CN105598601B - Aircraft heating system engine bleed conduit welding method - Google Patents
Aircraft heating system engine bleed conduit welding method Download PDFInfo
- Publication number
- CN105598601B CN105598601B CN201610099376.1A CN201610099376A CN105598601B CN 105598601 B CN105598601 B CN 105598601B CN 201610099376 A CN201610099376 A CN 201610099376A CN 105598601 B CN105598601 B CN 105598601B
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- Prior art keywords
- transition duct
- new
- metal
- metal bellows
- welding
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
- B23K31/02—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K37/00—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Rigid Pipes And Flexible Pipes (AREA)
Abstract
The invention belongs to welding technique, is related to the improvement to aircraft heating system engine bleed conduit welding method.Characterized in that, the step of welding, is as follows：Change the structure of transition duct and catheter sheath；Weld new transition duct (5) and metal bellows (2)；Welding metal mesh grid (3) and metal bellows (2)；Weld new transition duct (5) and new catheter sheath (6).The present invention proposes a kind of improved aircraft heating system engine bleed conduit welding method, adds the protection to welding bead, and it is cracking in the prolonged vibration environment of engine to avoid welding bead, ensure that safe to use；The release failure that fuses occurs in welding process for the twine for having prevented metal net.
Description
Technical field
The invention belongs to welding technique, is related to the improvement to aircraft heating system engine bleed conduit welding method.
Background technology
The operation principle of aircraft heating system is：It is that driving cabin and cockpit heat using engine bleed, is set on engine
In respect of bleed interface, it is necessary to be connected engine bleed mouth with heating pipeline using bleed conduit.Due to meeting when engine works
Vibration is produced, engine has Vibration Absorption Designing when mounted, if connected with hard tube, the vibration of engine will be passed by hard tube
Onto aircaft configuration, the time grown will wrap up, jeopardize aircraft safety.A kind of current aircraft heating system starts power traction
The structure of airway is referring to Fig. 1, and it is by 2, two metal nets 3 of a metal bellows, two Geju City transition ducts 1 and two
Old catheter sheath 4 forms.The maximum outside diameter of metal bellows 2 is d1, and the minimum outer diameter of metal bellows 2 is d2.Wavy metal
The assembling structure at the both ends of pipe 2 is identical, is specifically：Metal net 3 is located at the outside of metal bellows 2 and is welded as entirety, old
Catheter sheath 4 is located at the outside of metal net 3, and old transition duct 1 is that an one end carries bell-mouthed cylinder, bell-mouthed
External diameter is d1, and the termination of metal bellows 2 is welded with termination of the old transition duct 1 with bell-mouthed one end and old catheter sheath 4
Entirety is connected in, the material of above-mentioned part is stainless steel.The welding method of above-mentioned bleed conduit is：First by the end of metal bellows 2
Head diameter is processed as d1, then by old transition duct 1 with bell-mouthed one end, metal bellows 2, metal net 3 and old
Catheter sheath 4 is welded simultaneously using argon arc fusion welding.Its shortcoming is：The welding bead formed after welding is larger, unsightly, welding bead shape
There is no safeguard measure into rear outside, welding bead occurs out conduit in the prolonged vibration environment of engine in use
Split, influence safe to use.It is transition duct, metal bellows, metal knitted because metal knitted twine is thinner in welding process
Net, the thawing speed of catheter sheath are different, transition duct in welding process, metal bellows often occur, metal net, lead
Tube boot does not melt and twine fusing release failure.
The content of the invention
The purpose of the present invention is：A kind of improved aircraft heating system engine bleed conduit welding method is proposed, so as to
Increase the protection to welding bead, avoid welding bead cracking in the prolonged vibration environment of engine, influence safety；Prevent metal
The release failure that fuses occurs in welding process for the twine of mesh grid.
The technical scheme is that：Aircraft heating system engine bleed conduit welding method, the bleed welded are led
Pipe includes a transition duct of metal net 3, two of metal bellows 2, two and two catheter sheaths；Metal bellows 2
Maximum outside diameter be d1, the minimum outer diameter of metal bellows 2 is d2, and the assembling structure at the both ends of metal bellows 2 is identical, specifically
It is：Metal net 3 is located at the outside of metal bellows 2 and is welded as entirety, and catheter sheath is located at the outer of metal net 3
Face, the termination of metal bellows 2 and one end of transition duct and the termination of catheter sheath are welded as entirety, the material of above-mentioned part
For stainless steel；Characterized in that, the step of welding, is as follows：
1st, the structure of transition duct and catheter sheath is changed：The modification content of transition duct structure is：Cancel old transition to lead
The horn mouth of pipe 1, new transition duct 5 is set to turn into a cylinder, the external diameter of new transition duct 5 is d2, the wall thickness of new transition duct 5
It is identical with the wall thickness of metal bellows 2；The modification content of catheter sheath is：New catheter sheath 6 is a step cylinder, and it is by small
Diameter cylinder 6a, major diameter cylinder 6c and connection minor diameter cylinder 6a and major diameter cylinder 6c transitional cylinder 6b are formed, minor diameter cylinder 6a, transition
Cylinder 6b and major diameter cylinder 6c is integrally machined shaping, and minor diameter cylinder 6a internal diameter D2 and the gap of outside diameter d 2 of new transition duct 5 coordinate,
Minor diameter cylinder 6a length is less than the length of new transition duct 5, and major diameter cylinder 6c internal diameter D1 is outer slightly larger than metal net 3
Footpath；
2nd, new transition duct 5 and metal bellows 2 are welded：The end face of metal bellows 2 is processed first, ensures end face diameter
For d2；Then one end of the termination of metal bellows 2 and new transition duct 5 is welded as by entirety using the method for argon arc welding；
3rd, welding metal mesh grid 3 and metal bellows 2：Using the method for spot welding by metal net 3 and wavy metal
Pipe 2 is welded as entirety；
4th, new transition duct 5 and new catheter sheath 6 are welded：New catheter sheath 6 is assembled in new transition duct 5, newly led
The major diameter cylinder 6c of tube boot 6 is enclosed on the outside of metal net 3, using the method for soldering by the minor diameter of new catheter sheath 6
Cylinder 6a is welded as entirety with new transition duct 5.
It is an advantage of the invention that：A kind of improved aircraft heating system engine bleed conduit welding method is proposed, is increased
The protection to welding bead is added, it is cracking in the prolonged vibration environment of engine to avoid welding bead, ensure that safe to use；
The release failure that fuses occurs in welding process for the twine for having prevented metal net.
Brief description of the drawings
Fig. 1 is a kind of structural representation of current aircraft heating system engine bleed conduit.
Fig. 2 is the structural representation using the aircraft heating system engine bleed conduit of the inventive method welding.
Fig. 3 is the structural representation of new catheter sheath 6 in the present invention.
Embodiment
The present invention is described in further details below.Referring to Fig. 1 to Fig. 3, aircraft heating system engine bleed conduit
Welding method, the bleed conduit welded include a transition duct and two of metal net 3, two of metal bellows 2, two
Individual catheter sheath；The maximum outside diameter of metal bellows 2 is d1, and the minimum outer diameter of metal bellows 2 is d2,2 liang of metal bellows
The assembling structure at end is identical, is specifically：Metal net 3 is located at the outside of metal bellows 2 and is welded as entirety, catheter sheath
Positioned at the outside of metal net 3, the termination of metal bellows 2 and one end of transition duct and the termination of catheter sheath are welded as
Overall, the material of above-mentioned part is stainless steel；Characterized in that, the step of welding, is as follows：
1st, the structure of transition duct and catheter sheath is changed：The modification content of transition duct structure is：Cancel old transition to lead
The horn mouth of pipe 1, new transition duct 5 is set to turn into a cylinder, the external diameter of new transition duct 5 is d2, the wall thickness of new transition duct 5
It is identical with the wall thickness of metal bellows 2；The modification content of catheter sheath is：New catheter sheath 6 is a step cylinder, and it is by small
Diameter cylinder 6a, major diameter cylinder 6c and connection minor diameter cylinder 6a and major diameter cylinder 6c transitional cylinder 6b are formed, minor diameter cylinder 6a, transition
Cylinder 6b and major diameter cylinder 6c is integrally machined shaping, and minor diameter cylinder 6a internal diameter D2 and the gap of outside diameter d 2 of new transition duct 5 coordinate,
Minor diameter cylinder 6a length is less than the length of new transition duct 5, and major diameter cylinder 6c internal diameter D1 is outer slightly larger than metal net 3
Footpath；
2nd, new transition duct 5 and metal bellows 2 are welded：The end face of metal bellows 2 is processed first, ensures end face diameter
For d2；Then one end of the termination of metal bellows 2 and new transition duct 5 is welded as by entirety using the method for argon arc welding；
3rd, welding metal mesh grid 3 and metal bellows 2：Using the method for spot welding by metal net 3 and wavy metal
Pipe 2 is welded as entirety；
4th, new transition duct 5 and new catheter sheath 6 are welded：New catheter sheath 6 is assembled in new transition duct 5, newly led
The major diameter cylinder 6c of tube boot 6 is enclosed on the outside of metal net 3, using the method for soldering by the minor diameter of new catheter sheath 6
Cylinder 6a is welded as entirety with new transition duct 5.
The present invention operation principle be：
The first step, new transition duct 5 is welded together with metal bellows 2, connecting into one has flexible sealing
Pipeline.Metal bellows 2 can free bend, for the flexible connection in pipeline, reduce pipeline mount stress, new transition duct
5, which are used for pipeline, connects；
Second step, metal net 3 is welded on the first raised face at the both ends of metal bellows 2, metal net 3 is used
In protection metal bellows 2, the twine of metal net 3 is thinner, is welded to metal net 3 using the welding manner of spot welding
On first raised face at the both ends of metal bellows 2, conventional melting welding can blow twine rapidly, can not be welded；
3rd step, new catheter sheath 6 is welded in new transition duct 5, internal diameter and the new transition duct of new catheter sheath 6
5 external diameter is identical, this to be designed to ensure good fit, and welding bead is small, uniformly attractive in appearance.New catheter sheath 6 is by new transition
The welding bead of conduit 5 and metal bellows 2 protects, and prevents weld from damaged influence aircraft safety occur；
Embodiment
Metal bellows, metal net, new transition duct, the material of new catheter sheath are 1Cr18Ni9Ti stainless
Steel, there is good weldability, same material fusing point is identical, and welding performance is optimal.Metal bellows uses with new transition duct
Argon arc fusion welding, the region by new catheter sheath bag internally；Metal bellows and metal net use spot welding, and the region is new
Catheter sheath bag is internally；Metal bellows uses soldering with new transition duct.The conduit welding bead being processed using the present invention
It is small, it is uniformly attractive in appearance, there is enough intensity and soft readjustment function.
Claims (1)
1. aircraft heating system engine bleed conduit welding method, the bleed conduit welded includes a metal bellows
(2), two metal nets (3), two transition ducts and two catheter sheaths；The maximum outside diameter of metal bellows (2) is d1,
The minimum outer diameter of metal bellows (2) is d2, and the assembling structure at metal bellows (2) both ends is identical, is specifically：Metal net
(3) it is located at outside metal bellows (2) and is welded as entirety, catheter sheath is located at the outside of metal net (3), metal wave
The termination and one end of transition duct of line pipe (2) and the termination of catheter sheath are welded as entirety, and the material of above-mentioned part is stainless
Steel；Characterized in that, the step of welding, is as follows：
1.1st, the structure of transition duct and catheter sheath is changed：The modification content of transition duct structure is：Cancel old transition duct
(1) horn mouth, new transition duct (5) is made to turn into a cylinder, the external diameter of new transition duct (5) is d2, new transition duct (5)
Wall thickness it is identical with the wall thickness of metal bellows (2)；The modification content of catheter sheath is：New catheter sheath (6) is a step
Cylinder, it is by minor diameter cylinder (6a), major diameter cylinder (6c) and the transitional cylinder of connection minor diameter cylinder (6a) and major diameter cylinder (6c)
(6b) is formed, and minor diameter cylinder (6a), transitional cylinder (6b) and major diameter cylinder (6c) are integrally machined shaping, the internal diameter of minor diameter cylinder (6a)
D2 and the gap of outside diameter d 2 of new transition duct (5) coordinate, and the length of minor diameter cylinder (6a) is less than the length of new transition duct (5),
The internal diameter D1 of major diameter cylinder (6c) is slightly larger than the external diameter of metal net (3)；
1.2nd, new transition duct (5) and metal bellows (2) are welded：The end face of metal bellows (2) is processed first, ensures end face
A diameter of d2；Then the termination of metal bellows (2) and one end of new transition duct (5) are welded as using the method for argon arc welding
It is overall；
1.3rd, welding metal mesh grid (3) and metal bellows (2)：Using the method for spot welding by metal net (3) and metal
Bellows (2) is welded as entirety；
1.4th, new transition duct (5) and new catheter sheath (6) are welded：New catheter sheath (6) is assembled to new transition duct (5)
On, the major diameter cylinder (6c) of new catheter sheath (6) is enclosed on the outside of metal net (3), using the method for soldering by new conduit
The minor diameter cylinder (6a) of sheath (6) is welded as entirety with new transition duct (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610099376.1A CN105598601B (en) | 2016-02-23 | 2016-02-23 | Aircraft heating system engine bleed conduit welding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610099376.1A CN105598601B (en) | 2016-02-23 | 2016-02-23 | Aircraft heating system engine bleed conduit welding method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105598601A CN105598601A (en) | 2016-05-25 |
| CN105598601B true CN105598601B (en) | 2018-01-16 |
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ID=55979219
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610099376.1A Active CN105598601B (en) | 2016-02-23 | 2016-02-23 | Aircraft heating system engine bleed conduit welding method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105598601B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110465717B (en) * | 2019-06-28 | 2022-04-22 | 秦皇岛市泰德管业科技有限公司 | TIG arc brazing welding method |
| CN113864057A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Air-entraining structure in double-layer casing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2670609Y (en) * | 2003-08-12 | 2005-01-12 | 董菁荣 | Flexible metal bellows of vehicle exhaust pipe |
| CN201475531U (en) * | 2009-09-02 | 2010-05-19 | 航天晨光股份有限公司 | Oxygen blast metal hose |
| CN203215122U (en) * | 2013-03-23 | 2013-09-25 | 浙江鸿森机械有限公司 | Double-welded corrugated pipe with single welding spot |
| CN203703441U (en) * | 2013-12-01 | 2014-07-09 | 太原航空仪表有限公司 | Bellow type universal joint |
| CN204572155U (en) * | 2014-12-30 | 2015-08-19 | 浙江乐鼎波纹管有限公司 | Protection type flexible corrugated pipe for automobile exhaustion |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101260229B1 (en) * | 2011-11-03 | 2013-05-03 | 신동해(주) | Vibration-absorbing tube for refrigerating compressor |
-
2016
- 2016-02-23 CN CN201610099376.1A patent/CN105598601B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2670609Y (en) * | 2003-08-12 | 2005-01-12 | 董菁荣 | Flexible metal bellows of vehicle exhaust pipe |
| CN201475531U (en) * | 2009-09-02 | 2010-05-19 | 航天晨光股份有限公司 | Oxygen blast metal hose |
| CN203215122U (en) * | 2013-03-23 | 2013-09-25 | 浙江鸿森机械有限公司 | Double-welded corrugated pipe with single welding spot |
| CN203703441U (en) * | 2013-12-01 | 2014-07-09 | 太原航空仪表有限公司 | Bellow type universal joint |
| CN204572155U (en) * | 2014-12-30 | 2015-08-19 | 浙江乐鼎波纹管有限公司 | Protection type flexible corrugated pipe for automobile exhaustion |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105598601A (en) | 2016-05-25 |
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