CN106271298B - Airplane turbine spiral case nozzle connection ring welding fixture - Google Patents
Airplane turbine spiral case nozzle connection ring welding fixture Download PDFInfo
- Publication number
- CN106271298B CN106271298B CN201510296593.5A CN201510296593A CN106271298B CN 106271298 B CN106271298 B CN 106271298B CN 201510296593 A CN201510296593 A CN 201510296593A CN 106271298 B CN106271298 B CN 106271298B
- Authority
- CN
- China
- Prior art keywords
- connection ring
- nozzle connection
- expansion tube
- welding fixture
- central shaft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- 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
- B23K37/04—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups for holding or positioning work
- B23K37/0426—Fixtures for other work
- B23K37/0435—Clamps
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- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The present invention relates to welding fixture technical field,A kind of more particularly to airplane turbine spiral case nozzle connection ring welding fixture,Including the base for contradicting outlet nozzle end face,Central shaft is vertically arranged with the middle part of base,Center outer shaft sleeve is connected to the guide post for limiting outlet nozzle inner circle,Support plate,Nozzle connection ring expansion tube is provided with the upside of support plate,Nozzle connection ring expansion tube includes two semi-circular bulging blocks being separated from each other,Nozzle connection ring expansion tube is socketed on outside central shaft,Cone tank is provided with the middle part of nozzle connection ring expansion tube,Be provided with above nozzle connection ring expansion tube for by two bulging blocks to the separated compression bar in both sides,Compression bar is socketed on outside central shaft,The upper end of compression bar is provided with clamp nut,Clamp nut is connected with central axle threads,Scientific structure of the present invention,Locking spray nozzle connection ring is horizontally outward separated by two bulging blocks,It is fixed,It ensure that welding quality.
Description
Technical field
The present invention relates to welding fixture technical field, more particularly to a kind of airplane turbine spiral case nozzle connection ring weld clip
Tool.
Background technology
In aviation field, turbocharging technology has applied more than 100 years, and turbine mainly by turbocharger and gives up
The shaft that air turbine composition, turbocharger and exhaust gas turbine are connected with impeller by both ends is attached, and works as engine combustion
The fuel in storehouse produced after fully burning the exhaust gas of high pressure-temperature, and exhaust gas enters the impeller in exhaust gas turbine promotion exhaust gas turbine
Rotate, so as to drive the impeller in turbocharger, rotation produces very big negative pressure to the impeller in turbocharger at a high speed, will be outer
It is compressed in the air suction turbocharger on boundary, obtains the air of high temperature and pressure, the air of high temperature and pressure enters engine
Combustion bin burns, so circulation, in cycles.
Scientific and technical personnel propose a kind of new turbocharger, see attached drawing 1, it mainly includes such as lower component：Turbocharging
Device body, the body include turbine shroud 01, set the cavity that can accommodate impeller in turbine shroud 01, the lower section of turbine shroud 01 is opened
Nozzle connection ring 02 is equipped with mouthful, the lower section of nozzle connection ring 02 is equipped with outlet nozzle 03, and outlet nozzle 03 passes through anti-icing gas shell
Body is connected with turbine shroud 01, and the other end of turbine shroud 01 is provided with flange 04.
Traditional turbocharger is due to needing the environment for bearing prolonged high temperature and high pressure to be carried out mostly using cast iron
Forging, but the overall cast iron forging technology that carries out is complicated, qualification rate is low, and in order to overcome the above problem, scientific and technical personnel attempt to use aluminium
Lumber is forged instead of cast iron, reduces the weight of product, its technique is used and is welded to connect, but in actual application
It was found that aluminium sheet welding is easily deformed, the size finally obtained is greatly shunk.According to technological requirement, it is necessary to ensure nozzle connection ring
02nd, outlet nozzle 03, three part concentricitys of flange of turbine shroud 01 are not more than 0.04, and 02 side of nozzle connection ring is extremely
The range error of the flange of turbine shroud 01 is less than 0.1mm, is difficult to ensure that during actual welding, seriously affect product matter
Amount.
The content of the invention
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to and provide a kind of airplane turbine spiral case nozzle connection boxing
Welding fixture, its scientific structure, locking spray nozzle connection ring is horizontally outward separated by two bulging blocks, fixed, ensure that weldering
Connect quality.
The technical solution adopted by the present invention to solve the technical problems is：A kind of airplane turbine spiral case nozzle connection ring welding
Fixture, it includes being used for the base for contradicting outlet nozzle end face, and central shaft, the center are vertically arranged with the middle part of the base
Outer shaft sleeve be connected to for limit outlet nozzle inner circle guide post, support plate, it is swollen to be provided with nozzle connection ring on the upside of the support plate
Tube expansion, the nozzle connection ring expansion tube include two semi-circular bulging blocks being separated from each other, the nozzle connection ring expansion tube
It is socketed on outside the central shaft, cone tank, the nozzle connection ring expansion tube is provided with the middle part of the nozzle connection ring expansion tube
Top is provided with for described two bulging blocks to be socketed on outside the central shaft to the separated compression bar in both sides, the compression bar, institute
The upper end for stating compression bar is provided with clamp nut, and the clamp nut is connected with the central axle threads.
Further, the outside diameter of the guide post is equal with the internal diameter of the outlet nozzle.
Further, the bulging block bottom is provided with first convex for stretch into the annular groove in the middle part of nozzle connection ring
Edge.
Further, the thickness of first flange is less than the width of the annular groove.
Further, when the compression bar comes downwards to extreme lower position, first flange of bulging block contradicts the annular groove
Bottom.
Further, be provided with the top of the bulging block for limit the nozzle connection ring end circular hole inner circle second
Flange.
Further, the bulging block is provided with for forming the cone tank half close to the side of the central shaft
Inclined hole, the inclined hole upside are provided with the straight hole for being oriented to for the compression bar.
The beneficial effects of the invention are as follows：A kind of airplane turbine spiral case nozzle connection ring welding fixture, it includes being used to contradict
The base of outlet nozzle end face, central shaft is vertically arranged with the middle part of the base, and the center outer shaft sleeve is connected to for limiting
The guide post of outlet nozzle inner circle, support plate, the support plate upside are provided with nozzle connection ring expansion tube, the nozzle connection ring
Fixing device includes two semi-circular bulging blocks being separated from each other, and the nozzle connection ring expansion tube is socketed on the central shaft
Outside, cone tank is provided with the middle part of the nozzle connection ring expansion tube, is provided with above the nozzle connection ring expansion tube for inciting somebody to action
Described two bulging blocks are socketed on outside the central shaft to the separated compression bar in both sides, the compression bar, and the upper end of the compression bar is set
There is clamp nut, the clamp nut is connected with the central axle threads, scientific structure of the present invention, horizontal by two bulging blocks
Outwards separation locking spray nozzle connection ring, it is fixed, it ensure that welding quality.
Brief description of the drawings
Fig. 1 is the structure diagram for the airplane turbine spiral case that the present invention processes.
Fig. 2 is the airplane turbine spiral case nozzle connection ring welding fixture of the present invention.
Fig. 3 is the structure diagram of bulging block in Fig. 2.
Description of reference numerals：
1 --- central shaft
2 --- base
3 --- guide post
4 --- support plate
5 --- bulging block
51 --- the first flange
52 --- the second flange
53 --- inclined hole
54 --- straight hole
6 --- compression bar
7 --- clamp nut.
Embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings, is not the reality the present invention
Apply scope limited to this.
As shown in Figure 2 and Figure 3, the airplane turbine spiral case nozzle connection ring welding fixture of the present embodiment, it includes being used to contradict
The base 2 of outlet nozzle end face, the middle part of the base 2 are vertically arranged with central shaft 1, are socketed with and are used for outside the central shaft 1
Guide post 3, the support plate 4 of outlet nozzle inner circle are limited, the upside of support plate 4 is provided with nozzle connection ring expansion tube, the spray
Mouth connection ring expansion tube includes two semi-circular bulging blocks 5 being separated from each other, and the nozzle connection ring expansion tube is socketed on described
Outside central shaft 1, cone tank is provided with the middle part of the nozzle connection ring expansion tube, is provided with above the nozzle connection ring expansion tube
For described two bulging blocks 5 to be socketed on outside the central shaft 1 to the separated compression bar 6 in both sides, the compression bar 6, the compression bar 6
Upper end be provided with clamp nut 7, the clamp nut 7 is threadedly coupled with the central shaft 1, in use, by airplane turbine snail
The outlet nozzle of shell is placed on downwards on base 2, and outlet nozzle is socketed on outside guide post 3, then nozzle connection ring is put into from top
In turbine volute, nozzle connection ring is socketed on outside the nozzle connection ring expansion tube, when tightening clamp nut 7, clamp nut 7
Move downward, promote compression bar 6 also to move downward, since support plate 4 supports bulging block 5, effect of the bulging block 5 in compression bar 6 upwards
Under move out in the horizontal direction so that nozzle connection ring, which is fixed, makes it not move, then from top by nozzle connection ring
Weld together with turbine volute, the inventive structure science, locking spray nozzle connection is horizontally outward separated by two bulging blocks 5
Ring, it is fixed, it ensure that welding quality.
Further, the outside diameter of the guide post 3 is equal with the internal diameter of the outlet nozzle, can limit turbine volute level
The displacement in direction, so as to ensure outlet nozzle, the concentricity of nozzle connection ring.
Further, 5 bottom of bulging block be provided with for stretch into the annular groove in the middle part of nozzle connection ring first
Flange 51, the diameter of the annular groove is big, and the diameter of other parts is small, can be with by the first flange 51 for moving horizontally outward
Stretch into the annular groove, and then pass through the annular groove fixed nozzle connection ring.
Further, the thickness of first flange 51 is less than the width of the annular groove, avoids the first flange 51 from blocking
In the annular groove.
Further, when the compression bar 6 comes downwards to extreme lower position, 5 first flange 51 of bulging block contradicts the annular
The bottom of groove, i.e., diametrically contradict the annular groove, so that clamping nozzle connection ring.
Further, the top of the bulging block 5 be provided with for limit the nozzle connection ring end circular hole inner circle the
Two flanges 52.
Further, the bulging block 5 is provided with for forming the cone tank half close to the side of the central shaft 1
Inclined hole 53, the upside of the inclined hole 53 is provided with the straight hole 54 for being oriented to for the compression bar 6.
Finally it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than the present invention is protected
The limitation of scope is protected, although being explained with reference to preferred embodiment to the present invention, those of ordinary skill in the art should
Work as understanding, can be to technical scheme technical scheme is modified or replaced equivalently, without departing from the reality of technical solution of the present invention
Matter and scope.
Claims (7)
1. airplane turbine spiral case nozzle connection ring welding fixture, it is characterised in that：Including the bottom for contradicting outlet nozzle end face
Seat (2), central shaft (1) is vertically arranged with the middle part of the base (2), is socketed with outside the central shaft (1) for limiting outlet
The guide post (3) of nozzle inner circle, support plate (4), support plate (4) upside are provided with nozzle connection ring expansion tube, the nozzle
Connection ring expansion tube includes two semi-circular bulging blocks (5) being separated from each other, and the nozzle connection ring expansion tube is socketed on described
Central shaft (1) outside, is provided with cone tank, is set above the nozzle connection ring expansion tube in the middle part of the nozzle connection ring expansion tube
It is useful for described two bulging blocks (5) being socketed on the central shaft (1) to the separated compression bar in both sides (6), the compression bar (6)
Outside, the upper end of the compression bar (6) is provided with clamp nut (7), and the clamp nut (7) is threadedly coupled with the central shaft (1).
2. airplane turbine spiral case nozzle connection ring welding fixture according to claim 1, it is characterised in that：The guide post
(3) outside diameter is equal with the internal diameter of the outlet nozzle.
3. airplane turbine spiral case nozzle connection ring welding fixture according to claim 1, it is characterised in that：The bulging block
(5) bottom is provided with the first flange (51) for stretching into the annular groove in the middle part of nozzle connection ring.
4. airplane turbine spiral case nozzle connection ring welding fixture according to claim 3, it is characterised in that：Described first is convex
The thickness of edge (51) is less than the width of the annular groove.
5. airplane turbine spiral case nozzle connection ring welding fixture according to claim 3, it is characterised in that：The compression bar
(6) when coming downwards to extreme lower position, (5) first flange (51) of bulging block contradicts the bottom of the annular groove.
6. airplane turbine spiral case nozzle connection ring welding fixture according to claim 3, it is characterised in that：The bulging block
(5) top is provided with the second flange (52) for limiting the nozzle connection ring end circular hole inner circle.
7. airplane turbine spiral case nozzle connection ring welding fixture according to claim 3, it is characterised in that：The bulging block
(5) side of the close central shaft (1) is provided with the inclined hole (53) for forming the cone tank half, the inclined hole (53)
Upside is provided with the straight hole (54) for being oriented to for the compression bar (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510296593.5A CN106271298B (en) | 2015-06-03 | 2015-06-03 | Airplane turbine spiral case nozzle connection ring welding fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510296593.5A CN106271298B (en) | 2015-06-03 | 2015-06-03 | Airplane turbine spiral case nozzle connection ring welding fixture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106271298A CN106271298A (en) | 2017-01-04 |
| CN106271298B true CN106271298B (en) | 2018-04-17 |
Family
ID=57655423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510296593.5A Expired - Fee Related CN106271298B (en) | 2015-06-03 | 2015-06-03 | Airplane turbine spiral case nozzle connection ring welding fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106271298B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108145337A (en) * | 2017-12-30 | 2018-06-12 | 珠海市业成轨道交通设备科技有限公司 | A kind of connection ring of high speed motor car oil-pressure damper and the welding point of pedestal |
| CN111473967B (en) * | 2020-05-12 | 2022-03-25 | 中国航发湖南动力机械研究所 | Centering structure and turbine test device with same |
| CN111604813A (en) * | 2020-06-28 | 2020-09-01 | 长春理工大学 | Composite nozzle abrasive flow polishing clamp |
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| FR2931715A1 (en) * | 2008-05-30 | 2009-12-04 | Snecma | Integral welding transfer method for compressor of turbomachine in aeronautical field, involves individually fabricating fixed blades by laser fusion, and assembling loops and blades for forming synchronizing ring sector of turbomachine |
| CN202507016U (en) * | 2012-03-16 | 2012-10-31 | 贵州红湖发动机零部件有限公司 | Expanding and welding device for annular weld joints of sheet metal parts in automatic welding process |
| CN203779021U (en) * | 2014-02-19 | 2014-08-20 | 襄阳三鹏航空科技有限公司 | Auxiliary device for welding aircraft turbocharger |
| CN104368837A (en) * | 2014-11-19 | 2015-02-25 | 常州市常欧金属制品有限公司 | Expansion fixture device |
| CN104736292A (en) * | 2012-09-07 | 2015-06-24 | 诺沃皮尼奥内有限公司 | Method for repairing a turbomachine component |
| CN204686338U (en) * | 2015-06-03 | 2015-10-07 | 襄阳三鹏航空科技有限公司 | Airplane turbine spiral case nozzle connecting ring weld jig |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009052885A1 (en) * | 2007-10-24 | 2009-04-30 | Borgwarner Inc. | Method for connecting a turbine wheel and a shaft of an exhaust-gas turbocharger by means of a capacitor discharge welding process |
| US8784065B2 (en) * | 2011-05-24 | 2014-07-22 | Caterpillar Inc. | Friction welding of titanium aluminide turbine to titanium alloy shaft |
-
2015
- 2015-06-03 CN CN201510296593.5A patent/CN106271298B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2931715A1 (en) * | 2008-05-30 | 2009-12-04 | Snecma | Integral welding transfer method for compressor of turbomachine in aeronautical field, involves individually fabricating fixed blades by laser fusion, and assembling loops and blades for forming synchronizing ring sector of turbomachine |
| CN202507016U (en) * | 2012-03-16 | 2012-10-31 | 贵州红湖发动机零部件有限公司 | Expanding and welding device for annular weld joints of sheet metal parts in automatic welding process |
| CN104736292A (en) * | 2012-09-07 | 2015-06-24 | 诺沃皮尼奥内有限公司 | Method for repairing a turbomachine component |
| CN203779021U (en) * | 2014-02-19 | 2014-08-20 | 襄阳三鹏航空科技有限公司 | Auxiliary device for welding aircraft turbocharger |
| CN104368837A (en) * | 2014-11-19 | 2015-02-25 | 常州市常欧金属制品有限公司 | Expansion fixture device |
| CN204686338U (en) * | 2015-06-03 | 2015-10-07 | 襄阳三鹏航空科技有限公司 | Airplane turbine spiral case nozzle connecting ring weld jig |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106271298A (en) | 2017-01-04 |
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Granted publication date: 20180417 Termination date: 20210603 |
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