CN102974908A - 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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- CN102974908A CN102974908A CN2012104323474A CN201210432347A CN102974908A CN 102974908 A CN102974908 A CN 102974908A CN 2012104323474 A CN2012104323474 A CN 2012104323474A CN 201210432347 A CN201210432347 A CN 201210432347A CN 102974908 A CN102974908 A CN 102974908A
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- dividing plate
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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 the oxyhydrogen engine head construction, be specifically related to a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer.
Background technology
Exist violent physical and chemical changes during the liquid rocket engine thrust chamber internal combustion, will cause the high-frequency combustion instability of thrust chamber, cause serious consequence, especially the tangential rough burning phenomenon of high frequency.The rough burning of inhibition high frequency is an important and complicated key technology in the liquid-propellant rocket engine development, also is the maximum risk place of rocket development.
Mainly adopt in the world the devices such as dividing plate, the operatic tunes, quarter-wave pipe and helmholtz resonance device to suppress the thrust chamber rough burning.As shown in Figure 1, several hydrogen nozzle 3 that is circular layout and oxygen nozzles 5 of assembling on the head panel 4 of oxyhydrogen engine thrust chamber head, wherein hydrogen nozzle 3 is placed in outside the oxygen nozzle 5, above head panel 4, outer also the overlapping of hydrogen nozzle 3 and oxygen nozzle 5 have dividing plate nozzle 2.But in the prior art, dividing plate nozzle 2 for being adhesively fixed, comes off under high-temperature work environment each other easily, causes the rough burning of thrust chamber high frequency to occur.
Summary of the invention
Purpose of the present invention provides a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, and it is applied to copper base solder in the argon arc soldering field, and technique is simple, reliability is high, constant product quality, production efficiency high.
Realize the technical scheme of the object of the invention: a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, wherein at the assembling of head panel several hydrogen nozzle that is circular layout and oxygen nozzles, the hydrogen nozzle is placed in outside the oxygen nozzle; Also cover has the dividing plate nozzle above the head panel, outside hydrogen nozzle and the oxygen nozzle, it leaves 1.0mm with interior fit-up gap between head panel adjacent separator nozzle radially, adopt the argon arc method for welding to connect between the radially adjoining dividing plate nozzle, concrete argon arc soldering step is as follows:
(a) copper base solder is fixed in the dividing plate nozzle zone to be welded by spot welding;
(b) regulate the argon arc welding welding parameter, make Current Control be controlled at 2 ~ 30L/min at 5 ~ 100A, argon flow amount, the copper base solder fixing to spot welding heats, begin welding at the 2mm of distance head panel～15mm place, progressively by argon arc heating copper base solder, the fusion length that forms at dividing plate nozzle gap place is not more than 25mm, and weld width is not more than 8mm, guarantees that regional temperature to be welded is no more than 1000 ℃.
The method of attachment of aforesaid a kind of oxyhydrogen engine thrust chamber header stabilizer, its described dividing plate nozzle is with double-layer tube wall structure, and outer wall thickness is at 0.2 ~ 1mm.
The method of attachment of aforesaid a kind of oxyhydrogen engine thrust chamber header stabilizer, its described dividing plate nozzle is threaded connection outside the hydrogen nozzle with internal thread.
The method of attachment of aforesaid a kind of oxyhydrogen engine thrust chamber header stabilizer, it carries out pickling, gasoline cleaning, alcohol wash preliminary treatment to the dividing plate nozzle surface, to guarantee the to-be-welded region zero defect before carrying out the argon arc soldering.
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 the argon arc soldering field, and this technology is applied to the connection of power chamber header stabilizer, solved the technical problem of oxyhydrogen engine thrust chamber head high frequency rough burning.The thrust chamber header stabilizer of manufacturing of the present invention has improved production efficiency and product quality.
Median septum nozzle of the present invention is with double-layer tube wall structure, and center-aisle helps heat to shed, and its outer wall thickness is thinner at 0.2 ~ 1mm, and general solder technology can't realize stable the connection, the penetration clogging occurs easily.Adopt argon arc method for welding of the present invention and related process parameter, can effectively weld, the welding large deformation is for follow-up head steady provides stable reliability.
Compare with common argon arc fusion welding, the argon arc soldering has that deflection is little, and the heat affected area degree of superheat is low, again can be by the control welding variables, heat input when regulating easily and flexibly solder shape seam, this is with a wide range of applications at aspects such as welding precision component, thin-walled materials.
Description of drawings
Fig. 1 is oxyhydrogen engine header stabilizer structural representation;
Fig. 2 is that the A-A of Fig. 1 is to cutaway view;
Fig. 3 is dividing plate nozzle arrangements schematic diagram.
Among the figure: 1. fit-up gap; 2. dividing plate nozzle; 3. hydrogen nozzle; 4. head panel; 5. oxygen nozzle.
The specific embodiment
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.
As depicted in figs. 1 and 2, a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, wherein at head panel 4 assembling several hydrogen nozzle 3 that is circular layout and oxygen nozzles 5, hydrogen nozzle 3 is placed in outside the oxygen nozzle 5, and also cover has dividing plate nozzle 2 above head panel 4, outside hydrogen nozzle 3 and the oxygen nozzle 5.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 is threaded connection outside hydrogen nozzle 3 with internal thread.
Leave 1.0mm with interior fit-up gap 1 between head panel adjacent separator nozzle 2 radially, then adopt the argon arc method for welding to connect between the radially adjoining dividing plate nozzle 2, concrete argon arc soldering step is as follows:
(a) copper base solder is fixed in dividing plate nozzle 2 zones to be welded by spot welding;
(b) regulate the argon arc welding welding parameter, make Current Control be controlled at 15L/min at 50A, argon flow amount, the copper base solder fixing to spot welding heats, begin welding at distance head panel 10mm place, progressively by argon arc heating copper base solder, the fusion length that forms at dividing plate nozzle 2 gap locations is not more than 25mm, and weld width is not more than 8mm, guarantees that regional temperature to be welded is no more than 1000 ℃.
Above-mentioned carry out the argon arc soldering before, dividing plate nozzle 2 surfaces are carried out pickling, gasoline are cleaned, the alcohol wash preliminary treatment, to guarantee the to-be-welded region zero defect.
As depicted in figs. 1 and 2, a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, wherein at head panel 4 assembling several hydrogen nozzle 3 that is circular layout and oxygen nozzles 5, hydrogen nozzle 3 is placed in outside the oxygen nozzle 5, and also cover has dividing plate nozzle 2 above head panel 4, outside hydrogen nozzle 3 and the oxygen nozzle 5.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 is threaded connection outside hydrogen nozzle 3 with internal thread.
Leave 1.0mm with interior fit-up gap 1 between head panel adjacent separator nozzle 2 radially, then adopt the argon arc method for welding to connect between the radially adjoining dividing plate nozzle 2, concrete argon arc soldering step is as follows:
(a) copper base solder is fixed in dividing plate nozzle 2 zones to be welded by spot welding;
(b) regulate the argon arc welding welding parameter, make Current Control be controlled at 2L/min at 5A, argon flow amount, the copper base solder fixing to spot welding heats, begin welding at distance head panel 2mm place, progressively by argon arc heating copper base solder, the fusion length that forms at dividing plate nozzle 2 gap locations is not more than 25mm, and weld width is not more than 8mm, guarantees that regional temperature to be welded is no more than 1000 ℃.
Above-mentioned carry out the argon arc soldering before, dividing plate nozzle 2 surfaces are carried out pickling, gasoline are cleaned, the alcohol wash preliminary treatment, to guarantee the to-be-welded region zero defect.
As depicted in figs. 1 and 2, a kind of method of attachment of oxyhydrogen engine thrust chamber header stabilizer, wherein at head panel 4 assembling several hydrogen nozzle 3 that is circular layout and oxygen nozzles 5, hydrogen nozzle 3 is placed in outside the oxygen nozzle 5, and also cover has dividing plate nozzle 2 above head panel 4, outside hydrogen nozzle 3 and the oxygen nozzle 5.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 is threaded connection outside hydrogen nozzle 3 with internal thread.
Leave 1.0mm with interior fit-up gap 1 between head panel adjacent separator nozzle 2 radially, then adopt the argon arc method for welding to connect between the radially adjoining dividing plate nozzle 2, concrete argon arc soldering step is as follows:
(a) copper base solder is fixed in dividing plate nozzle 2 zones to be welded by spot welding;
(b) regulate the argon arc welding welding parameter, make Current Control be controlled at 30L/min at 100A, argon flow amount, the copper base solder fixing to spot welding heats, begin welding at distance head panel 15mm place, progressively by argon arc heating copper base solder, the fusion length that forms at dividing plate nozzle 2 gap locations is not more than 25mm, and weld width is not more than 8mm, guarantees that regional temperature to be welded is no more than 1000 ℃.
Above-mentioned carry out the argon arc soldering before, dividing plate nozzle 2 surfaces are carried out pickling, gasoline are cleaned, the alcohol wash preliminary treatment, to guarantee the to-be-welded region zero defect.
Claims (4)
1. the method for attachment of an oxyhydrogen engine thrust chamber header stabilizer, wherein at head panel (4) assembling several hydrogen nozzle (3) that is circular layout and oxygen nozzles (5), wherein hydrogen nozzle (3) is placed in outside the oxygen nozzle (5); Also cover has dividing plate nozzle (2) outside head panel (4) top, hydrogen nozzle (3) and oxygen nozzle (5), it is characterized in that: between head panel (4) adjacent separator nozzle (2) radially, leave 1.0mm with interior fit-up gap (1), adopt the argon arc method for welding to connect between the radially adjoining dividing plate nozzle (2), concrete argon arc soldering step is as follows:
(a) copper base solder is fixed in dividing plate nozzle (2) zone to be welded by spot welding;
(b) regulate the argon arc welding welding parameter, make Current Control be controlled at 2 ~ 30L/min at 5 ~ 100A, argon flow amount, the copper base solder fixing to spot welding heats, begin welding at the 2mm of distance head panel (4) ~ 15mm place, progressively by argon arc heating copper base solder, the fusion length that forms at dividing plate nozzle (2) gap location is not more than 25mm, and weld width is not more than 8mm, guarantees that regional temperature to be welded is no more than 1000 ℃.
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) is threaded connection outside hydrogen nozzle (3) with internal thread.
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 the argon arc soldering, pickling, gasoline cleaning, alcohol wash preliminary treatment are carried out in dividing plate nozzle (2) surface, to guarantee the to-be-welded region zero defect.
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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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| CN102974908B CN102974908B (en) | 2015-03-04 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103949787A (en) * | 2014-04-25 | 2014-07-30 | 甘肃虹光电子有限责任公司 | Method for fixing inner cavity of short millimeter wave band coaxial magnetron and damping ring |
| CN107503861A (en) * | 2017-09-12 | 2017-12-22 | 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 biasing spray panel |
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2012
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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 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103949787A (en) * | 2014-04-25 | 2014-07-30 | 甘肃虹光电子有限责任公司 | Method for fixing inner cavity of short millimeter wave band coaxial magnetron and damping ring |
| 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 |
| CN107503861A (en) * | 2017-09-12 | 2017-12-22 | 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 biasing spray panel |
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| CN102974908B (en) | 2015-03-04 |
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