CN107740120A - The restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion - Google Patents
The restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion Download PDFInfo
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- CN107740120A CN107740120A CN201711045201.3A CN201711045201A CN107740120A CN 107740120 A CN107740120 A CN 107740120A CN 201711045201 A CN201711045201 A CN 201711045201A CN 107740120 A CN107740120 A CN 107740120A
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- China
- Prior art keywords
- laser
- cavitation erosion
- cavitation
- blade tip
- polishing
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- 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.)
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
- C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
- C23C24/106—Coating with metal alloys or metal elements only
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
- C23F17/00—Multi-step processes for surface treatment of metallic material involving at least one process provided for in class C23 and at least one process covered by subclass C21D or C22F or class C25
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion proposed by the present invention should, it is intended to repairs area's fine microstructures, the high restorative procedure of anti-cavitation ability for a kind of.The technical scheme is that：Polishing cavitation erosion hole is filed with Pneumatic rotary first, excludes all cavitation erosion defects；Secondly, optical maser wavelength 1070nm, 500~600W of laser power, 3~4g/min of powder sending quantity, spot diameter 1.5mm, sweep speed 4mm/s, individual layer height are set:0.5mm, overlapping rate:50% technological parameter, cavitation erosion hole defect is repaired using the laser cladding method of synchronous powder feeding system；Then polish by hand to the vane wheel profile forming polishing repairing type after laser melting coating reparation；It is 1064nm to reset optical maser wavelength, and laser energy is 7~8J, and spot diameter is 4~5mm, and laser pulse width is 10ns technological parameter, restoring area is carried out with laser shock peening method two-sided strengthened.
Description
Technical field
The present invention relates to aerial motor spare part to repair field, is mainly used in repairing for reinforcing impeller of pump blade tip cavitation erosion hole
Compound method.
Background technology
Aeroplane engine is reinforced impeller of pump and rotated at a high speed with the rotating speed of ten thousand revs/min of (2.7~3.0), blade tip surface due to
Occur substantial amounts of cavitation erosion hole in the presence of cavitation damage and scrap.The method of generally use is the method using welding by gas at present
Pit filling is repaired, and is then reused, and is that the anti-cavitation ability of impeller is not still carried effectively the shortcomings that this method
It is high.If coating the coating of anti-cavitation using surface, because wheel speed is especially high, table is easily caused during running at high speed
The localized delamination of finishing coat and engine is broken down.
With laser impact intensified continuous development, played an important role in terms of part life is improved.Laser rushes
It is an advanced green process for treating surface to hit reinforcing, has efficient, cleaning, low consumption, ultrafast particular advantages, is rushed through laser
After hitting ripple reinforcing, tensile property, fatigue behaviour, friction and wear behavior and corrosion resistance of material etc., largely
All it is improved.Based on laser impact intensified particular advantages, will be played an important role in terms of impeller cavitation erosion ability is improved,
Not open report repairs the related data of aeroplane engine reinforcing impeller of pump using reiforcing laser impact technology both at home and abroad.
The content of the invention
The present invention is in place of above-mentioned the shortcomings of the prior art, there is provided one kind repairs area's fine microstructures, anti-cavitation energy
Power is high, the method that can effectively repair the cavitation erosion of aeroengine thrust augmentation impeller of pump blade tip.
The above-mentioned purpose of the present invention can be reached by following measures, a kind of engine reinforcing impeller of pump blade tip cavitation erosion
Restorative procedure, it is characterised in that comprise the following steps：Cavitation erosion hole → laser melting coating reparation cavitation erosion hole → polishing is removed using polishing
The reparation flow of repairing type → laser impact intensified restoring area；Polishing cavitation erosion hole is filed with Pneumatic rotary first, excludes all cavitation erosions
Defect；Secondly, cavitation erosion hole defect is repaired using the laser cladding method of synchronous powder feeding system, technological parameter uses：Laser
Wavelength 1070nm, 500~600W of laser power, 3~4g/min of powder sending quantity, spot diameter 1.5mm, sweep speed 4mm/s, cladding
Individual layer height:0.5mm, overlapping rate:50%；With 45~105 μm of TC4 titanium alloy spherical powders of powder size；Then use
The method of manual grinding, the vane wheel profile forming polishing repairing type after laser melting coating reparation is recovered；Again using laser impact intensified
Method is two-sided strengthened to restoring area progress, and technological parameter is：Laser wavelength is 1064nm, and laser energy is 7~8J, hot spot
A diameter of 4~5mm, laser pulse width are 10ns technological parameter, are overlapped using circular light spot, overlapping rate 50%, restraint layer
Using water, absorbed layer uses black belt.
The present invention has the advantages that compared to prior art.
The present invention removes cavitation erosion hole → laser melting coating reparation cavitation erosion hole → polishing repairing type → laser impact intensified using polishing
After the reparation flow of restoring area, laser melting coating and laser impact intensified reparation, area's fine microstructures are repaired, are formed in restoring area
Residual compressive stress layer after one layer of 0.8~1.0mm, significantly improves the anti-cavitation ability of part, impeller life bring up to 2.0 times with
On, it the composite can be widely applied to the reparation in aeroengine thrust augmentation impeller of pump large area cavitation erosion hole.
Embodiment
Describe to be used to disclose the present invention below so that those skilled in the art can realize the present invention.It is excellent in describing below
Embodiment is selected to be only used as illustrating, it may occur to persons skilled in the art that other obvious modifications.
According to the present invention, cavitation erosion hole → laser melting coating reparation cavitation erosion hole → polishing repairing type → laser-impact is removed using polishing
Strengthen restoring area and repair flow, file polishing cavitation erosion hole with Pneumatic rotary first, exclude all cavitation erosion defects；Secondly, using same
The laser cladding method for walking powder feeding is repaired to cavitation erosion hole defect, and technological parameter is：Laser wavelength 1070nm, laser power
500~600W, 3~4g/min of powder sending quantity, spot diameter 1.5mm, sweep speed 4mm/s, the individual layer height of cladding:0.5mm, take
Connect rate:50%, with 45~105 μm of TC4 titanium alloy spherical powders of powder size；Then the method for using manual grinding, to swashing
Vane wheel profile forming polishing repairing type after light cladding reparation is recovered；Restoring area is carried out using laser shock peening method again double
Surface strengthening, technological parameter are：Laser wavelength is 1064nm, and laser energy is 7~8J, and spot diameter is 4~5mm, laser arteries and veins
The technological parameter that width is 10ns is rushed, is overlapped using circular light spot, overlapping rate 50%, restraint layer uses water, and absorbed layer is using black
Coloring agent band.
Embodiment 1
There is large area cavitation erosion hole for engine reinforcing impeller of pump blade tip after 500h running life.Using this
Invention is repaired, and is filed first using Pneumatic rotary and cavitation erosion hole is polished, exclude all cavitation erosion defects；Joined again using technique
Number is：Laser wavelength 1070nm, laser power 500W, powder sending quantity 4g/min, spot diameter 1.5mm, sweep speed 4mm/s,
The individual layer height of cladding:0.5mm, overlapping rate:50%；Powder uses TC4 titanium alloy spherical powders, 45~105 μm of powder size,
Defect is repaired with the laser cladding method of synchronous powder feeding system, then using the method for manual grinding, vane wheel profile forming carried out
Recover.Optical maser wavelength is finally used as 1064nm, laser energy 7J, spot diameter 4mm, laser pulse width 10ns,
Overlapped using circular light spot, overlapping rate 50%, restraint layer uses water, and absorbed layer uses black belt, with laser impact intensified side
Method carries out two-sided strengthened to restoring area.By test analysis, the impeller that this method is strengthened is repairing one floor 0.8mm's of area's formation
Residual compressive stress layer, fine microstructures, component-level field investigation show repair after booster pump impeller life can reach 1200h with
On, the life-span brings up to 2.4 times.
Embodiment 2
There is large area cavitation erosion hole for engine reinforcing impeller of pump blade tip after 500h running life.Using this
Invention is repaired, and cavitation erosion hole is polished using Pneumatic rotary file, excludes all cavitation erosion defects.Technological parameter is used again
For：Laser wavelength 1070nm, laser power 600W, powder sending quantity 5g/min, spot diameter 1.5mm, sweep speed 4mm/s, melt
The individual layer height covered:0.5mm, overlapping rate:50%.Powder uses TC4 titanium alloy spherical powders, 45~105 μm of powder size, uses
The laser cladding method of synchronous powder feeding system is repaired to defect；Then the method for using manual grinding, vane wheel profile forming is carried out extensive
It is multiple, finally use optical maser wavelength laser energy 8J, spot diameter 5mm, laser pulse width 10ns, to be adopted for 1064nm
Overlapped with circular light spot, overlapping rate 50%, restraint layer uses water, and absorbed layer uses black belt, uses laser shock peening method
Restoring area is carried out two-sided strengthened.By test analysis, the impeller that this method is strengthened is repairing one floor 0.95mm's of area's formation
Residual compressive stress layer, fine microstructures, component-level field investigation show repair after booster pump impeller life can reach 1500h with
On, the life-span brings up to 3.0 times.
General principle, principal character and the advantages of the present invention of the present invention has been shown and described above.The technology of the industry
For personnel it should be appreciated that the present invention is not limited to the above embodiments, that described in above-described embodiment and specification is the present invention
Principle, various changes and modifications of the present invention are possible without departing from the spirit and scope of the present invention, these change and
Improvement is both fallen within the range of claimed invention.The protection domain of application claims by appended claims and its
Equivalent defines.
Claims (1)
1. a kind of restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion should, it is characterised in that comprises the following steps：Using beating
Grind off degasification pit → laser melting coating reparation cavitation erosion hole → polishing repairing type → laser impact intensified restoring area and repair flow, with swashing
The cladding of light shock peening is repaired blade tip cavitation range and carried out again laser impact intensified；First polishing cavitation erosion is filed with Pneumatic rotary
Hole, excludes all cavitation erosion defects；Secondly, setting, optical maser wavelength 1070nm, 500~600W of laser power, 3~4g/ of powder sending quantity
Min, spot diameter 1.5mm, sweep speed 4mm/s, individual layer height:0.5mm, overlapping rate:50% technological parameter, with powder grain
The TC4 spherical powders of 45~105 μm of degree, cavitation erosion hole defect is repaired using the laser cladding method of synchronous powder feeding system；Then
Using the method for manual grinding, the vane wheel profile forming polishing repairing type after laser melting coating reparation is recovered；Reset optical maser wavelength
For 1064nm, laser energy is 7~8J, and spot diameter is 4~5mm, and laser pulse width is 10ns technological parameter, using circle
Shape hot spot overlaps, and overlapping rate 50%, restraint layer uses water, and absorbed layer uses black belt, with laser shock peening method to repairing
Multiple region carries out two-sided strengthened.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711045201.3A CN107740120A (en) | 2017-10-31 | 2017-10-31 | The restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711045201.3A CN107740120A (en) | 2017-10-31 | 2017-10-31 | The restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107740120A true CN107740120A (en) | 2018-02-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711045201.3A Pending CN107740120A (en) | 2017-10-31 | 2017-10-31 | The restorative procedure of engine reinforcing impeller of pump blade tip cavitation erosion |
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| CN (1) | CN107740120A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111633374A (en) * | 2020-06-01 | 2020-09-08 | 湖北三江航天江北机械工程有限公司 | Method for repairing damage inside attitude control engine combustion chamber shell |
| CN111962064A (en) * | 2020-07-28 | 2020-11-20 | 江苏大学 | Method for strengthening surface shape memory alloy coating of axial flow pump blade through jet cavitation |
-
2017
- 2017-10-31 CN CN201711045201.3A patent/CN107740120A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111633374A (en) * | 2020-06-01 | 2020-09-08 | 湖北三江航天江北机械工程有限公司 | Method for repairing damage inside attitude control engine combustion chamber shell |
| CN111962064A (en) * | 2020-07-28 | 2020-11-20 | 江苏大学 | Method for strengthening surface shape memory alloy coating of axial flow pump blade through jet cavitation |
| CN111962064B (en) * | 2020-07-28 | 2022-04-26 | 江苏大学 | Method for strengthening surface shape memory alloy coating of axial flow pump blade through jet cavitation |
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Application publication date: 20180227 |