CN106041237A - Positioning method for honeycomb type tight seal pieces of aircraft engine - Google Patents
Positioning method for honeycomb type tight seal pieces of aircraft engine Download PDFInfo
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- CN106041237A CN106041237A CN201610394948.9A CN201610394948A CN106041237A CN 106041237 A CN106041237 A CN 106041237A CN 201610394948 A CN201610394948 A CN 201610394948A CN 106041237 A CN106041237 A CN 106041237A
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- Prior art keywords
- honeycomb
- clamping plate
- copper strips
- welding
- metal outer
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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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
-
- 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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
-
- 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
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
The invention discloses a positioning method for honeycomb type tight seal pieces of an aircraft engine. The method is used for enabling the tight seal pieces and a metal outer ring to be subject to energy storage point welding connection before vacuum brazing, and therefore the tight seal pieces are positioned; and the positioning method comprises the following steps: the metal outer ring is provided, and the tight seal pieces are annularly arranged on the inner side of the metal outer ring; and an electrode is provided, and the tight seal pieces and the metal outer ring are welded together from the annular inner sides of the tight seal pieces. According to the positioning method, before vacuum brazing, a honeycomb and the metal outer ring are subject to energy storage point welding connection, and accordingly, the phenomenon that in the brazing process, the honeycomb and the metal ring are separated, and consequently the low welding yield is caused is avoided; and in addition, the invention further provides the new energy storage point welding electrode for the honeycomb tight seal pieces of the aircraft engine. According to the electrode, through the specific structural design, the burning phenomenon of the honeycomb tight seal pieces in the energy storage point welding process can be effectively avoided, and the machining efficiency is improved.
Description
Technical field
The present invention relates to aero-engine honeycomb class obturage the orientation problem before part vacuum brazing, especially a kind of utilize storage
Spot welding aero-engine honeycomb class can be obturaged the method that part positions.
Background technology
Aero-engine honeycomb class part of obturaging is mode of obturaging more conventional in current aero-engine, the most widely should
In various types, and stepping up along with engine performance, the requirement to operating temperature is more and more higher, so that honeybee
The range of application of nest is more and more wider.And the connection of honeycomb and matrix substantially solves by vacuum brazing.Therefore, how by honeycomb
Effectively position the primary technical problem being to solve honeycomb soldering.At present, honeycomb substrate material cores lattice typically have a size of
0.8mm or 1.6mm, thickness only 0.05mm.For ease of with the coordinating of matrix, honeycomb supply of material state is generally annealed state.So, when
During assembly soldering, position according to fixture, then honeycomb will experience in clamping process and once deform, the most also than
More serious, enter back into vacuum drying oven when carrying out soldering, in soldering temperature-rise period and reach brazing temperature whole during, assembly
Matrix material and brazing jig are intended to be deformed, and ultimately result in fixture and weaken the effect of contraction of honeycomb or lost efficacy, thus produce
Raw brazing defect.
Chinese patent application 201210190174.X discloses part injury when one prevents tack-weld honeycomb texture
Devices and methods therefor, the prior art carries out tack welding to honeycomb texture by the way of spot welding, when avoiding soldering with this
Defect.Meanwhile, during for avoiding spot welding, honeycomb texture is impaired, and the honeycomb structure assembly being spot welded is positioned over absolutely by the prior art
On edge bracket so that it is work surface contacts with insulator support, thus avoid on work surface because spot welding causes damage.But this is existing
The problem that technology can not be reduced or avoided between electrode and honeycomb the honeycomb scorch caused owing to discharge capacity is excessive.
Summary of the invention
The technical problem to be solved in the present invention is to make owing to discharge capacity is excessive to be reduced or avoided between electrode and honeycomb
The problem of honeycomb scorch become, the invention provides a kind of aero-engine honeycomb class and obturages the localization method of part, be used for
Before vacuum brazing, described part of obturaging is positioned；Avoid honeycomb in brazing process to separate with becket simultaneously, cause seam
Rate is low and the phenomenon of honeycomb burn.
For solving above-mentioned technical problem, the present invention proposes a kind of aero-engine honeycomb class and obturages the localization method of part,
Described method is for before vacuum brazing, and part of aero-engine honeycomb class being obturaged carries out percussion spot welding with metal outer shroud and is connected,
With this, described part of obturaging is positioned；Avoid honeycomb in brazing process to separate with becket simultaneously, cause welded rate low and
The phenomenon of honeycomb burn.Described localization method comprises the steps: to provide a metal outer shroud, by described aero-engine honeycomb
Class part of obturaging is arranged in the inner side of described metal outer shroud ringwise；Thering is provided an electrode, described electrode includes interconnective behaviour
Making bar and welding bars, described welding bars connects a welding body, the annular of part of obturaging from described aero-engine honeycomb class
Described welding body is resisted against the inner side of described metal outer shroud and is welded to together by inner side.
Preferably, the cuboid that described welding body is substantially flat, it has the upper end being connected with described welding bars
The lower surface relative with described upper surface, face, left surface, right flank and front side between described upper surface and lower surface
Face and trailing flank；Described upper surface is respectively provided with a left side step and a right side with the junction of described left surface and right flank
Side stage rank；At described left side step and right side stepped locations, shape is respectively arranged with left side clamping plate and a right side accordingly
Clamping plate；One copper strips sheet is arranged on described lower surface, and on the left of it, free end and right side free end are respectively along described left surface
It is folded upward at extending into spill with right flank, and is clamped between described left side clamping plate and described left surface and described right side folder
Between plate and described right flank.
Preferably, between described copper strips sheet and described welding body, it is clamped with a rubber sheet gasket, for will be being welded this
Body from described aero-engine honeycomb class obturage the annular inboard of part be resisted against the inner side of described metal outer shroud when, carry
Reduce instantaneous pressure in pinpoint welding procedure for cushion effect, and make copper strips sheet become along the obturage surface of part of aero-engine honeycomb class
Shape, increases the contact area between copper strips sheet and weldment, reduces the burn of honeycomb, improve working (machining) efficiency.
Preferably, described left side clamping plate and right side clamping plate are bolted to described welding by left side bolt and right side respectively
On body.
Preferably, described left side clamping plate are the inverted l-shaped structure that structure is identical with right side clamping plate, described left side bolt and described
Right side bolt is perpendicular to the side of described left side clamping plate and the right side clamping plate described copper strips sheet of clamping and arranges.
Preferably, described left surface and right flank be respectively arranged with match with described left side bolt and right side bolt
Screwed hole, the left side free end of described copper strips sheet and right side free end are not higher than the minimum point of described screwed hole and arrange.
Preferably, described copper strips sheet is the most essentially identical with the length of described rubber sheet gasket.
Preferably, described copper strips sheet and described rubber sheet gasket have identical width.
Preferably, the thickness of the described welding body that the width of described copper strips sheet is not more than between described leading flank and trailing flank
Degree.
Preferably, the voltage range of spot welding is generally: 120V～240V.
The localization method of the present invention, before vacuum brazing, is connected by honeycomb is carried out percussion spot welding with metal outer shroud, with
This is avoided honeycomb in brazing process to separate with becket, causes the phenomenon that welded rate is low.It addition, the localization method of the present invention also carries
Obturaging part percussion spot welding electrode for a kind of new aero-engine honeycomb class, described electrode can by the design of specific structure
Obturage the burn phenomenon during part percussion spot welding effectively reducing honeycomb class, improve working (machining) efficiency.Further, provided by the present invention
Electrode structure by arranging easily deformable copper strips sheet on the work surface of welding body, assist the rubber with elastically deformable
Pad, in pinpoint welding procedure, copper strips sheet contacts with honeycomb surface, and thin copper strips sheet contacts with honeycomb face and can drop with deformation buffer
Low-pressure, the addition of rubber sheet gasket can reduce instantaneous pressure during spot welding further, simultaneously because rubber is yielding with copper strips,
Just increase the contact area of electrode and part during lower pressure, reduce due to big the caused honeycomb burn of discharge capacity, improve
Working (machining) efficiency.
Accompanying drawing explanation
The following drawings is only intended to, in schematically illustrating the present invention and explaining, not delimit the scope of the invention.Wherein,
Fig. 1 is shown that a kind of aero-engine honeycomb class of a specific embodiment according to the present invention and obturages the determining of part
The operation chart of method for position；
Fig. 2 is shown that in operation chart shown in Fig. 1 a kind of aero-engine honeycomb class used and obturages part energy storage point
The structural representation of weldering electrode；
Fig. 3 is shown that the decomposition diagram of electrode shown in Fig. 2.
Detailed description of the invention
In order to be more clearly understood from the technical characteristic of the present invention, purpose and effect, now comparison accompanying drawing illustrates this
Bright detailed description of the invention.Wherein, identical parts use identical label.
The most as described in the background section, aero-engine honeycomb class part of obturaging, before vacuum brazing, can use spot welding
Honeycomb is carried out tack welding, but the problem that there is the honeycomb scorch caused owing to discharge capacity is excessive.Therefore, the present invention carries
A kind of new aero-engine honeycomb class has been supplied to obturage the localization method of part, to avoid drawbacks described above.
Specifically, the aero-engine honeycomb class of the present invention obturage part need before vacuum brazing by sticky brazing filler material be pressed into
Honeycomb core lattice, for avoiding honeycomb problem on deformation in operation, the localization method of the present invention, before vacuum brazing, first will
Honeycomb carries out percussion spot welding with metal outer shroud and is connected, and avoids honeycomb in brazing process to separate with becket with this, causes welded rate
Low phenomenon.If part uses common copper electrode during carrying out percussion spot welding it addition, aero-engine honeycomb class is obturaged
Carry out honeycomb spot welding location, owing to percussion spot welding discharge capacity is excessive, often cause the burn on honeycomb surface and outer shaped part
Burn, and the reasonability of electrode design also can largely affect the point quality of honeycomb and outer shroud, and then affect follow-up weldering
Conjunction situation, seriously will cause part repeat repair welding or scrap, increase production cost.
Therefore, based on above-mentioned technical problem, the localization method of the present invention additionally provides a kind of new aero-engine honeycomb
Class is obturaged part percussion spot welding electrode, and described electrode can effectively reduce honeycomb class by the design of specific structure and obturage part energy storage
Burn phenomenon in pinpoint welding procedure, improves working (machining) efficiency.
That is, as it is shown in figure 1, it is shown that a kind of aero-engine honeycomb of a specific embodiment according to the present invention
Class is obturaged the operation chart of localization method of part, and aero-engine honeycomb class, for before vacuum brazing, is sealed by described method
Tight part 200 carries out percussion spot welding with metal outer shroud 300 and is connected, and positions described part 200 of obturaging with this；Avoid soldering simultaneously
During honeycomb separate with becket, cause welded rate low and honeycomb burn phenomenon.
Described localization method comprises the steps: first to provide a metal outer shroud 300, and the material of metal outer shroud 300 should
This preferable metal or alloy of selection electric conductivity is general conventional for chromium-zirconium-copper or chromium tungsten copper.Then by described aero-engine
Honeycomb class part 200 of obturaging is arranged in the inner side of metal outer shroud 300 ringwise.The aero-engine of one particular design is provided afterwards
Honeycomb class is obturaged part percussion spot welding electrode 100, is welded on metal outer shroud 300 in order to part 200 of obturaging and positions.That is,
Unlike the prior art, the localization method of the present invention is cellular localization to be welded on metal outer shroud, avoids honeycomb with this
The problem on deformation in operating process behind, meanwhile, the electrode 100 of particular design can avoid honeycomb class to obturage part energy storage point
Burn phenomenon during weldering.In pinpoint welding procedure, according to the structure of metal outer shroud and the difference of size and the difference of honeycomb thickness
Different, spot welding voltage range is generally: 120V～240V.
The structure of electrode 100 shows in figs 2 and 3, and wherein, Fig. 2 is shown that in operation chart shown in Fig. 1 used
A kind of aero-engine honeycomb class is obturaged the structural representation of part percussion spot welding electrode；Fig. 3 is shown that electrode shown in Fig. 2
Decomposition diagram.As Figure 2-3, electrode 100 includes interconnective action bars 3 and welding bars 1, and welding bars 1 connects one
Individual welding body 2, during operation, is resisted against welding body 2 from the obturage annular inboard of part 200 of described aero-engine honeycomb class
Part 200 also will be obturaged and metal outer shroud 300 welds together in the inner side of metal outer shroud 300.
Particularly, it is illustrated that the aero-engine honeycomb class of particular design obturage part percussion spot welding electrode 100 can be used for by
Aero-engine honeycomb class part 200 of obturaging carries out percussion spot welding with metal outer shroud 300 and is connected；Honeycomb in brazing process is avoided with this
Separate with becket, cause welded rate low and the phenomenon of honeycomb burn.
As Figure 2-3, the welding substantially flat cuboid of body 2 of described electrode 100, it has and welding bars
The lower surface 12 relative with upper surface 11, upper surface 11 that 1 connects, the left surface between upper surface 11 and lower surface 12
13, right flank 14 and leading flank 15 and trailing flank 16.Upper surface 11 has respectively with the junction of left surface 13 and right flank 14
There are a left side step 131 and a right side step 141；Left side step 131 and right side step 141 position shape are divided accordingly
It is not provided with left side clamping plate 132 and right side clamping plate 142；One copper strips sheet 17 is arranged on lower surface 12, on the left of it
Free end 171 and right side free end 172 are folded upward at extending into spill respectively along left surface 13 and right flank 14, and left side is freely
End 171 and right side free end 172 are clamped between left side clamping plate 132 and left surface 13 and right side clamping plate 142 and right side respectively
Between face 14.
Further, it is clamped with a rubber sheet gasket 18 between copper strips sheet 17 and welding body 2, for body will be being welded
2 from described aero-engine honeycomb class obturage the annular inboard of part be resisted against the inner side of described metal outer shroud when, carry
Reduce instantaneous pressure in pinpoint welding procedure for cushion effect, and make copper strips sheet 17 become along the obturage surface of part of aero-engine honeycomb class
Shape, increases the contact area between copper strips sheet 17 and weldment, reduces the burn of honeycomb, improve working (machining) efficiency.
The above-mentioned electrode structure of the present invention, easily deformable by arranging on the work surface (lower surface 12) of welding body 2
Copper strips sheet 17, assist with the rubber sheet gasket 18 of elastically deformable, in pinpoint welding procedure, copper strips sheet 17 contacts with honeycomb surface,
Thin copper strips sheet 17 contacts with honeycomb face and can reduce pressure with deformation buffer, and the addition of rubber sheet gasket 18 can reduce a little further
Instantaneous pressure during weldering, simultaneously because rubber is yielding with copper strips, just increases electrode 100 and honeycomb 200 during lower pressure
Contact area, reduces due to big the caused honeycomb burn of discharge capacity, improves working (machining) efficiency.
In a preferred embodiment, described left side clamping plate 132 and right side clamping plate 142 are made up of the metal of well conducting,
It is preferably metallic copper.Its effect is that the left side clamping plate 132 by well conducting and right side clamping plate 142 will welding body 2 and copper strips
Sheet 17 connects into loop so that copper strips sheet 17 can realize the function of percussion spot welding.Certainly, same, described welding bars 1 and weldering
Connect body 2 to be made up of the metal of well conducting, preferably metallic copper.
In a further advantageous embodiment, left side clamping plate 132 and right side clamping plate 142 are respectively by left side bolt 133 and the right side
Side bolt 143 is connected to weld on body 2.
Further, in another preferred embodiment, left side clamping plate 132 are the inverted L that structure is identical with right side clamping plate 142
Shape structure, it is simple to structure is exchanged and reduced number of parts.Left side bolt 133 and right side bolt 143 are perpendicular to left side clamping plate 132 and the right side
Side clamping plate 142 clamp the side of copper strips sheet 17 and arrange, i.e. left side bolt 133 and right side bolt 143 are perpendicular to left surface 13 and the right side
Side 14 is arranged.Wherein, left surface 13 and right flank 14 are respectively arranged with match with left side bolt 133 and right side bolt 143
The screwed hole 20 closed.In the above-described embodiments, left side clamping plate 132 and the right side clamping plate 142 of inverted l-shaped structure can utilize its upper end
Match with left side step 131 and a right side step 141, play the effect of location, it is to avoid left side clamping plate 132 in installation process
Rotate around left side bolt 133 and right side bolt 143 with right side clamping plate 142.
The when of dismounting copper strips sheet 17 and rubber sheet gasket 18, can only left side bolt 133 and right side bolt 143 be unscrewed
(being not required to from the screwed hole 20 of welding body 2, left side bolt 133 and right side bolt 143 are pulled down taking-up completely completely),
Make the gap between left side clamping plate 132 and right side clamping plate 142 and left surface 13 and right flank 14 more than copper strips sheet 17 and rubber
The thickness that pad 18 stacks up, thus above-mentioned inverted l-shaped structure and step design can save disassembly and assembly time, simultaneously can
To avoid frequently dismounting part loss (copper strips sheet 17 is easy to ablation to be damaged, and needs frequently to change).
It addition, use the left side clamping plate 132 of inverted l-shaped structure and the conductive structure of right side clamping plate 142, can improve clamping plate with
The contact area of copper strips sheet 17, on the one hand can reduce contact resistance, it is to avoid ablation, and the biggest holding area improves
The clamping dynamics at the two ends of copper strips sheet 17, it is to avoid the two ends of copper strips sheet 17 are torn in operation.If copper strips sheet 17
Two ends directly be screwed onto welding body 2 on, then the screwed hole position at copper strips sheet can form the region of strength reduction, when frequently
During pressing spot welding, the screwed hole position of copper strips sheet is easy to tear breakage.And the clamp region of present invention employing is permissible
Overcoming the problem that the tear of copper strips sheet end is damaged completely, the clamping plate of inverted l-shaped structure may also operate as coordinating with step being prone to simultaneously
The effect of location, the 3rd effect is can to dismantle clamping plate just can complete the replacing of copper strips sheet.That is, what the present invention provided falls
The clamping plate of L-shaped structure have three kinds of different functions and effect concurrently, are non-obvious for a person skilled in the art.
For avoiding structure to disturb, preferably left side free end 171 and the right side free end 172 of copper strips sheet 17 is not higher than screwed hole
The minimum point of 20 is arranged.Being similar to, preferably copper strips sheet 17 is the most essentially identical with the length of rubber sheet gasket 18, thus
Copper strips sheet 17 can be served as a contrast and end also minimum without departing from screwed hole 20 of rubber sheet gasket 18 by rubber sheet gasket 18 completely
Point, it is to avoid enter screwed hole 20 with interference bolt.
Further, preferably copper strips sheet 17 and rubber sheet gasket 18 have identical width.Further, the width of preferred copper strips sheet 17
Degree is not more than the thickness of the described welding body 2 between leading flank 15 and trailing flank 16.Its advantage be the edge of copper strips sheet 17 not
Can expose outside from leading flank 15 and trailing flank 16, it is to avoid the edge bending deformation of copper strips sheet 17.The more preferably width of copper strips sheet 17
Degree is equal to the thickness of welding body 2, it is simple to ensure the when of installation that the edge of copper strips sheet 17 is neat with leading flank 15 and trailing flank 16
Flat, it is easy to location, save the operating time, improve work efficiency.
Before the present invention is not carried out, use soldering that honeycomb is positioned, a soldering qualification rate about 40% of cellular component,
Annual fixture consumes about 300,000 yuan.After using percussion spot welding location, soldering qualification rate brings up to more than 80%, year equipment make
Expense only about 20,000 yuan.Series spot welding positions, it is ensured that honeycomb is adjacent to outer shroud, and honeycomb depth of burn is less than 0.5mm, outward
Ring is less than 0.2mm.
Although it will be appreciated by those skilled in the art that the present invention is to be described according to the mode of multiple embodiments, but
It is that the most each embodiment only comprises an independent technical scheme.For the sake of in description, so narration is only used to understand,
Description should be understood by those skilled in the art as an entirety, and by technical scheme involved in each embodiment
Regard as and can understand protection scope of the present invention in the way of being mutually combined into different embodiment.
The foregoing is only the schematic detailed description of the invention of the present invention, be not limited to the scope of the present invention.Any
Those skilled in the art, the equivalent variations made, revises and combines on the premise of without departing from the design of the present invention and principle,
The scope of protection of the invention all should be belonged to.
Claims (10)
1. aero-engine honeycomb class is obturaged a localization method for part, and aviation, for before vacuum brazing, is sent out by described method
Motivation honeycomb class part (200) of obturaging carries out percussion spot welding with metal outer shroud (300) and is connected, and enters described part of obturaging (200) with this
Row location；Avoid honeycomb in brazing process to separate with becket simultaneously, cause welded rate low and the phenomenon of honeycomb burn.It is special
Levying and be, described localization method comprises the steps: to provide a metal outer shroud (300), by described aero-engine honeycomb class
Part (200) of obturaging is arranged in the inner side of described metal outer shroud (300) ringwise；One electrode (100), described electrode are provided
(100) including interconnective action bars (3) and welding bars (1), described welding bars (1) connects welding body (2), from
Described welding body (2) is resisted against described metal outer shroud by the obturage annular inboard of part (200) of described aero-engine honeycomb class
(300) inner side is also welded to together.
2. the method for claim 1, it is characterised in that the cuboid that described welding body (2) is substantially flat, its
Have the lower surface (12) relative with the upper surface (11) that described welding bars (1) connects and described upper surface (11), be positioned at described
Left surface (13), right flank (14) and leading flank (15) between upper surface (11) and lower surface (12) and trailing flank (16)；
The junction of described upper surface (11) and described left surface (13) and right flank (14) be respectively provided with one on the left of step (131) and
One right side step (141)；Described left side step (131) and right side step (141) position shape are respectively arranged with accordingly
One left side clamping plate (132) and right side clamping plate (142)；One copper strips sheet (17) is arranged on described lower surface (12), its
Left side free end (171) and right side free end (172) are folded upward at prolonging respectively along described left surface (13) and right flank (14)
Be stretched into spill, and be clamped between described left side clamping plate (132) and described left surface (13) and described right side clamping plate (142) and
Between described right flank (14).
3. method as claimed in claim 2, it is characterised in that press from both sides between described copper strips sheet (17) and described welding body (2)
Hold a rubber sheet gasket (18), in the annular at part of welding body (2) being obturaged from described aero-engine honeycomb class
The when that side being resisted against the inner side of described metal outer shroud, it is provided that cushion effect reduces instantaneous pressure in pinpoint welding procedure, and makes copper
Strap (17) is obturaged along aero-engine honeycomb class the areal deformation of part, increases the contact surface between copper strips sheet (17) and weldment
Long-pending, reduce the burn of honeycomb, improve working (machining) efficiency.
4. the method as described in claim 2 and 3, it is characterised in that described left side clamping plate (132) and right side clamping plate (142) point
Tong Guo left side bolt (133) and right side bolt (143) not be connected on described welding body (2).
5. method as claimed in claim 3, it is characterised in that described left side clamping plate (132) and right side clamping plate (142) are structure
Identical inverted l-shaped structure, described left side bolt (133) and described right side bolt (143) be perpendicular to described left side clamping plate (132) and
Right side clamping plate (142) clamps the side of described copper strips sheet (17) and arranges.
6. method as claimed in claim 4, it is characterised in that be respectively arranged with on described left surface (13) and right flank (14)
The screwed hole (20) matched with described left side bolt (133) and right side bolt (143), the left side of described copper strips sheet (17) is freely
End (171) and right side free end (172) are not higher than the minimum point of described screwed hole (20) and arrange.
7. method as claimed in claim 5, it is characterised in that described copper strips sheet (17) and the length of described rubber sheet gasket (18)
The most essentially identical.
8. method as claimed in claim 6, it is characterised in that described copper strips sheet (17) has phase with described rubber sheet gasket (18)
Same width.
9. method as claimed in claim 7, it is characterised in that the width of described copper strips sheet (17) is not more than described leading flank
(15) thickness of the described welding body (2) and between trailing flank (16).
10. the method as described in claim 1-8, it is characterised in that the voltage range of spot welding is generally: 120V～240V.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610394948.9A CN106041237A (en) | 2016-06-06 | 2016-06-06 | Positioning method for honeycomb type tight seal pieces of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610394948.9A CN106041237A (en) | 2016-06-06 | 2016-06-06 | Positioning method for honeycomb type tight seal pieces of aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN106041237A true CN106041237A (en) | 2016-10-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610394948.9A Pending CN106041237A (en) | 2016-06-06 | 2016-06-06 | Positioning method for honeycomb type tight seal pieces of aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115815725A (en) * | 2023-02-20 | 2023-03-21 | 成都大金航太科技股份有限公司 | Brazing positioning protection device and brazing method for honeycomb parts |
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| CN202591825U (en) * | 2012-06-18 | 2012-12-12 | 北京飞机维修工程有限公司 | Spot-welding electrode for honeycomb exchange component |
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| CN201752815U (en) * | 2010-08-20 | 2011-03-02 | 西安航空动力股份有限公司 | Soft electrode for welding honeycomb annular component |
| CN201799774U (en) * | 2010-09-21 | 2011-04-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Silicone rubber padding electrode device for projection welding and positioning honey comb structure |
| CN201799773U (en) * | 2010-09-21 | 2011-04-20 | 沈阳黎明航空发动机(集团)有限责任公司 | Copper liner mesh type electrode device for projection welding positioning honeycomb cellular structure |
| CN202591825U (en) * | 2012-06-18 | 2012-12-12 | 北京飞机维修工程有限公司 | Spot-welding electrode for honeycomb exchange component |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115815725A (en) * | 2023-02-20 | 2023-03-21 | 成都大金航太科技股份有限公司 | Brazing positioning protection device and brazing method for honeycomb parts |
| CN115815725B (en) * | 2023-02-20 | 2023-05-12 | 成都大金航太科技股份有限公司 | Honeycomb part brazing positioning protection device and brazing method |
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Application publication date: 20161026 |