voltage frequency-stabilizing ignition device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20120145136A1 (en) * | 2010-12-14 | 2012-06-14 | John Antony Burrows | Multi-event corona discharge ignition assembly and method of control and operation |
| CN202747392U (en) * | 2012-07-30 | 2013-02-20 | 咸阳西燃机电设备有限公司 | Chargeable high-energy electric ignition device |
| CN104454288A (en) * | 2014-09-30 | 2015-03-25 | 四川泛华航空仪表电器有限公司 | Frequency-stabilization high-energy electronic ignition device |
| CN109653877A (en) * | 2018-11-30 | 2019-04-19 | 陕西航空电气有限责任公司 | It is a kind of to determine frequency point ignition circuit for Aero-Engine Start igniting |
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2021
- 2021-01-29 CN CN202110134755.0A patent/CN112963249A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120145136A1 (en) * | 2010-12-14 | 2012-06-14 | John Antony Burrows | Multi-event corona discharge ignition assembly and method of control and operation |
| CN202747392U (en) * | 2012-07-30 | 2013-02-20 | 咸阳西燃机电设备有限公司 | Chargeable high-energy electric ignition device |
| CN104454288A (en) * | 2014-09-30 | 2015-03-25 | 四川泛华航空仪表电器有限公司 | Frequency-stabilization high-energy electronic ignition device |
| CN109653877A (en) * | 2018-11-30 | 2019-04-19 | 陕西航空电气有限责任公司 | It is a kind of to determine frequency point ignition circuit for Aero-Engine Start igniting |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113958416A (en) * | 2021-11-11 | 2022-01-21 | 四川泛华航空仪表电器有限公司 | High-voltage frequency-stabilizing ignition device |
| CN113958416B (en) * | 2021-11-11 | 2023-11-17 | 四川泛华航空仪表电器有限公司 | High-voltage frequency-stabilizing ignition device |
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