CN102974908B - Connection method of thrust chamber head stabilizing device of hydrogen oxygen engine - Google Patents
Connection method of thrust chamber head stabilizing device of hydrogen oxygen engine Download PDFInfo
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- CN102974908B CN102974908B CN201210432347.4A CN201210432347A CN102974908B CN 102974908 B CN102974908 B CN 102974908B CN 201210432347 A CN201210432347 A CN 201210432347A CN 102974908 B CN102974908 B CN 102974908B
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Abstract
The invention provides a connection method of a thrust chamber head stabilizing device of a hydrogen oxygen engine. A plurality of hydrogen nozzles and oxygen nozzles which are placed in a ring mode are placed on a panel on the head position, wherein the hydrogen nozzles are sleeved outside the oxygen nozzles. Clapboard nozzles are sleeved above the panel on the head position and outside the hydrogen nozzles and the oxygen nozzles. An assembly gap within 1.0 millimeter is left between neighbouring clapboard nozzles in the radial direction of the penel on the head position. The neighbouring clapboard nozzles in the radial direction are connected in an argon arc brazing mode. Copper-based brazing filler metals are applied to the field of the argon arc brazing and connection of the thrust chamber head stabilizing device, and therefore the technical problem that high frequency instability burning of the hydrogen oxygen engine thrust chamber head is solved. The connection method of the thrust chamber head stabilizing device of the hydrogen oxygen engine is simple in process, high in reliability, stable in product quality and high in production efficiency.
Description
Technical field
The present invention relates to oxyhydrogen engine head construction, be specifically related to a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer.
Background technology
Violent physical and chemical changes is there is when setting forth the combustion chamber combustion of liquid-propellant rocket engine in the professional book such as " hydrogen-oxygen rocket and cryogenic technique thereof " and " liquid-propellant rocket engine principle ".The burning of wherein setting forth combustion chamber in " liquid-propellant rocket engine principle " books can cause the combustion instability of thrust chamber, causes serious consequence.According to combustor pressure oscillations frequency, rough burning is divided into high-frequency combustion instability, low-frequency combustion instability and intermediate-frequency combustion instability, wherein high-frequency combustion instability is very serious to the harm of engine, can be divided into longitudinal vibration shape, the tangential vibration shape, the radial vibration shape and the combination vibration shape.Suppressing somatic sypermutation to be an important and key technology for complexity in liquid-propellant rocket engine development, is also that maximum risk place developed by rocket.
To burn the harm brought for liquid-propellant rocket engine high frequency instability, in " liquid-propellant rocket engine principle ", refer to three kinds of braking measures: ejector filler face dividing plate, acoustic damping device (i.e. the operatic tunes) and improve the combustion stability (improving from the mode such as structure, pressure drop) of ejector filler.As shown in Figure 1, the head panel 4 of oxyhydrogen engine thrust chamber head assembles several hydrogen nozzle 3 be circular layout and oxygen nozzles 5, wherein hydrogen nozzle 3 is placed on outside oxygen nozzle 5, and above head panel 4, the outer also cover of hydrogen nozzle 3 and oxygen nozzle 5 has dividing plate nozzle 2.But the fixed form mentioning dividing plate nozzle in " engine manufacturing technology " has common soldering fixed form, and set forth whether also need brazing between adjacent separator.Being fixedly connected with of aforementioned barriers not only easily comes off under high-temperature work environment, and the space between adjacent separator easily forms somatic sypermutation again.
Summary of the invention
Object of the present invention provides a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, and copper base solder is applied in arc brazing in argon field by it, and technique is simple, reliability is high, constant product quality, production efficiency are high.
Realize the technical scheme of the object of the invention: a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, on head panel, wherein assemble several hydrogen nozzle be circular layout and oxygen nozzles, hydrogen nozzle is placed on outside oxygen nozzle; Above head panel, hydrogen nozzle and oxygen nozzle outward also cover have dividing plate nozzle, it leaves the fit-up gap within 1.0mm between the adjacent separator nozzle of head panel radial direction, adopt arc brazing in argon method to connect between radially adjoining dividing plate nozzle, concrete arc brazing in argon step is as follows:
A copper base solder is fixed in dividing plate nozzle region to be welded by spot welding by ();
B () regulates argon arc welding welding parameter, Current Control is made to control at 2 ~ 30L/min at 5 ~ 100A, argon flow amount, the copper base solder fixing to spot welding heats, welding is started at 2mm ~ 15mm place of distance head panel, progressively heat copper base solder by argon arc, the fusion length formed at dividing plate nozzle gap place is not more than 25mm, and weld width is not more than 8mm, ensures that regional temperature to be welded is no more than 1000 DEG C.
The method of attachment of a kind of oxyhydrogen engine thrust chamber header stabilizer as above, the dividing plate nozzle described in it is with double-layer tube wall structure, and outer wall thickness is at 0.2 ~ 1mm.
The method of attachment of a kind of oxyhydrogen engine thrust chamber header stabilizer as above, the dividing plate nozzle described in it, with internal thread, is threaded connection outside hydrogen nozzle.
The method of attachment of a kind of oxyhydrogen engine thrust chamber header stabilizer as above, it is before carrying out arc brazing in argon, carries out pickling, gasoline cleaning, alcohol washes pretreatment, to ensure to-be-welded region zero defect to dividing plate nozzle surface.
Effect of the present invention is: the method for attachment of oxyhydrogen engine thrust chamber header stabilizer of the present invention, copper base solder is applied in arc brazing in argon field, and this technology is applied to the connection of power room header stabilizer, solve the technical problem of oxyhydrogen engine thrust chamber head somatic sypermutation.The thrust chamber header stabilizer of manufacture of the present invention improves production efficiency and product quality.
Median septum nozzle of the present invention is with double-layer tube wall structure, and center-aisle contributes to heat and sheds, and its outer wall thickness is thinner at 0.2 ~ 1mm, and general solder technology cannot realize stable connection, easily occurs penetration clogging.Adopt arc brazing in argon method of the present invention and related process parameters, can effectively weld, welding large deformation, stablizing for subsequent header provides stable reliability.
Compared with common argon arc fusion welding, it is little that arc brazing in argon has deflection, and the heat affected area degree of superheat is low, again by controlling welding variables, regulate heat input during solder shape seam easily and flexibly, this is with a wide range of applications in welding precision component, thin-walled material etc.
Accompanying drawing explanation
Fig. 1 is oxyhydrogen engine header stabilizer structural representation;
Fig. 2 is that the A-A of Fig. 1 is to sectional view;
Fig. 3 is dividing plate nozzle arrangements schematic diagram.
In figure: 1. fit-up gap; 2. dividing plate nozzle; 3. hydrogen nozzle; 4. head panel; 5. oxygen nozzle.
Detailed description of the invention
Be described in further details below in conjunction with the method for attachment of the drawings and specific embodiments to a kind of oxyhydrogen engine thrust chamber header stabilizer of the present invention.
Embodiment 1
As depicted in figs. 1 and 2, a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, on head panel 4, wherein assemble several hydrogen nozzle 3 of being circular layout and oxygen nozzle 5, hydrogen nozzle 3 is placed on outside oxygen nozzle 5, and above head panel 4, the outer also cover of hydrogen nozzle 3 and oxygen nozzle 5 has dividing plate nozzle 2.As shown in Figure 3, described dividing plate nozzle 2 is with double-layer tube wall structure, and outer wall thickness is at 0.6mm.Dividing plate nozzle 2, with internal thread, is threaded connection outside hydrogen nozzle 3.
Between the adjacent separator nozzle 2 of head panel radial direction, leave the fit-up gap 1 within 1.0mm, then adopt arc brazing in argon method to connect between radially adjoining dividing plate nozzle 2, concrete arc brazing in argon step is as follows:
A copper base solder is fixed in dividing plate nozzle 2 region to be welded by spot welding by ();
B () regulates argon arc welding welding parameter, Current Control is made to control at 15L/min at 50A, argon flow amount, the copper base solder fixing to spot welding heats, in distance, head panel 10mm place starts welding, progressively heat copper base solder by argon arc, the fusion length formed at dividing plate nozzle 2 gap location is not more than 25mm, and weld width is not more than 8mm, ensures that regional temperature to be welded is no more than 1000 DEG C.
Above-mentioned carry out arc brazing in argon before, to dividing plate nozzle 2 surface carry out pickling, gasoline cleaning, alcohol washes pretreatment, to ensure to-be-welded region zero defect.
Embodiment 2
As depicted in figs. 1 and 2, a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, on head panel 4, wherein assemble several hydrogen nozzle 3 of being circular layout and oxygen nozzle 5, hydrogen nozzle 3 is placed on outside oxygen nozzle 5, and above head panel 4, the outer also cover of hydrogen nozzle 3 and oxygen nozzle 5 has dividing plate nozzle 2.As shown in Figure 3, described dividing plate nozzle 2 is with double-layer tube wall structure, and outer wall thickness is at 0.2mm.Dividing plate nozzle 2, with internal thread, is threaded connection outside hydrogen nozzle 3.
Between the adjacent separator nozzle 2 of head panel radial direction, leave the fit-up gap 1 within 1.0mm, then adopt arc brazing in argon method to connect between radially adjoining dividing plate nozzle 2, concrete arc brazing in argon step is as follows:
A copper base solder is fixed in dividing plate nozzle 2 region to be welded by spot welding by ();
B () regulates argon arc welding welding parameter, Current Control is made to control at 2L/min at 5A, argon flow amount, the copper base solder fixing to spot welding heats, in distance, head panel 2mm place starts welding, progressively heat copper base solder by argon arc, the fusion length formed at dividing plate nozzle 2 gap location is not more than 25mm, and weld width is not more than 8mm, ensures that regional temperature to be welded is no more than 1000 DEG C.
Above-mentioned carry out arc brazing in argon before, to dividing plate nozzle 2 surface carry out pickling, gasoline cleaning, alcohol washes pretreatment, to ensure to-be-welded region zero defect.
Embodiment 3
As depicted in figs. 1 and 2, a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, on head panel 4, wherein assemble several hydrogen nozzle 3 of being circular layout and oxygen nozzle 5, hydrogen nozzle 3 is placed on outside oxygen nozzle 5, and above head panel 4, the outer also cover of hydrogen nozzle 3 and oxygen nozzle 5 has dividing plate nozzle 2.As shown in Figure 3, described dividing plate nozzle 2 is with double-layer tube wall structure, and outer wall thickness is at 1mm.Dividing plate nozzle 2, with internal thread, is threaded connection outside hydrogen nozzle 3.
Between the adjacent separator nozzle 2 of head panel radial direction, leave the fit-up gap 1 within 1.0mm, then adopt arc brazing in argon method to connect between radially adjoining dividing plate nozzle 2, concrete arc brazing in argon step is as follows:
A copper base solder is fixed in dividing plate nozzle 2 region to be welded by spot welding by ();
B () regulates argon arc welding welding parameter, Current Control is made to control at 30L/min at 100A, argon flow amount, the copper base solder fixing to spot welding heats, in distance, head panel 15mm place starts welding, progressively heat copper base solder by argon arc, the fusion length formed at dividing plate nozzle 2 gap location is not more than 25mm, and weld width is not more than 8mm, ensures that regional temperature to be welded is no more than 1000 DEG C.
Above-mentioned carry out arc brazing in argon before, to dividing plate nozzle 2 surface carry out pickling, gasoline cleaning, alcohol washes pretreatment, to ensure to-be-welded region zero defect.
Claims (4)
1. a method of attachment for oxyhydrogen engine thrust chamber header stabilizer, wherein at the upper assembling of head panel (4) several hydrogen nozzle (3) be circular layout and oxygen nozzles (5), wherein hydrogen nozzle (3) is placed on oxygen nozzle (5) outward; Also overlap outward at head panel (4) top, hydrogen nozzle (3) and oxygen nozzle (5) and have dividing plate nozzle (2), it is characterized in that: between the adjacent separator nozzle (2) that head panel (4) is radial, leave the fit-up gap (1) within 1.0mm, adopt arc brazing in argon method to connect between radially adjoining dividing plate nozzle (2), concrete arc brazing in argon step is as follows:
A copper base solder is fixed in dividing plate nozzle (2) region to be welded by spot welding by ();
B () regulates argon arc welding welding parameter, Current Control is made to control at 2 ~ 30L/min at 5 ~ 100A, argon flow amount, the copper base solder fixing to spot welding heats, welding is started at 2mm ~ 15mm place of distance head panel (4), progressively heat copper base solder by argon arc, the fusion length formed at dividing plate nozzle (2) gap location is not more than 25mm, and weld width is not more than 8mm, ensures that regional temperature to be welded is no more than 1000 DEG C.
2. the method for attachment of a kind of oxyhydrogen engine thrust chamber header stabilizer according to claim 1, is characterized in that: described dividing plate nozzle (2) is with double-layer tube wall structure, and outer wall thickness is at 0.2 ~ 1mm.
3. the method for attachment of a kind of oxyhydrogen engine thrust chamber header stabilizer according to claim 1 and 2, is characterized in that: described dividing plate nozzle (2), with internal thread, is threaded connection at hydrogen nozzle (3) outward.
4. the method for attachment of a kind of oxyhydrogen engine thrust chamber header stabilizer according to claim 1, it is characterized in that: before carrying out arc brazing in argon, pickling, gasoline cleaning, alcohol washes pretreatment are carried out, to ensure to-be-welded region zero defect to dividing plate nozzle (2) surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210432347.4A CN102974908B (en) | 2012-11-02 | 2012-11-02 | Connection method of thrust chamber head stabilizing device of hydrogen oxygen engine |
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| CN201210432347.4A CN102974908B (en) | 2012-11-02 | 2012-11-02 | Connection method of thrust chamber head stabilizing device of hydrogen oxygen engine |
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| CN102974908A CN102974908A (en) | 2013-03-20 |
| CN102974908B true CN102974908B (en) | 2015-03-04 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103949787B (en) * | 2014-04-25 | 2016-12-07 | 甘肃虹光电子有限责任公司 | A kind of fixing means of short millimeter band coaxial manetron inner chamber decay ring |
| CN107503861B (en) * | 2017-09-12 | 2019-03-12 | 中国人民解放军战略支援部队航天工程大学 | A kind of threaded connection can blocking type rocket engine propellant bias spray panel |
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| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| RU2246025C1 (en) * | 2003-06-03 | 2005-02-10 | Открытое акционерное общество Научно-производственное объединение "Искра" | Extensible nozzle of rocket engine |
| CN101737200A (en) * | 2008-11-10 | 2010-06-16 | 北京航空航天大学 | Modularized heat-capacity type thrust chamber |
| CN102022225A (en) * | 2010-12-30 | 2011-04-20 | 北京航空航天大学 | Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector |
| CN102350574A (en) * | 2011-09-07 | 2012-02-15 | 无锡市创新化工设备有限公司 | Argon arc welding double-gun butt-welding method |
-
2012
- 2012-11-02 CN CN201210432347.4A patent/CN102974908B/en active Active
Patent Citations (6)
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| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| US6107596A (en) * | 1999-02-04 | 2000-08-22 | Otkrytoe Aktsionernoe Obschestvo "Nauchno-Proizvodstvennoe Obiedinenie "Energomash"Imeni Akademika V.P. Glushko" | Method for producing a welded-brazed combustion chamber |
| RU2246025C1 (en) * | 2003-06-03 | 2005-02-10 | Открытое акционерное общество Научно-производственное объединение "Искра" | Extensible nozzle of rocket engine |
| CN101737200A (en) * | 2008-11-10 | 2010-06-16 | 北京航空航天大学 | Modularized heat-capacity type thrust chamber |
| CN102022225A (en) * | 2010-12-30 | 2011-04-20 | 北京航空航天大学 | Test unit for hydrogen-rich/ oxygen-rich gas multinozzle gas-gas injector |
| CN102350574A (en) * | 2011-09-07 | 2012-02-15 | 无锡市创新化工设备有限公司 | Argon arc welding double-gun butt-welding method |
Non-Patent Citations (1)
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| 国外典型大推力氢氧发动机推力室技术方案综述;丁兆波等;《导弹与航天运载技术》;20120810;27-30、38 * |
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