CN102528197A - Brazing method for titanium alloy injector of two-component thruster - Google Patents
Brazing method for titanium alloy injector of two-component thruster Download PDFInfo
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- CN102528197A CN102528197A CN2011103617847A CN201110361784A CN102528197A CN 102528197 A CN102528197 A CN 102528197A CN 2011103617847 A CN2011103617847 A CN 2011103617847A CN 201110361784 A CN201110361784 A CN 201110361784A CN 102528197 A CN102528197 A CN 102528197A
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- brazing
- titanium alloy
- tapered hole
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Abstract
The invention discloses a brazing method for a titanium alloy injector of a two-component thruster. A brazing seam is arranged in the mode of matching a straight pipe with a tapered hole, the straight pipe is in interference fit with the bottom of the tapered hole, and a reinforcing process method after brazing heat insulation is added. By introducing the structure of the tapered hole and the reinforcing process after brazing heat insulation, self-alignment of a propellant pipeline in assembly is ensured, and welding flux is prevented from blocking a channel. Besides, by controlling the taper of a hole wall, the brazing seam is effectively welded together, so that the problem of reduction of local strength of the brazing seam due to circumferentially uneven gaps is avoided, brazing reliability of the injector is improved, the risk of propellant leakage of the injector is basically eliminated, and uniformity of performances of products is improved.
Description
Technical field
The invention belongs to the space structure processing technique field, particularly a kind of novel braze welding method that is used for double elements thruster titanium alloy ejector filler.
Background technology
The double elements thruster is the main reaction force execution unit of spacecraft attitude control, produces thrust through ejection high temperature, high-speed fuel gas, keeps spacecraft attitude control and track to shift.Wherein ejector filler is the critical component that the double elements thruster is realized propellant feed, atomizing, and its performance directly has influence on the thruster machine performance.At present, double elements thruster ejector filler is because number of parts is more, and the vacuum brazing modes that adopt connect more between the part, and solder joint quantity is a lot.Soldering between the straight tube of particularly existing ejector filler propellant runner and flange and the spray assembly; Adopt straight tube and circular hole Type of Welding; Its fit clearance is difficult to control, and the centering accuracy is difficult to guarantee, can cause the existence of ejector filler runner to cause the risk of leaking because of the solder joint undercapacity.
Sealing requirements for thruster in the space industry is very high; And vacuum brazing requires very high for fit clearance and welding condition; And intensity is lower; Lack effective nondestructiving detecting means and effectively criterion at present, solder joint exists because of undercapacity, can not tolerate the risk that spacecraft is launched and the high-intensity oscillation of satellite and the rocket separation phase leaks.To leak in case the ejector filler weld seam takes place, then will directly cause whole thruster to lose efficacy, even have and cause whole propulsion subsystem to lose efficacy, so the risk of whole spacecraft inefficacy.Therefore, solve the low problem of double elements thruster titanium alloy ejector filler weld strength, the risk of stopping a leak has important and practical meanings at space industry.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the prior art deficiency, the method for welding that a kind of solder joint intensity is high, the fit clearance scope of application is wideer, the assembling simple, reliability is high is provided.
Technical solution of the present invention is, a kind of method for welding that is used for double elements thruster titanium alloy ejector filler may further comprise the steps: step 1, solder joint are set to straight tube and tapered hole fit form, and straight tube and tapered hole bottom are interference fit; Step 2, the filled welding; Step 3, insulation is 3-20 minute between 900 ℃-1000 ℃; Step 4, between 850 ℃-950 ℃ intensive treatment 3-10 hour; Step 5 is cooled off with stove.
The range of taper of tapered hole is 1 in the said step 1: 20-1: 100.
Holding temperature in the said step 3 is 900 ℃-1000 ℃, and temperature retention time is 3-20 minute.
Reinforcement temperature in the said step 4 is 850 ℃-950 ℃, and the intensive treatment time is 3-10 hour.
The present invention's advantage compared with prior art is:
(1) the present invention's solder joint is set to straight tube and tapered hole fit form; Straight tube and tapered hole bottom are interference fit; When having guaranteed the assembling of propellant pipeline from centering, guarantee not blocking channel of scolder, the tapering of control hole wall; Guarantee the effective seam of solder joint, thereby avoided because of the circumferential inhomogeneous solder joint local strength decline problem that causes in gap.
(2) through increasing the strengthening treatment process method after soldering is incubated; Guaranteed (all can guarantee welding line structure intensity in 0.01～0.12mm) in a big way in fit clearance; Improve ejector filler soldering reliability, eliminated the risk of ejector filler propellant leakage basically.
(3) the present invention is through introducing the strengthening treatment process method after tapered hole structure and soldering are incubated; Guaranteed between the axle of hole from centering; And the scope of application for fit clearance is wideer, thereby has reduced the assembly difficulty of ejector filler, has improved the performance of products uniformity.
Description of drawings
Fig. 1 is a novel braze welding structural representation of the present invention;
Fig. 2 is the weld seam partial enlarged drawing;
Fig. 3 is the soldering processes schematic flow sheet of embodiment.
The specific embodiment
Further describe in detail below in conjunction with the accompanying drawing specific embodiments of the invention.In the present embodiment, the solder joint that cooperates with circular hole with three place's straight tubes of double elements thruster titanium alloy ejector filler is an example.
As shown in Figure 1,1,2,3 is the solder joint position that the ejector filler three place straight tubes relevant with the propellant runner cooperate with circular hole.
At first, this three places braze-welded structure is changed to straight tube 4, tapered hole 5 fit structures, straight tube 4 is an interference fit with the bottom of tapered hole 5, is 2mm-3mm through tapered hole 5 degree of depth are set, and guarantees that fit clearance is 0.01mm～0.12mm between the two.
As shown in Figure 2, the straight tube 4 at solder joint place remains unchanged, and the tapering of tapered hole 5 is 1: 20-1: between 100, and can be according to the different choice of welding material.In the present embodiment, tapering is selected 1: 70.During assembling, because the effect of tapered hole, straight tube and tapered hole bottom are interference fit, can realize straight tube nature centering, thereby have guaranteed the circumferential uniformity of solder joint.
After filled welding is accomplished, carrying out intensive treatment again after insulation a period of time under certain high temperature.Usually, according to the macroscopic property of titanium alloy material commonly used, and the braze melt temperature that is applicable to this material, the holding temperature scope is 900 ℃-1000 ℃, temperature retention time 3-20 minute; 850 ℃-950 ℃ of intensive treatment temperature, 3-10 hour intensive treatment time.In the present embodiment, welding material high-temperature titanium alloy material is selected 950 ℃ of its holding temperatures, temperature retention time 5 minutes; 900 ℃ of intensive treatment temperature, 8 hours intensive treatment time.Then weldment is cooled off with stove.
As shown in Figure 3, be the soldering processes schematic flow sheet of embodiment.
Through engineer testing to soldering after the strength of materials detect, in the present embodiment, adopt welding method of the present invention, shear strength is greater than 200MPa in the scope of fit clearance 0.01mm～0.12mm.
Certainly, under the situation that does not change its function, the equivalent transformation that carries out or alternative also falls into protection scope of the present invention to each building block of the present invention, position relation and connected mode.
The content of not doing to describe in detail in the specification of the present invention belongs to this area professional and technical personnel's known technology.
Claims (4)
1. a method for welding that is used for double elements thruster titanium alloy ejector filler is characterized in that, may further comprise the steps:
Step 1, solder joint are set to straight tube and tapered hole fit form, and straight tube and tapered hole bottom are interference fit;
Step 2, the filled welding;
Step 3, insulation is 3-20 minute between 900 ℃-1000 ℃;
Step 4, between 850 ℃-950 ℃ intensive treatment 3-10 hour;
Step 5 is cooled off with stove.
2. according to a kind of method for welding that is used for double elements thruster titanium alloy ejector filler of claim 1, it is characterized in that: the range of taper of tapered hole is 1 in the said step 1: 20-1: 100.
3. according to a kind of method for welding that is used for double elements thruster titanium alloy ejector filler of claim 1, it is characterized in that: the holding temperature in the said step 3 is 900 ℃-1000 ℃, and temperature retention time is 3-20 minute.
4. according to a kind of method for welding that is used for double elements thruster titanium alloy ejector filler of claim 1, it is characterized in that: the reinforcement temperature in the said step 4 is 850 ℃-950 ℃, and the intensive treatment time is 3-10 hour.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103617847A CN102528197A (en) | 2011-11-15 | 2011-11-15 | Brazing method for titanium alloy injector of two-component thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011103617847A CN102528197A (en) | 2011-11-15 | 2011-11-15 | Brazing method for titanium alloy injector of two-component thruster |
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| CN102528197A true CN102528197A (en) | 2012-07-04 |
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| CN2011103617847A Pending CN102528197A (en) | 2011-11-15 | 2011-11-15 | Brazing method for titanium alloy injector of two-component thruster |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662095A (en) * | 2013-12-20 | 2014-03-26 | 北京控制工程研究所 | Injector used for double-component attitude control thruster |
| CN106956053A (en) * | 2017-03-06 | 2017-07-18 | 东莞市迈纳斯航空技术有限公司 | A kind of vacuum brazing method of titanium alloy pipeline |
| CN107335880A (en) * | 2017-06-15 | 2017-11-10 | 湖北汉光科技股份有限公司 | The processing method of high-power klystron microwave output window closure |
| CN108581396A (en) * | 2018-06-21 | 2018-09-28 | 湖北三江航天江北机械工程有限公司 | Using the showerhead injector processing method of fine duct |
| CN113305390A (en) * | 2021-05-26 | 2021-08-27 | 成立航空股份有限公司 | Vacuum brazing method for interference fit clearance |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50145363A (en) * | 1974-05-15 | 1975-11-21 | ||
| JPH03138080A (en) * | 1989-10-20 | 1991-06-12 | Showa Alum Corp | Manufacture of tube with plate fin |
| CN1821552A (en) * | 2005-01-31 | 2006-08-23 | 三菱重工业株式会社 | Method for manufacturing variable-throat exhaust turbocharger and constituent members of nozzle throat area varying mechanism |
| CN1891389A (en) * | 2005-09-23 | 2007-01-10 | 深圳市宝安联华实业有限公司 | Method for realizing brazing in metal straight pipe, and its special apparatus |
-
2011
- 2011-11-15 CN CN2011103617847A patent/CN102528197A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50145363A (en) * | 1974-05-15 | 1975-11-21 | ||
| JPH03138080A (en) * | 1989-10-20 | 1991-06-12 | Showa Alum Corp | Manufacture of tube with plate fin |
| CN1821552A (en) * | 2005-01-31 | 2006-08-23 | 三菱重工业株式会社 | Method for manufacturing variable-throat exhaust turbocharger and constituent members of nozzle throat area varying mechanism |
| CN1891389A (en) * | 2005-09-23 | 2007-01-10 | 深圳市宝安联华实业有限公司 | Method for realizing brazing in metal straight pipe, and its special apparatus |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662095A (en) * | 2013-12-20 | 2014-03-26 | 北京控制工程研究所 | Injector used for double-component attitude control thruster |
| CN106956053A (en) * | 2017-03-06 | 2017-07-18 | 东莞市迈纳斯航空技术有限公司 | A kind of vacuum brazing method of titanium alloy pipeline |
| CN107335880A (en) * | 2017-06-15 | 2017-11-10 | 湖北汉光科技股份有限公司 | The processing method of high-power klystron microwave output window closure |
| CN107335880B (en) * | 2017-06-15 | 2019-10-01 | 湖北汉光科技股份有限公司 | The processing method of high-power klystron microwave output window closure |
| CN108581396A (en) * | 2018-06-21 | 2018-09-28 | 湖北三江航天江北机械工程有限公司 | Using the showerhead injector processing method of fine duct |
| CN113305390A (en) * | 2021-05-26 | 2021-08-27 | 成立航空股份有限公司 | Vacuum brazing method for interference fit clearance |
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Application publication date: 20120704 |