CN109357256A - A kind of igniter for ram rocket type heater - Google Patents
A kind of igniter for ram rocket type heater Download PDFInfo
- Publication number
- CN109357256A CN109357256A CN201811285801.1A CN201811285801A CN109357256A CN 109357256 A CN109357256 A CN 109357256A CN 201811285801 A CN201811285801 A CN 201811285801A CN 109357256 A CN109357256 A CN 109357256A
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- CN
- China
- Prior art keywords
- shell
- cylindrical hole
- igniter
- powder charge
- type heater
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Solid-Fuel Combustion (AREA)
Abstract
The invention discloses a kind of igniters for ram rocket type heater, belong to igniter technical field, comprising: electric igniter, shell, grate and powder charge；The outlet end of the shell is processed as spout structure, the spout structure is made of the first cylindrical hole, the second cylindrical hole and the round platform hole sequence along combustion gas direction, and first cylindrical hole diameter less than the second cylindrical hole diameter, the intersection of the first cylindrical hole and the second cylindrical hole formed sudden expansion step；Electric igniter is mounted on the input end of shell and is closed；Powder charge is coaxially mounted in the cavity of shell, is equipped with grate between end and the spout structure of shell；It is machined with more than two ventholes on the grate, the discharge of rear combustion gas is lighted for powder charge.The present invention is applied to the ignition start of ram rocket type heater, and igniting is stablized, and securely and reliably, does not occur heater and igniter ablation situation.
Description
Technical field
The invention belongs to igniter technical fields, and in particular to a kind of igniting dress for ram rocket type heater
It sets.
Background technique
Currently, igniter is generally made of electric igniter, powder charge, shell, the igniter working principle are as follows: when to electricity
After igniter supplies upper given DC pulse current, electric igniter, which works, exports high pressure flame, the powder charge in lead fire device,
Powder charge burning generates the spout output that high-temperature fuel gas flows through shell, lights heater incoming flow.
But the nozzle of current igniter uses gradual change type expansion segment, makes flame jet fast speed and working medium circle
The temperature in face is relatively low, and then reduces the ignition ability of flame jet, may cause heater firing delay.And current powder charge
Zirconium powder-lead orthoplumbate powder charge is mostly used greatly, can be generated more solid combustion after zirconium powder-lead orthoplumbate powder charge burning and be produced
Object, combustion product, which enters heater, to generate destruction to heater structure.
Summary of the invention
In view of this, being applied to punching press fire the present invention provides a kind of igniter for ram rocket type heater
The ignition start of arrow type heater, igniting are stablized, and securely and reliably, do not occur heater and igniter ablation situation.
The present invention is achieved through the following technical solutions:
A kind of igniter for ram rocket type heater, comprising: electric igniter, grate, shell and powder charge；
The shell is the tubular structure of both ends open, and an opening is input end, another opening is outlet end, outlet
End is processed as spout structure, and the spout structure is by the first cylindrical hole, the second cylindrical hole and the round platform hole sequence along combustion gas direction
Composition, and the diameter of the first cylindrical hole is less than the diameter of the second cylindrical hole, in the intersection of the first cylindrical hole and the second cylindrical hole
Sudden expansion step is formed, the diameter of the second cylindrical hole and the end diameter of round platform hole are identical, and the second cylindrical hole and round platform hole cross
Place is smooth transition；
Electric igniter is mounted on the input end of shell and is closed；
Powder charge is coaxially mounted in the cavity of shell, is equipped with grate between end and the spout structure of shell；Institute
It states and is machined with more than two ventholes with spout structure perforation on grate, the discharge of rear combustion gas is lighted for powder charge.
Further, the powder charge uses double base propellant powder charge.
It further, further include gasket seal, gasket seal is mounted on electric igniter and docks place with the end face of shell.
It further, further include cushion, cushion is mounted between powder charge and electric igniter.
It further, further include pressure measurement mouth, pressure measurement mouth is mounted on the outside of shell, and communicates with the cavity of shell, is used for
Measure the pressure in the cavity of shell.
The utility model has the advantages that the spout structure of (1) shell of the invention is equipped with sudden expansion step, increase flame jet and working medium interface
Temperature and action time, reduce flame jet speed, improve the temperature of flame jet and working medium interface, it is sharp pressure do not occur
The ignition ability of flame jet is improved, and and be effectively guaranteed heater and igniter so that heater igniting is steady in peak
Safety of structure.
(2) powder charge of the invention zirconium powder-lead orthoplumbate powder charge conventional using double base propellant powder charge replacement, it is biradical
Propellant loading technical maturity, solid content, can be to avoid solid combustion product to heater structure less than 5% in combustion product
Destruction, and double base propellant powder charge is packed into shell by free loading propellant mode, and production process is simple, high production efficiency.
(3) the combustion temperature of double base propellant powder charge of the invention is moderate, and outlet temperature is not more than 2100K, avoids ablation shell,
Shell can be reused, and production cost is low.
(5) fixed combustion product is generated after the present invention stops powder charge to be lighted by grate, prevents solid combustion product
Into heater destruction can be generated to heater structure.
Detailed description of the invention
Fig. 1 is structure composition figure of the invention；
Wherein, 1- electric igniter, 2- gasket seal, 3- shell, 4- powder charge, 5- grate, 6- pressure measurement mouth, 7-
Cushion, 8- spout structure.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
A kind of igniter for ram rocket type heater is present embodiments provided, referring to attached drawing 1, comprising: electric point
Fire tool 1, gasket seal 2, shell 3, powder charge 4, grate 5, pressure measurement mouth 6 and cushion 7；
The shell 3 is the tubular structure of both ends open, and an opening is input end, another opening is outlet end, out
Mouth end is processed as spout structure 8, and the spout structure 8 is by the first cylindrical hole, the second cylindrical hole and round platform hole along combustion gas direction
Sequence forms, and the diameter of the first cylindrical hole is less than the diameter of the second cylindrical hole, in the friendship of the first cylindrical hole and the second cylindrical hole
Sudden expansion step is formed at remittance, the diameter of the second cylindrical hole and the end diameter of round platform hole are identical, the second cylindrical hole and round platform hole
Intersection is smooth transition；Wherein, the diameter of first cylindrical hole is 4mm, and the diameter of the second cylindrical hole is 9mm；
Electric igniter 1 is mounted on the input end of shell 3 and is closed, and electric igniter 1 docks place with the end face of shell 3
Gasket seal 2 is installed, guarantees the input end sealing of shell 3, prevents powder charge 4 from lighting rear combustion gas and leak；
Powder charge 4 is coaxially mounted in the cavity of shell 3, and cushion 7 is equipped between one end and electric igniter 1, another
Grate 5 is installed between end and the spout structure 8 of shell 3；The more than two and spout knot is machined on the grate 5
The venthole that structure 8 penetrates through, in order to which the discharge of rear combustion gas is lighted in powder charge 4；The grate 5 after stopping powder charge 4 to be lighted for producing
Raw fixed combustion product, the cushion 7 is for generating biggish impact to electric igniter 1 after preventing powder charge 4 from lighting；The dress
Medicine 4 uses double base propellant powder charge；
Pressure measurement mouth 6 is mounted on the outside of shell 3, and communicates with the cavity of shell 3, in the cavity for measuring shell 3
Pressure.
Working principle: when heater prepares to light a fire, testing stand electrical system provides the direct current arteries and veins of setting to electric igniter 1
After rushing electric current, the work output high temperature, high pressure flame of electric igniter 1, and powder charge 4 of igniting, the burning of powder charge 4 generate high-temperature fuel gas and pass through
The spout structure 8 of shell 3 sprays, and lights heater.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (5)
1. a kind of igniter for ram rocket type heater, comprising: electric igniter (1), shell (3) and powder charge (4),
It is characterized in that, further includes grate (5)；
The shell (3) is the tubular structure of both ends open, and an opening is input end, another opening is outlet end, outlet
End is processed as spout structure (8), and the spout structure (8) is by the first cylindrical hole, the second cylindrical hole and rotary table along combustion gas direction
Hole sequence forms, and the diameter of the first cylindrical hole is less than the diameter of the second cylindrical hole, in the first cylindrical hole and the second cylindrical hole
Intersection forms sudden expansion step, and the diameter of the second cylindrical hole and the end diameter of round platform hole are identical, the second cylindrical hole and round platform hole
Intersection be smooth transition；
Electric igniter (1) is mounted on the input end of shell (3) and is closed；
Powder charge (4) is coaxially mounted in the cavity of shell (3), is equipped with gear between the spout structure (8) of end and shell (3)
Medicine plate (5)；It is machined with more than two ventholes with the spout structure (8) perforation on the grate (5), is used for powder charge
(4) discharge of rear combustion gas is lighted.
2. a kind of igniter for ram rocket type heater as described in claim 1, which is characterized in that the powder charge
(4) double base propellant powder charge is used.
3. a kind of igniter for ram rocket type heater as described in claim 1, which is characterized in that further include close
Gasket (2), gasket seal (2) are mounted on electric igniter (1) and dock place with the end face of shell (3).
4. a kind of igniter for ram rocket type heater as described in claim 1, which is characterized in that further include delaying
Punching pad (7), cushion (7) are mounted between powder charge (4) and electric igniter (1).
5. a kind of igniter for ram rocket type heater as described in claim 1, which is characterized in that further include surveying
Pressure mouth (6), pressure measurement mouth (6) is mounted on the outside of shell (3), and communicates with the cavity of shell (3), for measuring shell (3)
Pressure in cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811285801.1A CN109357256B (en) | 2018-10-31 | 2018-10-31 | A kind of igniter for ram rocket type heater |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811285801.1A CN109357256B (en) | 2018-10-31 | 2018-10-31 | A kind of igniter for ram rocket type heater |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109357256A true CN109357256A (en) | 2019-02-19 |
| CN109357256B CN109357256B (en) | 2019-10-18 |
Family
ID=65347488
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811285801.1A Active CN109357256B (en) | 2018-10-31 | 2018-10-31 | A kind of igniter for ram rocket type heater |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109357256B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0363834A1 (en) * | 1988-10-12 | 1990-04-18 | Ruhrgas Aktiengesellschaft | Burner, particularly a high-speed burner |
| RU2327892C2 (en) * | 2005-12-26 | 2008-06-27 | Александр Николаевич Бобров | Method of controlling solid-fuel rocket engine thrust and solid-fuel charge |
| CN102361221A (en) * | 2011-09-23 | 2012-02-22 | 柳孟柱 | Spark plug |
| CN103644047A (en) * | 2013-11-21 | 2014-03-19 | 北京动力机械研究所 | Igniting and starting device of solid rocket engine |
| US20140174313A1 (en) * | 2012-12-24 | 2014-06-26 | Raytheon Company | Electrically operated propellants |
| CN104061089A (en) * | 2014-05-18 | 2014-09-24 | 西北工业大学 | Device and method for testing solid fuel melting characteristics |
| CN106050476A (en) * | 2016-07-11 | 2016-10-26 | 湖北三江航天江河化工科技有限公司 | Liquid-propellant rocket engine ignition device and ignition method thereof |
| CN106524144A (en) * | 2016-12-09 | 2017-03-22 | 江苏大学 | Micro combustor for micro thermophotovoltaic system |
| CN107514644A (en) * | 2017-07-27 | 2017-12-26 | 西安航天动力研究所 | Dinitrogen tetroxide/Hydrazine propellant waste gas and liquids treatment burner and control method |
-
2018
- 2018-10-31 CN CN201811285801.1A patent/CN109357256B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0363834A1 (en) * | 1988-10-12 | 1990-04-18 | Ruhrgas Aktiengesellschaft | Burner, particularly a high-speed burner |
| RU2327892C2 (en) * | 2005-12-26 | 2008-06-27 | Александр Николаевич Бобров | Method of controlling solid-fuel rocket engine thrust and solid-fuel charge |
| CN102361221A (en) * | 2011-09-23 | 2012-02-22 | 柳孟柱 | Spark plug |
| US20140174313A1 (en) * | 2012-12-24 | 2014-06-26 | Raytheon Company | Electrically operated propellants |
| CN103644047A (en) * | 2013-11-21 | 2014-03-19 | 北京动力机械研究所 | Igniting and starting device of solid rocket engine |
| CN104061089A (en) * | 2014-05-18 | 2014-09-24 | 西北工业大学 | Device and method for testing solid fuel melting characteristics |
| CN106050476A (en) * | 2016-07-11 | 2016-10-26 | 湖北三江航天江河化工科技有限公司 | Liquid-propellant rocket engine ignition device and ignition method thereof |
| CN106524144A (en) * | 2016-12-09 | 2017-03-22 | 江苏大学 | Micro combustor for micro thermophotovoltaic system |
| CN107514644A (en) * | 2017-07-27 | 2017-12-26 | 西安航天动力研究所 | Dinitrogen tetroxide/Hydrazine propellant waste gas and liquids treatment burner and control method |
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| Publication number | Publication date |
|---|---|
| CN109357256B (en) | 2019-10-18 |
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