CN115559832A - Small-size torch of gas hydrogen oxygen point firearm structure - Google Patents
Small-size torch of gas hydrogen oxygen point firearm structure Download PDFInfo
- Publication number
- CN115559832A CN115559832A CN202211322544.0A CN202211322544A CN115559832A CN 115559832 A CN115559832 A CN 115559832A CN 202211322544 A CN202211322544 A CN 202211322544A CN 115559832 A CN115559832 A CN 115559832A
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- CN
- China
- Prior art keywords
- oxygen
- hydrogen
- ignition
- igniter
- nozzle
- Prior art date
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- Pending
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- 239000001301 oxygen Substances 0.000 title claims abstract description 39
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 39
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 34
- 239000001257 hydrogen Substances 0.000 title claims abstract description 29
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 29
- 239000007789 gas Substances 0.000 title claims abstract description 14
- 125000004435 hydrogen atom Chemical class [H]* 0.000 title 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 23
- 238000002485 combustion reaction Methods 0.000 claims abstract description 14
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 8
- 239000010949 copper Substances 0.000 claims abstract description 8
- 229910052802 copper Inorganic materials 0.000 claims abstract description 8
- 238000010892 electric spark Methods 0.000 claims abstract description 6
- 238000007789 sealing Methods 0.000 claims abstract description 5
- 239000010963 304 stainless steel Substances 0.000 claims abstract description 4
- 229910001369 Brass Inorganic materials 0.000 claims abstract description 4
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 claims abstract description 4
- 239000010951 brass Substances 0.000 claims abstract description 4
- 230000000694 effects Effects 0.000 claims abstract description 4
- 238000010008 shearing Methods 0.000 claims abstract description 4
- 150000002431 hydrogen Chemical class 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 229910002804 graphite Inorganic materials 0.000 claims description 2
- 239000010439 graphite Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 4
- 238000009530 blood pressure measurement Methods 0.000 claims 1
- 238000012856 packing Methods 0.000 claims 1
- 238000005496 tempering Methods 0.000 claims 1
- 230000005284 excitation Effects 0.000 description 5
- 239000003721 gunpowder Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Landscapes
- 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 discloses a small torch igniter structure taking gas hydrogen and gas oxygen as media. Setting hydrogen and oxygen coaxial shearing nozzles, controlling flow rate by using sonic nozzles, and igniting by using an electric spark plug. When the device is used, the pressure in front of the hydrogen and oxygen sonic nozzle is determined according to the mixing ratio, the spark plug is electrified to ignite, and the hydrogen and oxygen supply control valves are sequentially opened according to the pressure building time of hydrogen and oxygen filling, so that the hydrogen and oxygen combustion ignition can be completed. After ignition is successful, the spark plug can be powered off, and hydrogen and oxygen can be stably combusted in the ignition chamber of the igniter. The invention integrates the flow control sonic nozzle with the igniter, reduces the filling volume, improves the ignition response speed and reduces the effect after shutdown. The igniter body is made of 304 stainless steel, the sonic nozzle is made of brass, and red copper is used as a sealing washer. When the fire-back combustion oxygen pipe is in an unexpected condition and the system cannot respond emergently, the system is naturally blocked at the sonic nozzle.
Description
Technical Field
The invention relates to the field of rocket engine design, test and other combustion equipment, in particular to a miniaturized gas medium high-energy ignition device.
Background
Rocket engines using liquid propellant can be ignited by various ways, such as gunpowder, plasma, electric spark, etc., usually by a cartridge, and the fuel nozzle can be filled with an autoignition substance for ignition. After ignition, the combustion chamber may maintain combustion without further ignition. After several seconds of engine shutdown, the combustion chamber may be auto-ignited, however many engines are not able to ignite once the combustion chamber cools. At present, the upper stage rocket engine mostly adopts liquid hydrogen and liquid oxygen as fuels, and simultaneously needs to meet the task requirements of secondary starting and the like. This requires the installation of multiple igniters, adding complexity to the system. There is a need for a highly reliable, highly stable, reusable ignition device.
In addition, when the ground high-modulus test is carried out on the upper-stage rocket engine, a high-altitude environment is manufactured through a pre-vacuumizing system, and the engine is placed in the high-altitude environment to carry out various test runs. A commonly used pre-evacuation system is an engine-diffuser-ejector pump system. The ejector pump system requires a high-temperature and high-pressure steam medium to pump high-temperature, high-speed and large-mass-flow fuel gas generated by the engine. The steam medium is usually supplied by means of a gas generator, which is required to have high reliability, stability and long service life. Igniter burners also need to meet high reliability, stability and long life requirements.
The hydrogen-oxygen igniter has the following advantages:
compared with a gunpowder igniter, the gas hydrogen oxygen igniter can be repeatedly used, the problems of storage, transportation and management of firer equipment do not exist, the problem of repeated use and gunpowder replacement is avoided, and the gas hydrogen oxygen igniter has advantages in terms of use economy and convenience.
Compared with a high-energy igniter, the gas hydrogen oxygen igniter needs smaller ignition energy, does not have ultrahigh-voltage pulse excitation, has small interference on a test measurement and control system during ignition, does not need to consider the problems of electromagnetic compatibility and the like, and thus simplifies the test system.
Disclosure of Invention
The invention aims to provide a reusable hydrogen-oxygen small torch igniter which is used for ignition of combustion equipment such as rocket engines, burners and the like. The problem to be solved by the present invention is (1) to provide a stable high energy ignition excitation for combustion equipment; (2) Parameters such as ignition flow, temperature and pressure are adjustable, and the test use requirements of multiple working conditions are met.
The technical scheme of the invention is as follows: the designed flow of the igniter is 6g/s, the designed pressure is 5MPa, the hydrogen-oxygen mixing ratio is 1, the hydrogen flow is 3g/s, the oxygen flow is 3g/s, the allowable working mixing ratio is 0.7-1.1, the allowable working time is 10s, and the ignition excitation mode is a spark plug. The nozzle is in the form of a coaxial shearing nozzle, the flow is controlled by adopting a sonic nozzle, the sonic nozzle is integrated with an igniter, the filling volume is reduced, the ignition response speed is improved, and the effect after shutdown is reduced. The igniter body is made of 304 stainless steel, the sonic nozzle is made of brass, and red copper is used as a sealing washer. When the fire-back combustion oxygen pipe is in an unexpected condition and the system cannot respond emergently, the system is naturally blocked at the sonic nozzle. The design pressure before sound is 8MPa, the throat diameter of the oxygen sonic nozzle is 0.4mm, and the throat diameter of the hydrogen sonic nozzle is 0.8mm. The total length of the igniter is about 160mm, and the square size of the body part is 38x38mm. The primary parameters of interest for the igniter are: the pressure before the oxygen sonic nozzle, the pressure before the hydrogen sonic nozzle and the igniter. The sound velocity nozzle is provided with key parameters for flow control (mixing ratio), and the igniter pressure is an important parameter for ignition success or failure.
The invention has the advantages and positive effects that: (1) The gas hydrogen and gas oxygen media are adopted, and the spark plug is used as an ignition excitation mode, so that the ignition device has the advantages of adjustable parameters, reusability, high safety and high reliability. (2) The igniter has small size, light weight and simple medium supply system, and may be used widely in various kinds of combustor.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are the basic design of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts. FIG. 1 is a simplified schematic diagram of the present invention.
The ignition device comprises (1) an oxygen inlet, (2) a red copper gasket, (3) a sonic nozzle, (4) an igniter oxyhydrogen coaxial nozzle, (5) a sealing graphite gasket, (6) an electric spark plug, (7) a spark plug red copper gasket, (8) an ignition chamber pressure measuring interface, (9) an ignition chamber, (10) a connecting piece, (11) a fastening screw, (12) a hydrogen inlet
Detailed Description
The invention is further described below with reference to the figures and examples.
The designed flow of the igniter is 6g/s, the designed pressure is 5MPa, the hydrogen-oxygen mixing ratio is 1, the hydrogen flow is 3g/s, the oxygen flow is 3g/s, the allowable working mixing ratio is 0.7-1.1, the allowable working time is 10s, and the ignition excitation mode is a spark plug. The nozzle is in the form of a coaxial shearing nozzle, the flow is controlled by adopting a sonic nozzle, the sonic nozzle is integrated with an igniter, the filling volume is reduced, the ignition response speed is improved, and the effect after shutdown is reduced. The igniter body is made of 304 stainless steel, the sonic nozzle is made of brass, and red copper is used as a sealing washer. When the fire-back combustion oxygen pipe is in an unexpected condition and the system cannot respond emergently, the fire-back combustion oxygen pipe is naturally blocked at the sonic nozzle. The design pressure before sound is 8MPa, the throat diameter of the oxygen sonic nozzle is 0.4mm, and the throat diameter of the hydrogen sonic nozzle is 0.8mm. The igniter has a total length of about 160mm and a body square dimension of 38x38mm. The primary parameters of interest for the igniter are: the pressure before the oxygen-igniting sonic nozzle, the pressure before the hydrogen-igniting sonic nozzle and the pressure of an igniter. The sound velocity nozzle is provided with key parameters for flow control (mixing ratio), and the igniter pressure is an important parameter for ignition success or failure.
Claims (8)
1. The method of claim 1: the utility model provides a small-size torch point firearm structure of gas hydrogen, gas oxygen for thrust chambers such as rocket engine are igniteed and are used, its characterized in that comprises oxygen entry (1), red copper gasket (2), sonic nozzle (3), the coaxial nozzle of some firearm oxyhydrogen (4), sealed graphite packing ring (5), electric spark plug (6), spark plug red copper gasket (7), ignition chamber pressure measurement interface (8), ignition chamber (9), connecting piece (10), fastening screw (11), hydrogen entry (12), its characterized in that: ignition hydrogen and oxygen enter the coaxial nozzle (4) at the head of the igniter after passing through the sonic nozzle (3) through the inlets (12) and (1), the hydrogen and the oxygen are fully mixed in the ignition chamber (9) through gas-gas shearing, ignition is carried out through the electric spark plug (6), the electric spark plug (6) is powered off immediately, and the hydrogen and the oxygen continue to stably combust in the ignition chamber (9).
2. The method of claim 2: the method is characterized in that: the oxygen inlet (1) is connected with the head of the coaxial nozzle (4), the hydrogen inlet (12) is connected with the side surface of the coaxial nozzle (4), and after the hydrogen and the oxygen flow out of the coaxial nozzle, the oxygen is surrounded in the middle of the ignition chamber (9).
3. The method of claim 3: the sonic nozzle (3) for controlling the flow is integrated with the igniter, so that the filling volume of hydrogen and oxygen is reduced, the corresponding ignition speed can be improved, and the effect after shutdown is reduced.
4. Based on claim 1, there is the feature: 304 stainless steel is adopted for the hydrogen-oxygen coaxial nozzle (4) and the ignition chamber (9) of the igniter.
5. Based on claim 1, there is the feature: the sonic nozzle (3) is made of brass, the sonic nozzle sealing gasket is made of a red copper gasket (2), and when the unexpected conditions such as a tempering combustion oxygen supply pipeline and the like occur and the system cannot respond emergently, the sonic nozzle (3) can be naturally blocked.
6. Based on claim 1, there are the features: the pressure measuring interface (8) is arranged on the ignition chamber (9), and the pressure of the ignition chamber (9) can be measured by connecting a pressure sensor to judge whether the igniter is normally burnt.
7. Based on claim 1, there are the features: the inlet pressure of the oxygen inlet (1) and the hydrogen inlet (12) can be adjusted to adjust the combustion mixing ratio of the igniter, so that different ignition temperatures are realized.
8. Based on claim 1, there is the feature: the common ignition spark plug (9) provides 15-50 mJ energy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211322544.0A CN115559832A (en) | 2022-10-26 | 2022-10-26 | Small-size torch of gas hydrogen oxygen point firearm structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211322544.0A CN115559832A (en) | 2022-10-26 | 2022-10-26 | Small-size torch of gas hydrogen oxygen point firearm structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115559832A true CN115559832A (en) | 2023-01-03 |
Family
ID=84769286
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211322544.0A Pending CN115559832A (en) | 2022-10-26 | 2022-10-26 | Small-size torch of gas hydrogen oxygen point firearm structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115559832A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1918565A2 (en) * | 2006-11-02 | 2008-05-07 | Astrium GmbH | Ignition anode for re-ignitable rocket thrust chambers |
| CN102094728A (en) * | 2010-12-30 | 2011-06-15 | 北京航空航天大学 | Supplying device of small-flow and high-temperature gas propellant |
| US8117824B1 (en) * | 2009-02-04 | 2012-02-21 | The United States of America as represented by the Secterary of the Navy | Pollution free engine using hydrogen as a fuel |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN107893711A (en) * | 2017-10-27 | 2018-04-10 | 北京航天动力研究所 | A kind of gas hydrogen-oxygen torch type electric ignition device |
| CN114087089A (en) * | 2021-11-19 | 2022-02-25 | 北京航天试验技术研究所 | High-efficiency ignition conical surface injector |
-
2022
- 2022-10-26 CN CN202211322544.0A patent/CN115559832A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1918565A2 (en) * | 2006-11-02 | 2008-05-07 | Astrium GmbH | Ignition anode for re-ignitable rocket thrust chambers |
| US8117824B1 (en) * | 2009-02-04 | 2012-02-21 | The United States of America as represented by the Secterary of the Navy | Pollution free engine using hydrogen as a fuel |
| CN102094728A (en) * | 2010-12-30 | 2011-06-15 | 北京航空航天大学 | Supplying device of small-flow and high-temperature gas propellant |
| CN105952552A (en) * | 2016-04-29 | 2016-09-21 | 北京航空航天大学 | Rectangular transparent combustion chamber for optical diagnosis of small rocket engine |
| CN107893711A (en) * | 2017-10-27 | 2018-04-10 | 北京航天动力研究所 | A kind of gas hydrogen-oxygen torch type electric ignition device |
| CN114087089A (en) * | 2021-11-19 | 2022-02-25 | 北京航天试验技术研究所 | High-efficiency ignition conical surface injector |
Non-Patent Citations (1)
| Title |
|---|
| 李茂;高玉闪;金平;俞南嘉;马彬;蔡国飙;: "富氢/富氧燃气气-气喷嘴热试", 推进技术, no. 06, 15 December 2010 (2010-12-15), pages 696 - 700 * |
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