CN110449824A - Diesel engine cylinder holes convex shoulder restorative procedure - Google Patents
Diesel engine cylinder holes convex shoulder restorative procedure Download PDFInfo
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- CN110449824A CN110449824A CN201910789167.3A CN201910789167A CN110449824A CN 110449824 A CN110449824 A CN 110449824A CN 201910789167 A CN201910789167 A CN 201910789167A CN 110449824 A CN110449824 A CN 110449824A
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- cylinder holes
- convex shoulder
- fuselage
- grinding
- fuselage cylinder
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The present invention discloses a kind of diesel engine cylinder holes convex shoulder restorative procedure, comprising the following steps: A, polishes the corrosion location of fuselage cylinder holes convex shoulder, removes the part of corrosion, exposes metal true qualities；B, surface dye penetrant inspection is carried out to fuselage cylinder holes convex shoulder, checks for crackle；C, datum plane when reconditioning fuselage cylinder holes convex shoulder is determined；D, using cold welding machine and wlding, on fuselage cylinder holes convex shoulder corrosion location and defect carry out repair welding；E, installation grinding bracket and grinding tool carry out grinding to fuselage cylinder holes convex shoulder.Use diesel engine cylinder holes convex shoulder restorative procedure of the invention, fuselage cylinder holes convex shoulder position can effectively be repaired, voltage endurance capability is strong, it is not easy fragmentation, reach cylinder sleeve and installs and uses requirement, the service life of fuselage cylinder holes is greatly prolonged, the present invention had not only solved cast iron Welding Problems, but also completed the mach problem in heavy parts scene.
Description
Technical field
The present invention relates to diesel engines to repair field, in particular to a kind of diesel engine cylinder holes convex shoulder restorative procedure.
Background technique
As shown in Figure 1, the casting fuselage 3 of diesel engine, is inside provided with fuselage cylinder holes 4, the top of cylinder holes is provided with a cylinder
Hole convex shoulder position 2, cylinder sleeve 1 is packed into fuselage cylinder holes 4, and is limited by cylinder holes convex shoulder position 2, has a water in fuselage cylinder holes upper end
Mounting plane 5 is covered, water jacket 6 is fixedly connected by water jacket mounting plane 5 with fuselage.
After using the regular period, the cylinder holes convex shoulder position 2 contacted with cylinder sleeve 1 can be lost by scale, and corrosion occurs very much
Pit, meeting leak when situation is slight, pollutes lubricating oil, lubricating oil is caused to fail；It will cause water of the cylinder sleeve 1 in fuselage when situation is serious
Pingdu run-off the straight, to cause great engine-damaged accident.It therefore is very necessary and important to the maintenance of fuselage cylinder holes.
Diesel engine material is cast iron, while being huge body structure again, since cast iron weldability is poor, metal fusion welding
Heat is big in the process, is easy to produce thermal stress, to cause base material crackle.So using common cast iron back-welding method and work
There is very big operation difficulty in skill, scene is difficult condition needed for having operation, and (such as fuselage heats, and heat preservation is eliminated stress, prevented
Crackle etc.).
In actually maintenance, most common method is owner at present: using industrial sticker (iron-based or copper-based gluey material
Material, is commonly called as iron cement) corrosion location is filled up, after the dry hardening of sticker, scraping equating is whole, reaches predetermined size
Afterwards, it then installs and uses.The shortcomings that this method is: cast iron intensity requirement is not achieved in the mechanical performance of material after sticker hardening,
Common gray iron (HT100) compression strength σ a=500MPa, tensile strength sigma b=100MPa, bending strength σ w=260MPa, hardness
HB=143-229；And best sticker material, compression strength σ a=99.7MPa, shearing strength σ c=38MPa, hardness HS=
90, it is roughly equal to HB=668.The more visible sticker material compression strength of the two is far below gray iron (5 times), and hardness is higher than gray iron
(about 3 times), this results in sticker material when by pressure, not withstand pressure, easy to break.Diesel engine cylinder holes plane is being started
It when machine works, to bear cylinder bolt pretightning force (45-90MPa), the impact force (12.5- of fuel combustion explosion in the cylinder
14MPa) and thermal stress and vibration etc., it is impregnated in the cooling water circulated and impact along with having in fuselage, sticker material
Material ruptures soon, and washes away failure by water.Therefore fuselage cylinder holes etching problem can not be really solved using sticker, it can only
It is a kind of interim remedial measure.
Summary of the invention
In view of the above-mentioned problems, providing a kind of diesel engine cylinder it is an object of the invention to solve the deficiencies in the prior art
Hole convex shoulder restorative procedure.
To achieve the goals above, technical scheme is as follows:
The present invention provides a kind of diesel engine cylinder holes convex shoulder restorative procedure, which comprises the following steps:
A, it polishes the corrosion location of fuselage cylinder holes convex shoulder, removes the part of corrosion, expose metal true qualities；
B, surface dye penetrant inspection is carried out to fuselage cylinder holes convex shoulder, checks for crackle；Such as there is crackle, polishes
It eliminates；
C, determine that datum plane when reconditioning fuselage cylinder holes convex shoulder, the datum plane are vertical with fuselage cylinder holes inner wall；It presses
According to design requirement, the vertical range L of the datum plane Yu fuselage cylinder holes convex shoulder upper surface is determined, need after needing soldering with determination
The height of repairing；
D, using cold welding machine and wlding, on fuselage cylinder holes convex shoulder corrosion location and defect carry out repair welding；
E, installation grinding bracket and grinding tool, and after adjusting centrad and the depth of parallelism, fuselage cylinder holes convex shoulder is ground
Cut processing, be ground to it is corresponding with datum plane until, reconditioning complete.
In a preferred embodiment of the invention, in stepb, first fuselage cylinder holes shoulder surface is cleaned up, and makes machine
Body cylinder holes shoulder surface keeps drying, bleeding agent is then carried out even application to fuselage cylinder holes shoulder surface, spraying finishes it
Afterwards, it waits 5-15 minutes to be infiltrated, is cleaned up the bleeding agent for being sprayed on fuselage cylinder holes shoulder surface using cleaning agent, so that fuselage
The cleaning of cylinder holes shoulder surface, is finally dried with clean calico, imaging agent is sufficiently shaken up, and is kept to fuselage cylinder holes shoulder surface
Distance 150mm-300mm even application observes fuselage cylinder holes shoulder surface, until the size of mark trace does not change；It must
Multiple dye penetrant inspection can be carried out when wanting.
In a preferred embodiment of the invention, it in step C, on the water jacket mounting plane of fuselage cylinder holes upper end, looks at three
Measurement point X, Y, Z, it is desirable that fuselage cylinder holes convex shoulder position corresponding to measurement point is not corrosion default, complete plane；This
Plane where three measurement points, datum plane when as reconditioning plane；According to design requirement, determine the measurement point with it is right
The vertical range at the fuselage cylinder holes convex shoulder position answered, with determining eligible for repair height after needing soldering.
In a preferred embodiment of the invention, in step C, a standard ring is installed additional in fuselage cylinder holes upper end, by the standard
The datum plane when upper surface of ring is as reconditioning finds the position of not corrosion default on fuselage cylinder holes convex shoulder, according to setting
Meter requires, and determines the vertical range at the position Yu the datum plane, with determining eligible for repair height after needing soldering.
In a preferred embodiment of the invention, in step E, the grinding bracket is mounted in fuselage cylinder holes, including upper branch
Frame and lower bracket, the upper bracket, lower bracket are fixedly connected, and the upper bracket, lower bracket are respectively arranged with radial direction and hold out against fuselage
The top tight pieces of cylinder holes inner wall.Further, the grinding tool includes the shaft for being mounted on the center of the upper bracket, shaft with turn
It starts to take turns connection, grinding tool rotary head is mounted in the shaft, is rotated with the shaft, on the grinding tool rotary head
Grinding wheel is installed.Further, after grinding bracket and grinding tool install, dial gauge is mounted on grinding tool rotary head,
Centrad is adjusted, respectively to the elevation carrection of three measurement points, the depth of parallelism is adjusted, is no more than the data error of three measurement points
0.03mm；Grinding fuselage cylinder holes convex shoulder stops grinding when being ground to height L, and reconditioning is completed.
In a preferred embodiment of the invention, it after step E, is split whether there is to plane after grinding progress defect detecting test
Line carries out repair welding again and grinding work if necessary.
In a preferred embodiment of the invention, in step, using hand-held polishing machine and small-sized abrasive machine, to having occurred and that
The fuselage cylinder holes convex shoulder position of corrosion, polishes.
Using diesel engine cylinder holes convex shoulder restorative procedure of the invention, fuselage cylinder holes convex shoulder position can be effectively repaired,
Voltage endurance capability is strong, it is not easy to which fragmentation reaches cylinder sleeve and installs and uses requirement, greatly prolongs the service life of fuselage cylinder holes, the present invention
Not only cast iron Welding Problems had been solved, but also have completed the mach problem in heavy parts scene.The present invention is at low cost, is greatly saved
The cost of repairs and the expense for more renewing cylinder body, save the repairing time.
The features of the present invention sees the detailed description of the drawings of the present case and following preferable embodiment and obtains clearly
Solution.
Detailed description of the invention
Fig. 1 is the position view of diesel engine cylinder holes convex shoulder.
Fig. 2 is the flow chart of restorative procedure of the invention.
Fig. 3 is the schematic diagram for being ground bracket and grinding tool.
Specific embodiment
In order to be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, tie below
Closing specific embodiment, the present invention is further explained.
Referring to fig. 2, a kind of diesel engine cylinder holes convex shoulder restorative procedure, comprising the following steps:
A, the fuselage cylinder holes convex shoulder position for having occurred and that corrosion is beaten using hand-held polishing machine and small-sized abrasive machine
Mill removes the part of corrosion, exposes metal true qualities.
B, surface dye penetrant inspection is carried out to fuselage cylinder holes convex shoulder, checks for crackle；Such as there is crackle, polishes
It eliminates；The method of specific dye penetrant inspection is as follows:
First fuselage cylinder holes shoulder surface should be cleaned up, surface does not have apparent dirt, such as greasy dirt, corrosion, chip, paint
Then layer etc. is sufficiently cleaned with cleaning agent, last to be cleaned dose of volatilization is clean, so that fuselage cylinder holes shoulder surface keeps drying；
Bleeding agent is subjected to even application to fuselage cylinder holes shoulder surface, after spraying finishes, waits 5-15 points of about infiltration
Then clock is cleaned up the bleeding agent for being sprayed on workpiece surface using cleaning agent, so that fuselage cylinder holes shoulder surface cleans, finally
It is dried with clean calico；
After the bleeding agent of fuselage cylinder holes shoulder surface is cleaned out and dried, imaging agent is sufficiently shaken up, to fuselage
Cylinder holes shoulder surface is kept at a distance 150mm-300mm even application, after waiting a few minutes, can display defect, when necessary can be into
Row repeatedly flaw detection.
C, on the water jacket mounting plane of fuselage cylinder holes upper end, measurement point X at three, Y, Z are looked for, it is desirable that corresponding to measurement point
Fuselage cylinder holes convex shoulder position is not corrosion default, complete plane；Plane where these three measurement points, it is flat as reconditioning
Datum plane when face, datum plane are vertical with fuselage cylinder holes inner wall；It is polished flat measurement point and corresponding fuselage at three with sand paper
Rusty stain is removed at cylinder holes convex shoulder position, measures fuselage cylinder holes plane with height gauge or dial gauge, to fuselage on plane distance L, with
Technical data as defined in drawing is compared, with determining eligible for repair height after needing soldering.
Alternatively, if water jacket mounting plane out-of-flatness a standard ring can be installed additional in fuselage cylinder holes upper end, by standard ring
Datum plane when upper surface is as reconditioning is found the position of not corrosion default on fuselage cylinder holes convex shoulder, is wanted according to design
It asks, determines the vertical range at the position Yu the datum plane, with determining eligible for repair height after needing soldering.
D, using cold welding machine and wlding, on fuselage cylinder holes convex shoulder corrosion location and defect carry out repair welding；
The 9188G type welding machine that cold welding machine equipment choosing is produced by Yueqing City Polaris Electronics Co., Ltd., working principle
It is: uses advanced high-power IGBT inverter technology (AC-DC-AC-DC), external world's AC power source is converted into low-voltage,
The DC power supply of high current, source of welding current condition required for reaching, then by micro-computer technology, weld interval is carried out
It is accurately controlled, makes the electric energy converted in moment, be released between tungsten electrode and workpiece in the form of pulsed arc, temperature pole
High electric arc makes metal material workpiece and welding wire melt rapidly and be welded together, and achievees the purpose that welding.
The characteristics of this welding method and advantage are:
1, weld interval is very short, calorific value very little.
Welding can complete the fusion process of welding wire and workpiece within a few tens of milliseconds, relative to common welding machine (about several seconds)
For time, it is transmitted to the heat much less of workpiece, so workpiece substrate fever is seldom, the material temperature rise other than solder joint is small, no
Annealing can be generated, the phenomenon that discoloration.
2, substrate damage is small, indeformable, and welding is not easy to crack.
When being welded using cold welding, the molten bath volume that each weld pulse generates is less than 2mm3, the stress formed is also smaller,
Although soldering needs a many molten baths to combine, since the stress direction of solder joint disperses, the concentrated stress that workpiece is subject to compared with
It is small, so welded workpiece deformation is smaller, it is not easy to crack.
3, heat seal strength is high.
Cold welding welding is complete metallurgical welding, identical with usual electric welding welding effect.Position after welding can carry out vehicle,
Boring mills, and files, and bores, the post-productions such as mill.
Welding wire selects: to improve welding quality, it is ensured that welding effect compares by test of many times, the final choice U.S.
The nickel-base alloy specification NI-ROD44/ENiFeMn-Cl diameter 1.6mm welding wire of SMC company production is as wlding.
NI-ROD44/ENiFeMn-Cl welding wire is a kind of solid Ni-Fe-manganese welding wire, can in any position under to spheroidal graphite
Cast iron, malleable cast iron or grey cast-iron are automatically or semi-automatically welded, and the work such as weld preheating or post weld heat treatment are not needed,
It is easy to use simple and direct.
Main chemical compositions: Ni--------44 Mn------11 C-------1.5 Fe-------45
Minimum mechanical performance: tensile strength psi 100000 is roughly equal to Mpa 690
450Mpa requirement of the tensile strength higher than base material QT450.
E, installation grinding bracket and grinding tool.It referring to Fig. 3, is ground bracket and is mounted in fuselage cylinder holes, including upper bracket
11 and lower bracket 12, upper bracket, lower bracket be fixedly connected, upper bracket 11, lower bracket 12 are respectively arranged with the radial fuselage cylinder that holds out against
The top tight pieces 13 of hole inner wall.Grinding tool includes the shaft 21 for being mounted on the center of the upper bracket, shaft 21 and rotation handwheel
(not indicating in figure) connection, grinding tool rotary head 22 is mounted in shaft 21, rotates with shaft, on grinding tool rotary head 22
Grinding wheel 23 is installed, the reconditioning face 24 of grinding wheel 23 is corresponding with the upper surface of fuselage cylinder holes convex shoulder.
After grinding bracket and grinding tool install, dial gauge is mounted on grinding tool rotary head, rotation grinding work
Tool adjusts centrad respectively to the elevation carrection of three measurement points and adjusts the depth of parallelism according to the data of dial gauge；Make three
The data error of measurement point is no more than 0.03mm；Grinding fuselage cylinder holes convex shoulder stops grinding, repairs when being ground to height L
Mill is completed.
F, defect detecting test is being carried out with the presence or absence of crackle to plane after grinding, is carrying out repair welding again and grinding if necessary
Work.The altitude information of fuselage cylinder holes plane and water jacket mounting plane after measurement repairing, it is ensured that meet technology as defined in drawing
It is required that.
Using diesel engine cylinder holes convex shoulder restorative procedure of the invention, fuselage cylinder holes convex shoulder position can be effectively repaired,
Voltage endurance capability is strong, it is not easy to which fragmentation reaches cylinder sleeve and installs and uses requirement, greatly prolongs the service life of fuselage cylinder holes, the present invention
Not only cast iron Welding Problems had been solved, but also have completed the mach problem in heavy parts scene.The present invention is at low cost, is greatly saved
The cost of repairs and the expense for more renewing cylinder body, save the repairing time.
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and what is described in the above embodiment and the description is only the present invention
Principle, various changes and improvements may be made to the invention without departing from the spirit and scope of the present invention, these variation and
Improvement is both fallen in the range of claimed invention.The present invention claims protection scope by appended claims and its
Equivalent defines.
Claims (9)
1. diesel engine cylinder holes convex shoulder restorative procedure, which comprises the following steps:
A, it polishes the corrosion location of fuselage cylinder holes convex shoulder, removes the part of corrosion, expose metal true qualities；
B, surface dye penetrant inspection is carried out to fuselage cylinder holes convex shoulder, checks for crackle；Such as there is crackle, carries out polishing and disappear
It removes；
C, determine that datum plane when reconditioning fuselage cylinder holes convex shoulder, the datum plane are vertical with fuselage cylinder holes inner wall；According to setting
Meter requires, and determines the vertical range L of the datum plane Yu fuselage cylinder holes convex shoulder upper surface, needs to repair after needing soldering with determination
Height；
D, using cold welding machine and wlding, on fuselage cylinder holes convex shoulder corrosion location and defect carry out repair welding；
E, installation grinding bracket and grinding tool, and after adjusting centrad and the depth of parallelism, to fuselage cylinder holes convex shoulder carry out grinding plus
Work, be ground to it is corresponding with datum plane until, reconditioning complete.
2. diesel engine cylinder holes convex shoulder restorative procedure according to claim 1, which is characterized in that in stepb, first will
Fuselage cylinder holes shoulder surface cleans up, and fuselage cylinder holes shoulder surface is made to keep drying, then by bleeding agent to fuselage cylinder
Hole shoulder surface carries out even application and waits 5-15 minutes to be infiltrated after spraying finishes, and will be sprayed on fuselage cylinder holes using cleaning agent
The bleeding agent of shoulder surface cleans up, so that fuselage cylinder holes shoulder surface cleans, is finally dried, will be imaged with clean calico
Agent sufficiently shakes up, and keeps at a distance 150mm-300mm even application to fuselage cylinder holes shoulder surface, observes fuselage cylinder holes convex shoulder table
Face, until the size of mark trace does not change；Multiple dye penetrant inspection can be carried out when necessary.
3. diesel engine cylinder holes convex shoulder restorative procedure according to claim 1, which is characterized in that in step C, in machine
On the water jacket mounting plane of body cylinder holes upper end, measurement point X at three, Y, Z are looked for, it is desirable that fuselage cylinder holes convex shoulder corresponding to measurement point
Position is not corrosion default, complete plane；Plane where these three measurement points, benchmark when as reconditioning plane are flat
Face；According to design requirement, the vertical range of the measurement point with corresponding fuselage cylinder holes convex shoulder position is determined, need to weld with determination
Eligible for repair height after benefit.
4. diesel engine cylinder holes convex shoulder restorative procedure according to claim 1, which is characterized in that in step C, in machine
Body cylinder holes upper end installs a standard ring additional, convex in fuselage cylinder holes using the upper surface of the standard ring as datum plane when reconditioning
The position that not corrosion default is found on shoulder determines the vertical range at the position Yu the datum plane, according to design requirement with true
Surely eligible for repair height after soldering is needed.
5. diesel engine cylinder holes convex shoulder restorative procedure according to claim 3, which is characterized in that described in step E
Grinding bracket is mounted in fuselage cylinder holes, including upper bracket and lower bracket, the upper bracket, lower bracket are fixedly connected, it is described on
Bracket, lower bracket are respectively arranged with the radial top tight pieces for holding out against fuselage cylinder holes inner wall.
6. diesel engine cylinder holes convex shoulder restorative procedure according to claim 5, which is characterized in that the grinding tool packet
The shaft for being mounted on the center of the upper bracket is included, shaft is connect with rotation handwheel, and grinding tool rotary head is mounted on described turn
It on axis, is rotated with the shaft, grinding wheel is installed on the grinding tool rotary head.
7. diesel engine cylinder holes convex shoulder restorative procedure according to claim 6, which is characterized in that grinding bracket and grinding
After tool installs, dial gauge is mounted on grinding tool rotary head, centrad is adjusted, respectively to the height of three measurement points
Measurement adjusts the depth of parallelism, and the data error of three measurement points is made to be no more than 0.03mm；Grinding fuselage cylinder holes convex shoulder, works as mill
When cutting height L, stop grinding.
8. diesel engine cylinder holes convex shoulder restorative procedure according to claim 1, which is characterized in that after step E, right
Plane after grinding, which carries out defect detecting test, whether there is crackle, carry out repair welding again and grinding work if necessary.
9. diesel engine cylinder holes convex shoulder restorative procedure according to claim 1, which is characterized in that in step, use
Hand-held polishing machine and small-sized abrasive machine polish to the fuselage cylinder holes convex shoulder position for having occurred and that corrosion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910789167.3A CN110449824B (en) | 2019-08-26 | 2019-08-26 | Repairing method for cylinder hole shoulder of diesel engine body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910789167.3A CN110449824B (en) | 2019-08-26 | 2019-08-26 | Repairing method for cylinder hole shoulder of diesel engine body |
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| Publication Number | Publication Date |
|---|---|
| CN110449824A true CN110449824A (en) | 2019-11-15 |
| CN110449824B CN110449824B (en) | 2020-12-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910789167.3A Active CN110449824B (en) | 2019-08-26 | 2019-08-26 | Repairing method for cylinder hole shoulder of diesel engine body |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110948174A (en) * | 2019-11-26 | 2020-04-03 | 中国第一汽车股份有限公司 | Method for repairing casting defects of castings |
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2019
- 2019-08-26 CN CN201910789167.3A patent/CN110449824B/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110948174A (en) * | 2019-11-26 | 2020-04-03 | 中国第一汽车股份有限公司 | Method for repairing casting defects of castings |
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| CN110449824B (en) | 2020-12-22 |
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