CN204026696U - The system of the large flow combustible gas of fast processing - Google Patents
The system of the large flow combustible gas of fast processing Download PDFInfo
- Publication number
- CN204026696U CN204026696U CN201420215595.8U CN201420215595U CN204026696U CN 204026696 U CN204026696 U CN 204026696U CN 201420215595 U CN201420215595 U CN 201420215595U CN 204026696 U CN204026696 U CN 204026696U
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- China
- Prior art keywords
- igniter
- combustible gas
- trigger point
- combustion chamber
- point firearm
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Abstract
The utility model discloses the system of the large flow combustible gas of a kind of fast processing, comprise trigger point firearm, igniter, erecting device, control system; Described erecting device is for being fixed on described igniter in the atmosphere that may produce large flow combustible gas; Described igniter inside is provided with the composite solidpropellant powder column containing a large amount of metallics, and described trigger point firearm is connected with described igniter, in described igniter, is provided with nozzle, for eject high temperature containing energy metallic; Described control device is transferred to described trigger point firearm by IGNITION CONTROL holding circuit safely and reliably by firing command.The utility model arranges the igniter that can eject high-temperature gas moment by the periphery at hydrogen discharge mouth, thereby at the initial stage of flammable vapor cloud formation, is burnt fast, thereby avoids the detonation of combustible gas, has safety, swift advantage.
Description
Technical field
The utility model relates to a kind of system of fast processing combustible gas, relates in particular to the system of the large flow combustible gas of a kind of fast processing.
Background technology
Conventionally, low form carrier rocket, receives firing command at rocket and has taken off 7～10 second time to rocket.Receiving after the firing command of master control net, liquid-propellant rocket engine will continue a large amount of low temperature hydrogen of discharge to flat pad surrounding environment, until rocket takes off.If cannot reliably process rapidly the hydrogen of these a large amount of discharges, the hydrogen group of its gathering is mixed with air, reaches combustible gas detonation concentration interval, will likely produce detonation, the dangerous matter sources while becoming rocket launching.In addition, in the time that rocket engine occurs the fault mode of cold run and carries out emergency cutoff program, rocket around will be around a large amount of hydrogen cloud clusters, and now, the importance of the large flow hydrogen of fast processing solution is more outstanding.
In addition, in industrial processes, in daily life process, all there is the occasion that causes potential safety hazard as fuel gatherings such as natural gas, coal gas, ethane, acetylene, therefore, above situation all makes technology and the method for a kind of reliable treatments rapidly of current urgent need combustible gas, solves the potential danger of industrial, civilian combustible gas in application.
Utility model content
The purpose of this utility model is to provide the system of the large flow low temperature of a kind of reliable treatments fast combustible gas, solves large flow combustible gas and is gathered in the danger causing in industry and civilian process.
For achieving the above object, the system of the large flow combustible gas of a kind of fast processing of the utility model, comprises trigger point firearm, igniter, erecting device, control system;
Described igniter inside is provided with combustion chamber, in described combustion chamber, has fuel, is provided with composite solidpropellant powder column in described combustion chamber, and described composite solidpropellant powder column contains a large amount of metallics; In described igniter, be provided with nozzle, for ejecting the metallic of HTHP;
Described trigger point firearm is connected with described igniter, for lighting described fuel in combustion chamber;
Described erecting device is for fixing described igniter;
Described control system comprises control circuit, for by control circuit for described trigger point firearm provides heavy current, make it to light igniter;
Described control system is connected with described trigger point firearm by control circuit, described trigger point firearm is fixed on described igniter one end, be connected with described combustion chamber, described igniter is fixed in the atmosphere that may produce large flow combustible gas by described erecting device.
Described trigger point firearm is fixed in described igniter, and described combustion chamber is stretched in its one end, and the other end is connected with described control system by firing cable;
Described trigger point firearm is connected by electric connector with described firing cable;
Described trigger point firearm receives the signal of described control system and electric energy conversion is become to heat energy, the fuel igniting in described combustion chamber.
Described igniter is the container that is provided with a nozzle, is also provided with a jack on it, and for connecting described trigger point firearm, described igniter air-tightness is good;
Described igniter comprises respectively housing, internal insulation, combustion chamber from outside to inside, has fuel and composite solidpropellant in described combustion chamber; Described jack runs through described housing, internal insulation and combustion chamber, and described trigger point firearm is fixed in described jack, stretches into described combustion chamber.
Described erecting device is fixed support.
One end of described igniter is cone-shaped, and the other end is cylindrical, and described jack is arranged on cylindrical one side, and described nozzle is arranged on cone shape one side;
Housing, the internal insulation entirety of described igniter are cylindrical;
Described igniter inside is provided with columniform combustion chamber along central axis.
Described igniter is fixed on the rocket rocket body supporting arm both sides on rocket launching pad by described mounting bracket;
Described mounting bracket is for adjusting setting height(from bottom) and the angle of pitch of described igniter;
The direction of the spout indication of described igniter is towards rocket row's hydrogen mouth and lower than described rocket row hydrogen mouth;
The nozzle of described igniter is tapered, makes the high-temperature metal particle ejecting have larger spray angle; Described firing cable is a kind of cable of the high temperature ablation of resistance to moment.
Described control system comprises switching value output circuit, holding circuit, testing circuit;
Described switching value output circuit, for controlling the connecting and disconnecting of the circuit of described trigger point firearm, is igniter power supply;
Described switching value output circuit comprises two PLC controllers, be respectively a PLC controller and the 2nd PLC controller, a described PLC controller and the 2nd PLC controller are Redundancy Design, and a described PLC controller and the corresponding I/O interface of the 2nd PLC controller are connected respectively and control the gauge tap of single or multiple described triggering igniters; A described PLC controller is connected respectively described testing circuit and holding circuit with the corresponding I/O interface of the 2nd PLC controller;
Described testing circuit comprises protective resistance, detector;
In described testing circuit, be provided with at least three test points, be separately positioned on described protective resistance two ends and igniter common port;
Described holding circuit comprises PLC input module, relay and photoelectrical coupler, and described photoelectric coupler output end is connected with the corresponding I/O interface of described PLC controller.
The system of the large flow combustible gas of a kind of fast processing of the utility model also comprises sensing module, and described sensing module is connected with described control module;
Described sensing module is sensor, is combustible gas concentration sensor or photoelectric sensor;
Described sensor setting is in combustible gas atmosphere;
Described sensor is used for surveying combustible gas, and signal is transferred to control system.
The system composition that the utility model provides simply, response is quick, reliability is high, and Full-automatic remote control, can ensure the security that easily produces the environment of large flow combustible gas.Technology of the present utility model has wide range of applications, can be used in the booster system of oxyhydrogen engine, comprise the large-scale low-temperature type carrier rocket of using in manned moon landing and space station, also can be by above-mentioned sensing module being set in combustible gas discharge or leakage hole, input instruction using alarm signal as total system working signal, exist combustible gas to assemble thereby can be applied in, cause in the Industrial Engineering or civilian place of potential safety hazard, have advantages of that efficiency is high, response is fast, applicability is strong.
Brief description of the drawings
Fig. 1 is the structured flowchart of the system of the large flow combustible gas of the fast processing of the present embodiment.
Fig. 2 is the hydrogen combustion ignition device structure schematic diagram of the present embodiment.
Fig. 3 is the vertical direction layout drawing of the igniter of the present embodiment.
When Fig. 4 is the igniter work of the present embodiment, the top view of the simulation overlay area of ejection HTHP metallic.
Fig. 5 is the switching value output circuit schematic diagram of the control circuit of the present embodiment.
Fig. 6 is holding circuit and the testing circuit schematic diagram of the control circuit of the present embodiment.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is described in detail:
Shown in figure 1, the hydrogen treat system of the present embodiment comprises control system 1, trigger point firearm 2, igniter 3, erecting device 4 and sensing module.
Igniter 3 inside are provided with composite solidpropellant, for eject the metallic of a large amount of HTHPs in the situation of being heated, to light large flow flammable vapor cloud.
Trigger point firearm 2 is connected with igniter 3, for lighting the fuel in igniter 2.
Erecting device 4 is for being fixedly mounted on combustible gas atmosphere by igniter 3.
Control system 1 comprises control circuit, for by control circuit for trigger point firearm 2 provides heavy current, make it to light the composite solidpropellant in igniter 3;
Control system 1 is connected with trigger point firearm 2 by control circuit, and trigger point firearm 2 is fixed on igniter 3 one end and is connected with combustion chamber, and igniter 2 is fixed in the atmosphere that may produce large flow combustible gas by erecting device 4.
Sensing device in the present embodiment, for detection of combustible gas.
In the course of work, control system receives signal or the combustible gas discharge signal etc. of sensing module, and for providing heavy current to make it end, trigger point firearm produces electric spark by firing cable, composite solidpropellant in lead fire device, when its burning, can produce the gas of a large amount of HTHPs, by a large amount of metallic ejections, thereby for providing energy, extraneous flammable vapor cloud makes it burning.
Igniter 3 is for being provided with the container of a nozzle, and its air-tightness is good.
With reference to figure 2, in the present embodiment, igniter 3 comprises respectively housing 32, internal insulation 33, combustion chamber 34 from outside to inside, is provided with composite solidpropellant powder column 35 in combustion chamber 34.
In igniter 3, be provided with a jack 31 that runs through housing 32, internal insulation 33 and combustion chamber 34.Trigger point firearm 2 is fixed in jack 31, and combustion chamber 34 is stretched in its one end, and the other end is connected with control system 1 by firing cable; Trigger point firearm 2 is connected by electric connector with firing cable.
One end of igniter 3 is cone-shaped, and the other end is cylindrical, and jack 31 is arranged on cylindrical one side, and nozzle 36 is arranged on cone shape one side;
Housing 32 and internal insulation 33 are respectively cylindrical;
Combustion chamber 34 is along the central axis setting of igniter 3, cylindrical.
The nozzle 36 of igniter has certain angle of inclination, tapered, makes the metallic of ejection in igniter have larger spray angle.
In the present embodiment, the large flow hydrogen that the system of the large flow combustible gas of fast processing of the present utility model gives off before for the treatment of rocket launching on rocket launch platform.Rocket rocket body is fixed on four main supporting arms, and 8 igniters are horizontally fixed on 4 main supporting arm both sides between two by mounting bracket respectively; As shown in Figure 3, igniter 3 is horizontally fixed on rocket body supporting arm 5 both sides, and mounting bracket is for adjusting setting height(from bottom) and the angle of pitch of igniter 3; The direction of the spout indication of igniter 3 is towards rocket row hydrogen mouth 6, and the installation site of igniter 3 is lower than rocket row hydrogen mouth 6.
As shown in Figure 4, when the composite solidpropellant in igniter 3 is lighted, the nozzle 36 of igniter 3 can eject the metallic of large amount temperature higher than the HTHP of 900 degrees Celsius fast, the large flow low temperature hydrogen that its rocket by the liquid engine that ignites row hydrogen mouth 6 discharges.Because four rocket body supporting arms 5 are arranged on around two rocket row hydrogen mouths 6,8 igniters 3 are laid in four main supporting arm both sides between two, nozzle points to row's hydrogen mouth, therefore, in the time that the nozzle of 4 groups of igniters ejects the metallic of a large amount of HTHPs simultaneously, the scope of high-temperature metal particle can the whole hydrogen discharge mouth of envelope around.
In real work, for connecting the cable that the firing cable of trigger point firearm is a kind of high temperature ablation of resistance to moment.
The control circuit of the present embodiment comprises respectively switching value output circuit, holding circuit and testing circuit.As shown in Figure 5, the switching value output circuit 11 of the present embodiment comprises three group relaies and two PLC controllers, and two PLC controllers are respectively a PLC controller a1, the 2nd PLC controller a2, and the two is Redundancy Design each other, and unifies distribution by power supply L1.Output port IO2, the IO4 of the one PLC controller a1, IO6 control relay K1, relay K 3, relay K 5, output port IO2, the IO4 of the 2nd PLC controller a2, IO6 control relay K2, relay K 4, relay K 6 respectively, the branch circuit parallel connection of each relay and diode and resistance composition, relay K 1 is connected by contact respectively with relay K 6 with relay K 4, relay K 5 between two with relay K 2, relay K 3, form three tunnel connection in series-parallel redundancy structures, to realize reliable on-off control circuit.
In real work, relay K 1 and relay K 2 are for realizing the break-make of control circuit of single igniter, relay K 3 and relay K 4 be for realizing the break-make of ignition control circuit distribution bus of one or more groups igniter 3, relay K 5 with relay K 6 (belonging to testing circuit) for controlling the break-make of testing circuit 13.The course of action of all relays, need to realize sequential match control by PLC controller software.
As shown in Figure 6, the control system of the present embodiment also comprises testing circuit 13 and holding circuit 12.The input of the output connecting valve amount control circuit 11 of holding circuit 12.Holding circuit 12 comprises PLC input module 14; PLC input module 14 comprises the 3rd PLC controller, the 4th PLC controller (not shown in FIG.), and the protective resistance R of priming system, test point, photoelectrical coupler 15, relay K 5 and relay K 6 etc.The 3rd PLC controller and the 4th PLC controller redundancy each other.In testing circuit 13, be provided with three test points, be separately positioned on before protective resistance R, after protective resistance R and trigger point firearm common port.In the equipment self-inspection stage, by priming system special test equipment, from test point position, circuit resistance is tested, thereby determine path resistance state, by rational design photoelectrical coupler loop, make the action current of photoelectrical coupler 15 far below the safe current of igniter.In the time of path conduction detection, in the situation that guaranteeing that relay K 3, relay K 4 are opened a way, engage relay K5, relay K 6, if there is path in ignition circuit, photoelectrical coupler 15 conductings, the 3rd PLC controller and the 4th PLC controller will detect path conducting state, provide warning message.Holding circuit 12 mainly realizes the loop protection under current state by protective resistance R.Holding circuit 12 also comprises multiple contactors.Principle of the present utility model is: control system 1 receives igniting triggering signal (can be rocket firing signal, sensing module 5 signals and other signal) afterwards, press PLC and control sequential, start trigger point firearm 2 energising that circulates, supply current is DC5～10A.Trigger point firearm 2 is subject to exciting of DC current, composite solidpropellant powder column ignites, produce a large amount of high-temperature fuel gas, by metallic ejection in composite solidpropellant, the thousands of particle that contains certain heat energy arrives predetermined overlay area, as the necessary condition of lighting low temperature hydrogen, by the hydrogen that the reaches burning condition approach exhaustion that will burn.Hydrogen treat system is from receiving firing command in steady-working state, and the response time is less than 100 milliseconds.Can constantly there is heat exchange and blending with oxygen in air in the outermost low temperature hydrogen that liquid engine is discharged, reach the burning concentration condition of combustible gas, runs into the celestial body of high temperature heat, will be ignited.
The control method of the present embodiment, comprises the following steps:
Build the system of the large flow combustible gas of a kind of fast processing of the utility model;
Control system 1 receives igniting triggering signal (the combustible gas concentration alarm signal of rocket firing signal or sensing module 5) afterwards, by PLC control sequential by firing cable to trigger point firearm 2 energising that circulates, supply current is DC5A～10A;
Trigger point firearm 2 triggers igniter 3;
Fuel in the combustion chamber 34 of trigger point firearm 2 lead fire devices 3, makes composite solidpropellant burning, and moment produces high temperature and high pressure gas, by the metallic ejection of a large amount of HTHPs;
The metallic of a large amount of HTHPs mixes with large flow hydrogen, and the hydrogen that ignites.
Above embodiment is described preferred embodiment of the present utility model; not scope of the present utility model is limited; do not departing under the prerequisite of the utility model design spirit; various distortion and improvement that the common engineers and technicians in this area make the technical solution of the utility model, all should fall in the definite protection domain of claims of the present utility model.
Claims (8)
1. a system for the large flow combustible gas of fast processing, is characterized in that, comprises control system (1), trigger point firearm (2), igniter (3), erecting device (4);
Described igniter (3) inside is provided with combustion chamber (34), there is fuel described combustion chamber in (34), in described combustion chamber (34), establish and be filled with composite solidpropellant powder column (35), described composite solidpropellant powder column (35) contains a large amount of metallics; In described igniter (3), be provided with spout (36), for ejecting the metallic of HTHP;
Described trigger point firearm (2) is connected with described igniter (3), for lighting described fuel in combustion chamber;
Described erecting device (4) is for fixing described igniter (3);
Described control system (1) comprises control circuit, for being that described trigger point firearm (2) provides heavy current by control circuit, makes it to light igniter (3);
Described control system (1) is connected with described trigger point firearm (2) by control circuit, described trigger point firearm (2) is fixed on described igniter (3) one end, be connected with described combustion chamber (34), described igniter (2) is fixed in the atmosphere that may produce large flow combustible gas by described erecting device (4).
2. the system of the large flow combustible gas of fast processing according to claim 1, is characterized in that,
It is upper that described trigger point firearm (2) is fixed on described igniter (3), and described combustion chamber (34) is stretched in its one end, and the other end is connected with described control system (1) by firing cable;
Described trigger point firearm (2) is connected by electric connector with described firing cable;
Described trigger point firearm (2) receives the signal of described control system (1) and electric energy conversion is become to heat energy, the fuel in the described combustion chamber (34) of igniting.
3. the system of the large flow combustible gas of fast processing according to claim 2, is characterized in that,
Described igniter (3), for being provided with the container of a nozzle, is also provided with a jack (31) on it, for connecting described trigger point firearm (2), described igniter (3) air-tightness is good;
Described igniter (3) comprises respectively housing (32), internal insulation (33), combustion chamber (34) from outside to inside, has fuel and composite solidpropellant in described combustion chamber;
Run through described housing (32), internal insulation (33) and combustion chamber (34) at described jack (31), described trigger point firearm (2) is fixed in described jack (31), stretches into described combustion chamber (34).
4. the system of the large flow combustible gas of fast processing according to claim 3, is characterized in that,
Described erecting device (4) is mounting bracket.
5. the system of the large flow combustible gas of fast processing according to claim 4, is characterized in that,
One end of described igniter (3) is cone-shaped, and the other end is cylindrical, and described jack (31) is arranged on cylindrical one side, and described nozzle (36) is arranged on cone shape one side;
Housing (32), the internal insulation (33) of described igniter (3) are respectively cylindrical;
Described igniter (3) is inner is provided with columniform combustion chamber (34) along central axis.
6. the system of the large flow combustible gas of fast processing according to claim 5, is characterized in that,
Described igniter (3) is fixed on rocket rocket body supporting arm (5) both sides on rocket launching pad by described mounting bracket;
Described mounting bracket is used for adjusting setting height(from bottom) and the angle of pitch of described igniter (3);
The direction of nozzle (36) indication of described igniter (3) is pointed to rocket row's hydrogen mouth (6) and is arranged hydrogen mouth (6) lower than described rocket;
The nozzle (36) of described igniter (3) is tapered, makes the high-temperature metal particle ejecting have larger spray angle; Described firing cable is a kind of cable of the high temperature ablation of resistance to moment.
7. the system of the large flow combustible gas of fast processing according to claim 3, is characterized in that,
Described control system (1) comprises switching value output circuit (11), holding circuit (13), testing circuit (12);
Described switching value output circuit (11) is for controlling the connecting and disconnecting of the circuit of described trigger point firearm (2) and being its power supply;
Described switching value output circuit (11) comprises two PLC controllers, be respectively a PLC controller (a1) and the 2nd PLC controller (a2), a described PLC controller (a1) and the 2nd PLC controller (a2) are Redundancy Design, and a described PLC controller (a1) and the corresponding I/O interface of the 2nd PLC controller (a2) are connected respectively and control the gauge tap of single or multiple described trigger point firearms (2); A described PLC controller (a1) is connected respectively described testing circuit (13) and holding circuit (12) with the corresponding I/O interface of the 2nd PLC controller (a2);
Described testing circuit (13) comprises protective resistance R, detector;
In described testing circuit, be provided with at least three test points, be separately positioned on described protective resistance R two ends and igniter common port;
Described holding circuit (12) comprises PLC input module (14), relay and photoelectrical coupler (15), and the output of described photoelectrical coupler (15) is connected with the corresponding I/O interface of described PLC input module (14).
8. the system of the large flow combustible gas of fast processing according to claim 7, is characterized in that,
Also comprise sensing module, described sensing module is connected with described control system (1);
Described sensing module is sensor, is combustible gas concentration sensor or photoelectric sensor;
Described sensor setting is in combustible gas atmosphere;
Described sensor is used for surveying combustible gas, and signal is transferred to described control system (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420215595.8U CN204026696U (en) | 2014-04-29 | 2014-04-29 | The system of the large flow combustible gas of fast processing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420215595.8U CN204026696U (en) | 2014-04-29 | 2014-04-29 | The system of the large flow combustible gas of fast processing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204026696U true CN204026696U (en) | 2014-12-17 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420215595.8U Withdrawn - After Issue CN204026696U (en) | 2014-04-29 | 2014-04-29 | The system of the large flow combustible gas of fast processing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204026696U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103994448A (en) * | 2014-04-29 | 2014-08-20 | 北京航天发射技术研究所 | System and method for fast treating large-flow combustible gas |
| CN104791812A (en) * | 2015-04-20 | 2015-07-22 | 中国石油化工股份有限公司 | Torch ignition control system |
-
2014
- 2014-04-29 CN CN201420215595.8U patent/CN204026696U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103994448A (en) * | 2014-04-29 | 2014-08-20 | 北京航天发射技术研究所 | System and method for fast treating large-flow combustible gas |
| CN103994448B (en) * | 2014-04-29 | 2017-06-09 | 北京航天发射技术研究所 | The system and method for quick treatment big flow combustible gas |
| CN104791812A (en) * | 2015-04-20 | 2015-07-22 | 中国石油化工股份有限公司 | Torch ignition control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141217 Effective date of abandoning: 20170609 |
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| AV01 | Patent right actively abandoned |