CN101852148A - Oxygen/kerosene ignitor using pneumatic resonance ignition technology - Google Patents
Oxygen/kerosene ignitor using pneumatic resonance ignition technology Download PDFInfo
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- CN101852148A CN101852148A CN200910081278A CN200910081278A CN101852148A CN 101852148 A CN101852148 A CN 101852148A CN 200910081278 A CN200910081278 A CN 200910081278A CN 200910081278 A CN200910081278 A CN 200910081278A CN 101852148 A CN101852148 A CN 101852148A
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- igniter
- kerosene
- oxygen
- nozzle
- gasket seal
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Abstract
The invention discloses an oxygen/kerosene ignitor using a pneumatic resonance ignition technology, and belongs to the field of rocket motors. The oxygen/kerosene ignitor using the pneumatic resonance ignition technology comprises an oxygen path nozzle (1), a sealing spacer (2), a hot surface ignitor (3), a positioning ferrule (4), a sealing spacer (5), a resonating tube sleeve (6), a sealing spacer (7), a main oxygen collection ring (8), an ignitor body (9), an ignitor head (10), a kerosene/oxygen combined nozzle (11), a sealing spacer (12), a cavitation pipe (13), a kerosene connecting nozzle (14) and a sealing spacer (15). The hot surface ignitor works by using a pneumatic resonance heating method; and the resonating pipe is positioned on the side face of the ignitor head. The kerosene is sprayed into the nozzle from the side face of the kerosene/oxygen combined nozzle in the radial direction. The oxygen axially passes through the combined nozzle. The ignitor body is positioned in the main oxygen collection ring for replenishing oxygen to a burning torch for burning.
Description
[technical field]
The present invention relates to a kind of gas oxygen kerosene igniter device of using the Pneumatic resonance firing technique.
[background technique]
With liquid oxygen, kerosene be the liquid propellant rocket engine firing technique commonly used of propellant agent be utilize can with the starting fuel of gas oxygen spontaneous combustion, pneumatic fuel is introduced into the oxygen spontaneous ignition of firing chamber and the gas phase that enters under certain pressure, and the kerosene that will enter subsequently and liquid oxygen are lighted, this firing technique is very reliable, it can be used for the first order, also can be used for the pneumatic of second-stage rocket motor, its major defect is can only one-shot, can not satisfy the requirement that repeatedly starts.Hypergolic fuel has toxicity simultaneously, and inflammable, explosive, the difficult storage.For liquid oxygen, kerosene rocket motor,, can also design special start-up system in order repeatedly to start.Along with opening the oxygenant main valve, open the starting fuel supply valve of pilot jet during startup, spontaneous ignition thereupon, and form the burning torch.Main fuel enters the back and just lights by this torch, cuts off starting fuel when entering working state in the firing chamber immediately.This scheme awing can repeatedly be started, and shortcoming is that the special starting system of a cover must be arranged on the motor, has increased the weight of motor and the complexity that control is handled, and has influenced reliability.The high energy electric ignition also can realize repeatedly pneumatic.But spark ignition needs very powerful power supply, increase the very big electric ignition system of a cover weight, and the functional reliability of high-voltage circuit system is poor under vacuum condition, is difficult to overcome the interference of static and radio frequency, also can produce electrical interference to instrument on the arrow.
The Niwa success utilize Pneumatic resonance direct ignition scheme to light oxygen not have, generated oxygen kerosene lighting-off torch because the flame temperature height, combustion process has only continued 0.5s, the red copper igniting chamber with wall thickness in the test comes accumulation of heat, to prevent the wall ablation.This igniter needs thermal protection to handle, and increases the igniter structure complexity greatly.
[summary of the invention]
The purpose of this invention is to provide and a kind ofly can repeat repeatedly to start, neither increase the special starting system of a cover, can also avoid electrostatic radio frequency and disturb to overcome the gas oxygen/kerosene igniter of high-altitude ignition difficulty, reliable operation, lightweight application Pneumatic resonance firing technique.
Use Pneumatic resonance firing technique gas oxygen/kerosene igniter by oxygen road ozzle (1), gasket seal (2), hot surface igniter (3), positioning sleeve (4), gasket seal (5), resonance pipe box (6), sealing spot film (7), main oxygen collector ring (8), igniter body portion (9), igniter head (10), kerosene-gas oxygen built up nozzle (11), gasket seal (12), cavitation erosion pipe (13), kerosene connecting-tube nozzle (14), gasket seal (15) are formed.Hot surface igniter adopts the Pneumatic resonance mode of heating, and resonatron is positioned at igniter head side.Kerosene radially sprays in the nozzle from kerosene-gas oxygen built up nozzle side.Oxygen axially passes through built up nozzle.Igniter body portion is provided with main oxygen collector ring and is used for burning to the lighting-off torch oxygenating.Igniter head and body portion adopt stainless steel material.
The advantage of this invention has: (a) hot surface igniter is positioned at the igniting chamber side, and resonator gas is not subjected to the propellant agent condition restriction, can freely select propellant.(b) not limited by condition of resonance, the pressure of oxygen and kerosene and flow can change in a big way.(c) system architecture is simple, and reliable operation is compared with spark ignition, can not produce other instrument and equipments and disturb.(d) adopt premixed nozzle, helped the blending of gas oxygen kerosene, be beneficial to igniting.(e) adopt main oxygen collector ring that torch is carried out the oxygenating burning, can improve the energy of igniting.(f) igniter head and body portion adopt stainless steel material, and cost is low, and is easy to process.
[description of drawings]
Fig. 1 is a gas oxygen/kerosene igniter of using the Pneumatic resonance firing technique
[embodiment]
Further specify the present invention below in conjunction with accompanying drawing.
As shown in Figure 1, the gas oxygen/kerosene igniter of using the Pneumatic resonance firing technique is by oxygen road ozzle (1), gasket seal (2), hot surface igniter (3), positioning sleeve (4), gasket seal (5), resonance pipe box (6), gasket seal (7), main oxygen collector ring (8), igniter body portion (9), igniter head (10), kerosene-gas oxygen built up nozzle (11), and gasket seal (12), cavitation erosion pipe (13), kerosene connecting-tube nozzle (14), gasket seal (15) are formed.
Oxygen road ozzle (1) is positioned on igniter head (10) central axis, link to each other with igniter head (10) by screw thread, it is the passage of oxygen inlet point firearm, this joint sealing realizes by gasket seal (2), gasket seal (2) adopts red copper to make, and carrying out annealing in process, igniter head (10) is made for stainless steel material.Kerosene connecting-tube nozzle (14) is positioned at igniter head (10) side, is connected with igniter head (10) by screw thread.Cavitation erosion pipe (13) and gasket seal (12) are housed between kerosene connecting-tube nozzle (14) and the igniter head (10), and the cavitation erosion pipe is used to control kerosene oil flow.Kerosene-gas oxygen built up nozzle (11) is arranged in igniter head (10), is fixed on igniter head (10) center during by oxygen road ozzle (1) means of press seals packing ring (2).Kerosene-gas oxygen built up nozzle passes through seal washer (2) with extraneous sealing and seal washer (15) is realized.In the test, oxygen enters kerosene-gas oxygen built up nozzle from oxygen road, center ozzle (1), kerosene from igniter head side face, and kerosene sprays into built up nozzle with the radial spray form, and oxygen axially sprays into, the atomization and vaporization that helps kerosene like this, easily blending is evenly and by reliable ignition.Hot surface igniter (3) is positioned at igniter head (10) side, links to each other with resonance pipe box (6) by engage thread, and the resonance pipe box is welded on igniter head side.Can adjust the length that hot surface igniter (3) enters igniting chamber by adjusting positioning sleeve (6) and gasket seal (5) thickness.Igniter body portion (9) links to each other with igniter head (10) by screw thread, adopts gasket seal (7) sealing of red copper between the two, and igniter body portion (9) adopts stainless steel material to make.The outside weld of igniter body portion is connected to main oxygen collector ring (8), by main oxygen collector ring the lighting-off torch from the igniter ejection is carried out the oxygenating burning, improves ignition energy.
When using the gas oxygen/kerosene igniter work of Pneumatic resonance technology, earlier by resonator gas heating hot surface igniter (3), then by oxygen road ozzle (1) and kerosene connecting-tube nozzle (14) aerating oxygen and kerosene, kerosene radially sprays into kerosene-gas oxygen built up nozzle (11), oxygen axially enters kerosene-gas oxygen built up nozzle (11), mix gas-liquid then and spray into igniting chamber head (10) from kerosene-gas oxygen built up nozzle (11) again, the formation lighting-off torch is lighted in hot surface igniter (3) back that touches heating, by main oxygen collector ring (8) lighting-off torch being carried out oxygenating when igniter body portion (9) sprays burns, the lighting-off torch energy further promotes, and helps igniting.
Claims (4)
1. use the gas oxygen/kerosene igniter of Pneumatic resonance firing technique, by oxygen road ozzle (1), gasket seal (2), hot surface igniter (3), positioning sleeve (4), gasket seal (5), resonance pipe box (6), sealing spot film (7), main oxygen collector ring (8), igniter body portion (9), igniter head (10), kerosene-gas oxygen built up nozzle (11), gasket seal (12), cavitation erosion pipe (13), kerosene connecting-tube nozzle (14), gasket seal (15) are formed, and it is characterized in that:
Oxygen road ozzle (1) is positioned on igniter head (10) central axis, linking to each other with igniter head (10) by screw thread, is the passage of oxygen inlet point firearm, and this joint sealing realizes by gasket seal (2), gasket seal (2) adopts red copper to make, and carries out annealing in process.Kerosene connecting-tube nozzle (14) is positioned at igniter head (10) side, is connected with igniter head (10) by screw thread.Cavitation erosion pipe (13) and gasket seal (12) are housed between kerosene connecting-tube nozzle (14) and the igniter head (10).Kerosene-gas oxygen built up nozzle (11) is arranged in igniter head (10), is fixed on igniter head (10) center during by oxygen road ozzle (1) means of press seals packing ring (2).Kerosene-gas oxygen built up nozzle passes through seal washer (2) with extraneous sealing and seal washer (15) is realized.Hot surface igniter (3) is positioned at igniter head (10) side, links to each other with resonance pipe box (6) by engage thread, and resonance pipe box (6) is welded on igniter head side.Igniter body portion (9) links to each other with igniter head (10) by screw thread, adopts gasket seal (7) sealing of red copper between the two.The outside weld of igniter body portion is connected to main oxygen collector ring (8).
2. the gas oxygen/kerosene igniter of application Pneumatic resonance firing technique according to claim 1 is characterized in that: described kerosene-gas oxygen built up nozzle radial side has spray orifice.
3. the gas oxygen/kerosene igniter of application Pneumatic resonance firing technique according to claim 1 is characterized in that: hot surface igniter (3) is positioned at igniter head side, and positioning sleeve (4) and gasket seal (5) are arranged between the igniter head.
4. the gas oxygen/kerosene igniter of application Pneumatic resonance firing technique according to claim 1 is characterized in that: igniter body portion (9), igniter body portion (10) adopt stainless steel material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910081278A CN101852148A (en) | 2009-04-01 | 2009-04-01 | Oxygen/kerosene ignitor using pneumatic resonance ignition technology |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910081278A CN101852148A (en) | 2009-04-01 | 2009-04-01 | Oxygen/kerosene ignitor using pneumatic resonance ignition technology |
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| CN101852148A true CN101852148A (en) | 2010-10-06 |
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| CN200910081278A Pending CN101852148A (en) | 2009-04-01 | 2009-04-01 | Oxygen/kerosene ignitor using pneumatic resonance ignition technology |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102016112619A1 (en) | 2016-06-24 | 2017-12-28 | Christian Bauer | Engine ignition device for an engine and ignition method |
| CN107762636A (en) * | 2017-10-23 | 2018-03-06 | 南京航空航天大学 | Kerosene igniter and ignition method applied to micro turbine engine starting system |
| CN109113896A (en) * | 2018-08-31 | 2019-01-01 | 西安航天动力研究所 | A kind of small-sized plug-in type chemical ignitor |
| CN109322750A (en) * | 2018-10-16 | 2019-02-12 | 北京动力机械研究所 | The dual-purpose high-energy igniter of micro gas-liquid |
| CN109441643A (en) * | 2018-09-27 | 2019-03-08 | 北京航空航天大学 | Micro turbojet engine and gas-turbine combustion chamber igniter |
| CN111765017A (en) * | 2020-06-11 | 2020-10-13 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN113352061A (en) * | 2021-08-11 | 2021-09-07 | 西安远航真空钎焊技术有限公司 | Method for producing a gas generator |
| CN114592989A (en) * | 2022-05-09 | 2022-06-07 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
| CN114776482A (en) * | 2022-05-20 | 2022-07-22 | 西北工业大学 | Liquid rocket engine propulsion system utilizing resonance ignition |
| CN114776478A (en) * | 2022-05-20 | 2022-07-22 | 西北工业大学 | Liquid rocket engine two-component propulsion system utilizing resonance ignition |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017220754A1 (en) | 2016-06-24 | 2017-12-28 | Christian Bauer | Ignition device and ignition method |
| DE102016112619A1 (en) | 2016-06-24 | 2017-12-28 | Christian Bauer | Engine ignition device for an engine and ignition method |
| US11204002B2 (en) | 2016-06-24 | 2021-12-21 | Christian Bauer | Ignition device and ignition method |
| CN107762636A (en) * | 2017-10-23 | 2018-03-06 | 南京航空航天大学 | Kerosene igniter and ignition method applied to micro turbine engine starting system |
| CN109113896A (en) * | 2018-08-31 | 2019-01-01 | 西安航天动力研究所 | A kind of small-sized plug-in type chemical ignitor |
| CN109113896B (en) * | 2018-08-31 | 2024-02-06 | 西安航天动力研究所 | Small plug-in type chemical igniter |
| CN109441643A (en) * | 2018-09-27 | 2019-03-08 | 北京航空航天大学 | Micro turbojet engine and gas-turbine combustion chamber igniter |
| CN109441643B (en) * | 2018-09-27 | 2020-12-01 | 北京航空航天大学 | Micro-turbojet engine and ignition device for combustion chamber of gas turbine |
| CN109322750A (en) * | 2018-10-16 | 2019-02-12 | 北京动力机械研究所 | The dual-purpose high-energy igniter of micro gas-liquid |
| CN111765017B (en) * | 2020-06-11 | 2023-11-03 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN111765017A (en) * | 2020-06-11 | 2020-10-13 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN113352061A (en) * | 2021-08-11 | 2021-09-07 | 西安远航真空钎焊技术有限公司 | Method for producing a gas generator |
| CN114592989B (en) * | 2022-05-09 | 2022-08-16 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
| CN114592989A (en) * | 2022-05-09 | 2022-06-07 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
| CN114776478A (en) * | 2022-05-20 | 2022-07-22 | 西北工业大学 | Liquid rocket engine two-component propulsion system utilizing resonance ignition |
| CN114776478B (en) * | 2022-05-20 | 2023-06-09 | 西北工业大学 | Liquid rocket engine double-component propulsion system utilizing resonance ignition |
| CN114776482B (en) * | 2022-05-20 | 2023-08-11 | 西北工业大学 | Liquid rocket engine propulsion system utilizing resonance ignition |
| CN114776482A (en) * | 2022-05-20 | 2022-07-22 | 西北工业大学 | Liquid rocket engine propulsion system utilizing resonance ignition |
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Application publication date: 20101006 |