CN106392342A - Laser drilling device and method for gas turbine blade - Google Patents
Laser drilling device and method for gas turbine blade Download PDFInfo
- Publication number
- CN106392342A CN106392342A CN201611103992.6A CN201611103992A CN106392342A CN 106392342 A CN106392342 A CN 106392342A CN 201611103992 A CN201611103992 A CN 201611103992A CN 106392342 A CN106392342 A CN 106392342A
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- China
- Prior art keywords
- gas turbine
- turbine blades
- galvanometer
- infrared laser
- laser
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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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/36—Removing material
- B23K26/38—Removing material by boring or cutting
- B23K26/382—Removing material by boring or cutting by boring
-
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/02—Positioning or observing the workpiece, e.g. with respect to the point of impact; Aligning, aiming or focusing the laser beam
- B23K26/04—Automatically aligning, aiming or focusing the laser beam, e.g. using the back-scattered light
- B23K26/046—Automatically focusing the laser beam
-
- 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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
- B23K26/702—Auxiliary equipment
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention relates to a laser drilling device and method for a gas turbine blade. The laser drilling device comprises a control system, an infrared detection system and a drilling system. The drilling system comprises an infrared laser device for transmitting infrared pulse lasers. The infrared pulse lasers transmit a focusing lens, a galvanometer and a telecentric field lens which are arranged in sequence and then are focused onto the surface of the gas turbine blade. The infrared detection system is used for scanning the profile of the surface of the gas turbine blade under the control of the control system. The control system is used for controlling the deflection angle of the galvanometer and controlling the galvanometer and the telecentric field lens to move in the vertical direction according to the profile of the surface of the gas turbine blade for adjusting the position of a focusing point focused onto the surface of the gas turbine blade so as to drill the specified position of the surface of the gas turbine blade. By the adoption of the technical scheme of the laser drilling device and method for the gas turbine bade, the hole size and the hole position of the surface of the blade are controlled precisely, so that the hole wall surface of a drilled hole is smooth, and the strength of the blade with the drilled hole is kept high.
Description
Technical field
The present invention relates to machining technology field, more particularly, to a kind of laser hole drilling system of gas turbine blades and side
Method.
Background technology
Raising living environment being required with people, utilizes aspect in production of energy, gas turbine power generation technology should
With being increasingly subject to people's attention.In China, the enforcement of West-East National Gas Transmission Project and the development of Coke Industry so that increasingly
Many coal gas output units, in the urgent need to finding the new way of energy effectively utilizes, become coke-stove gas using gas turbine power generation
One of optimum selection of application.
In order to optimize ability and the efficiency of multiple circulating generation unit, turbine inlet temperature must be as high as possible.This will carry
The temperature of high flame, and then lead to the growth of NOx emission producing will be exceeded.Therefore designer have to find combustor and
The construction featuress of turbine, these features are allowed to retain cooling air using as combustion air.This is to higher temperature and less cold
But the combination of the demand of air introduces other concepts in Complicated Periodic or steam cooling.
Traditional blade boring method is using mechanical cutter head or spark machined, and this method of mechanical cutter head boring is easy
Cause material substrate to damage, crackle is also larger, and efficiency is slower, and cutter head is very expensive and easy to wear, need to regularly replace；Electrical spark working
Work, though higher than mechanical cutter head borehole accuracy, the ceramic material that blade surface specially can be sputtered in reality processing produces
Raw destruction, leads to waste paper, shortens the service life of blade.And these drilling operatings are usually associated with cutting adjuvant, liquid
Adjuvant stick problem so that cutting tangent plane relatively rough, there is fine crackle and local stress.Must also enter after cutting
The post processings such as row cleaning, polishing.
Content of the invention
The technical problem to be solved is to provide a kind of laser hole drilling system of gas turbine blades, overcomes tradition
Blade boring method blade is caused damage defect.
For this purpose it is proposed, the present invention proposes a kind of laser hole drilling system of gas turbine blades, including：Control system, red
Outer detection system and hole-drilling system；Described hole-drilling system includes：For launch pulsed infrared laser infrared laser and according to
The focus lamp of secondary setting, galvanometer and telecentricity field lens；Described pulsed infrared laser is through the focus lamp, galvanometer and the telecentricity that set gradually
Described gas turbine blades surface is focused on after field lens；
Described IRDS is used under the control of described control system, and the profile on gas turbine blades surface is entered
Row scanning；
Described control system be used for being controlled according to the profile on described gas turbine blades surface the deflection angle of described galvanometer with
And control described galvanometer and telecentricity field lens in the vertical direction to move, to adjust Jiao focusing on described gas turbine blades surface
The position of point, holes to the specified location on described gas turbine blades surface.
Preferably, the optical axis rotation that described focus lamp is located around it, through the described infrared pulse of described focus lamp outgoing
Laser rotates around described optical axis.
Preferably, described hole-drilling system also includes：The optical gate being connected with the outfan of described infrared laser and described light
The reflecting mirror that the beam expanding lens of the outfan linking of lock is connected with the outfan of described beam expanding lens；
Described pulsed infrared laser through setting gradually described optical gate, beam expanding lens, enter described focus lamp after reflecting mirror.
Preferably, this device also includes：Sample fixed platform, it is separately positioned on the air blowing of described sample fixed platform both sides
System and dust-precipitating system；
Described scavenger system is used for blow gas；Described dust-precipitating system is matched with described scavenger system, for collecting
State the gas through described sample fixed station of scavenger system blowout.
Preferably, the surface of described gas turbine blades scribbles Protection glue, and the inside of described gas turbine blades is filled with
Teflon material.
On the other hand, the embodiment of the present invention additionally provide a kind of using any one described gas turbine blades above-mentioned
The method that laser hole drilling system carries out laser drill to gas turbine blades, the method includes：
Control IRDS that the profile on described gas turbine blades surface is scanned；
Control infrared laser transmitting pulsed infrared laser；Wherein, described pulsed infrared laser is poly- through set gradually
Described gas turbine blades surface is focused on after Jiao Jing, galvanometer and telecentricity field lens；
According to the profile on described gas turbine blades surface, control the deflection angle of galvanometer and control described galvanometer and telecentricity
Field lens in the vertical direction moves, to adjust the position of the focus focusing on described gas turbine blades surface, to described combustion gas
The specified location on turbine blade surface is holed.
Preferably, the optical axis rotation that described focus lamp is located around it, through the described infrared pulse of described focus lamp outgoing
Laser rotates around described optical axis.
Preferably, described pulsed infrared laser through setting gradually optical gate, beam expanding lens, enter described focusing after reflecting mirror
Mirror.
Preferably, while the specified location to described gas turbine blades surface is holed, also include：
By being arranged on the scavenger system blow gas of sample fixed platform side；
By being arranged on the dust-precipitating system that matches with described scavenger system of described sample fixed platform opposite side, collect institute
State the gas through described sample fixed station of scavenger system blowout.
Preferably, before the profile to gas turbine blades surface is scanned, also include：
In the surface-coated protective layer of described gas turbine blades, and fill Teflon in the inside of described gas turbine blades
Grand material.
The laser hole drilling system of gas turbine blades provided in an embodiment of the present invention and method, by high-power infrared sharp
Pulsed infrared laser launched by light device, and by means of IRDS, blade surface area is scanned and feeds back to control system
System, is controlled the position of galvanometer by control system according to scanning result, thus adjusting the position of focus, so that the blade processed
Surface all in high-power iraser focus so that blade surface pass size and hole site precise control, to reach brill
Hole wall surface of the hole is relatively smooth, and boring rear blade intensity keeps higher, the processing effect of pass size and position holding high levels.
Brief description
The features and advantages of the present invention can be more clearly understood from by reference to accompanying drawing, accompanying drawing is schematic and should not manage
Solution is to carry out any restriction to the present invention, in the accompanying drawings：
Fig. 1 is to embodiments provide a kind of structural representation of the laser hole drilling system of gas turbine blades；
Fig. 2 is to embodiments provide a kind of schematic flow sheet of the method for drilling holes of gas turbine blades.
Specific embodiment
Below in conjunction with accompanying drawing, embodiments of the present invention is described in detail.
It should be noted that traditional gas turbine blades boring is using mechanical cutter head and spark machined, can be to processing
The substrate of material causes to damage or the ceramic material of blade surface is damaged, the use leading to waste paper or shortening blade
In the life-span, also need after piercing to be carried out the treatment process such as polishing.The embodiment of the present invention can avoid these using laser drill
The appearance of problem, and laser has noncontact, the characteristic such as free from environmental pollution, easy to control.First, gas turbine blades are nickeliferous
The resistant to elevated temperatures metal material of base, intensity and hardness are higher, and traditional machining and spark machined simultaneously are not suitable for processing.Its
Secondary, as a kind of novel processing method, the suitability to material is stronger, and the blade surface of suitable different curve adds for laser
Work；And the produced Instantaneous peak power of high-power pulse laser is extremely strong, can moment blade surface matrix material be removed, and right
Base material injury is less.So the embodiment of the present invention carries out blade boring using infrared laser as lasing light emitter, by means of
External optical system, under unique focusing arrangement, to realize the means that a kind of laser of novelty is holed to blade surface.
As shown in figure 1, embodiments providing a kind of laser hole drilling system of gas turbine blades, this device bag
Include：Control system, IRDS 8 and hole-drilling system；Described hole-drilling system includes：For launching the red of pulsed infrared laser
Outer laser instrument 1 and the focus lamp 5 setting gradually, galvanometer 6 and telecentricity field lens 7；Described pulsed infrared laser is through setting gradually
Focus lamp 5, focus on described gas turbine blades surface after galvanometer 6 and telecentricity field lens 7；
Described IRDS 8 is used for the profile under the control of described control system, to gas turbine blades surface
It is scanned；
Described control system is used for the profile according to described gas turbine blades surface, controls the deflection angle of described galvanometer 6
And control described galvanometer 6 and telecentricity field lens 7 in the vertical direction to move, focus on described gas turbine blades surface to adjust
Focus position, the specified location on described gas turbine blades surface is holed.
It should be noted that gas turbine blades are higher to ir-absorbance containing Ni-based resistant to elevated temperatures high hard
Metal material, the pulsed infrared laser of strong absorbing wavelength 1064nm of high temperature resistant nickel based metal class material, so the present invention is implemented
Example can be the infrared pulsed lasers of 1064nm using the higher wavelength of absorbance, thus almost all of laser energy can
Gas turbine blades surface is absorbed.Meanwhile, laser spot can be high with respect to processed gas turbine blades surface pass
Speed moves up and down and light beam energy high-speed rotation, and laser spot can form required boring line of cut, it will makes laser spot
Advanced downwards along fixing Cutting Road, until being finally completed the punching of gas turbine blades.Laser beam axis move to next again
Blade pass direction, is so repeatedly completed the processing of blade surface pass.
Specifically, in the fixing sample fixed platform of gas turbine blades to be processed, and by means of IRDS 8
Gas turbine blades surface region is scanned and scanning result is fed back to control system.Control system controls iraser
Device 1 launches pulsed infrared laser, and the contour shape on the gas turbine surface obtaining according to scanning, by controlling galvanometer 6 motor
Galvanometer 6 is driven to deflect, galvanometer 6 includes X-axis galvanometer 6 and Y-axis galvanometer 6, by changing the inclined of X-axis galvanometer 6 and Y-axis galvanometer 6
Corner, all can change the position of the focus focusing on gas turbine blades surface after telecentricity field lens 7, by controlling galvanometer
6 and telecentricity field lens 7 is lower in the Z-axis direction moves, such that it is able to make focus move up and down, to ensure processed blade surface all
In high-power iraser focus, and then realize the drill precise holes to blade for the pulsed infrared laser of high-energy.Wherein, red
Outer pulse laser, after focus lamp 5 focusing, forms circular light spot, after galvanometer 6 and telecentricity field lens 7, makes light path in leaf
Less hot spot is focused on piece, so that the laser focusing that energy is higher, density is higher is to required machining area.
The laser hole drilling system of gas turbine blades provided in an embodiment of the present invention, is sent out by high-power infrared laser
Penetrate pulsed infrared laser, and by means of IRDS, blade surface area is scanned and feeds back to control system, by
Control system controls the position of galvanometer according to scanning result, thus adjusting the position of focus, so that the blade surface processed
So that blade surface pass size and hole site precise control all in high-power iraser focus, to reach drilling hole
Wall is relatively smooth, and boring rear blade intensity keeps higher, the processing effect of pass size and position holding high levels.
On the basis of above-described embodiment, the optical axis rotation that described focus lamp 5 is located around it, go out through described focus lamp 5
The described pulsed infrared laser penetrated rotates around described optical axis, so that light beam high-speed rotation, the boring line of cut required for being formed.
Further, described hole-drilling system also includes：The optical gate 2 being connected with the outfan of described infrared laser 1 and described optical gate 2
Outfan linking the reflecting mirror 4 that is connected with the outfan of described beam expanding lens 3 of beam expanding lens 3；Described pulsed infrared laser passes through
Described focus lamp 5 is entered after the described optical gate 2 that sets gradually, beam expanding lens 3, reflecting mirror 4.
In optic path, optical gate 2 plays the external control of laser break-make, is not at laser being hindered during machining state
Block, also function to certain protective effect, prevent operator to be subject to unexpected injury.The enlargement ratio of beam expanding lens 3 can from 5～10 times
Adjust, its effect is to 5-10 times before and to be collimated the enlarged-diameter of laser beam, makes the depth of parallelism of outgoing beam more
Good, be conducive to being focused light beam in follow-up system.This reflecting mirror 4 is 45 ° of completely reflecting mirrors, and reflecting mirror 4 primarily serves
The effect of optical path-deflecting, the distance between reflecting mirror 4 and beam expanding lens 3 specifically do not limit, but its position is in Machine Design
When eyeglass center holding level of trying one's best consistent or vertically consistent (in Fig. 1, light path corner is right angle, realizes vertical changed course), with
Facilitate the regulation of light path, reach focus lamp 5 after the vertical changed course of light path, be focused by focus lamp 5, form circular light spot, then
Telecentricity field lens 7 is reached so that light path is focused into less hot spot on blade by galvanometer 6, so that energy is more concentrated, more sharp
Control with bore size and position.
On the basis of above-described embodiment, the laser hole drilling system of gas turbine blades provided in an embodiment of the present invention also wraps
Include：Sample fixed platform, the scavenger system 9 being separately positioned on described sample fixed platform both sides and dust-precipitating system 10；Described blow
Gas system 9 is used for blow gas；Described dust-precipitating system 10 is matched with described scavenger system 9, for collecting described scavenger system 9
The gas through described sample fixed station 11 of blowout.
It should be noted that scavenger system 9 is located at the side of sample fixed station 11, in order to beneficial to boring, pass through to blow
Gas system 9 is blown and to be taken away dust and residue during blade processing etc., simultaneously can be in the opposite side of sample fixed station 11
Setting dust-precipitating system 10, to receive scavenger system 9 blowout the gas through described sample fixed station 11, thus collect dust and
Residue.
Wherein, in order to improve process repeatability and the stability of laser drill blade, gas turbine blades hole to be drilled
Surface scribbles Protection glue, and the inside of gas turbine blades is filled with teflon material.Specifically, before boring, by gas turbine
Leaf cleaning is clean, and applies last layer Protection glue, after being spaced 1 hour, repastes last layer Protection glue, glue stable curing to be protected
Afterwards, in blade, filling teflon material, to protect inner chamber, secures the vanes in the particular jig of sample fixed station 11 afterwards
Carry out follow-up drilling operating.The test of corresponding pass can be made using specific measurer such as divider after piercing it is ensured that each aperture
Size meets design requirement, and the gas turbine blades after boring can be done with air-flow detection and pass through and carry out to verify air-flow
Thermal imaging detection is minimum to ensure aperture edge crackle, improves the quality of gas turbine blades.
On the other hand, as shown in Fig. 2 the embodiment of the present invention additionally provides a kind of swashing using above-mentioned gas turbine blades
The method that light drilling equipment carries out laser drill to gas turbine blades, the method comprises the following steps：
S1：Control IRDS 8 that the profile on described gas turbine blades surface is scanned；
S2：Control infrared laser 1 transmitting pulsed infrared laser；Wherein, described pulsed infrared laser is through setting gradually
Focus lamp 5, focus on described gas turbine blades surface after galvanometer 6 and telecentricity field lens 7；
S3：According to the profile on described gas turbine blades surface, control the deflection angle of galvanometer 6 and control described galvanometer 6
Move with telecentricity field lens 7 in the vertical direction, to adjust the position of the focus focusing on described gas turbine blades surface, to institute
The specified location stating gas turbine blades surface is holed.
It should be noted that above-mentioned steps S1-S3 are with control system as executive agent, specifically, combustion gas wheel to be processed
In the fixing sample fixed platform of machine blade, and by means of IRDS 8, gas turbine blades surface region is swept
Retouch and scanning result is fed back to control system.Control system controls infrared laser 1 transmitting pulsed infrared laser, and according to sweeping
Retouch the contour shape on the gas turbine surface obtaining, drive galvanometer 6 to deflect by controlling galvanometer motor, galvanometer 6 includes X-axis
Galvanometer and Y-axis galvanometer, by changing the deflection angle of X-axis galvanometer and Y-axis galvanometer, all can change and focus on after telecentricity field lens 7
In the position of the focus on gas turbine blades surface, by controlling galvanometer 6 and telecentricity field lens 7 lower movement in the Z-axis direction, thus
Focus can be made to move up and down, to ensure processed blade surface all in high-power iraser focus, and then realize
The drill precise holes to blade for the pulsed infrared laser of high-energy.Wherein, pulsed infrared laser, after focus lamp 5 focusing, is formed
Circular light spot, after galvanometer 6 and telecentricity field lens 7, makes light path be focused into less hot spot on blade, so that energy is more
The laser focusing high, density is higher is to required machining area.
The method for drilling holes of gas turbine blades provided in an embodiment of the present invention, is sent out by high-power infrared laser
Penetrate pulsed infrared laser, and by means of IRDS, blade surface area is scanned and feeds back to control system, by
Control system controls the position of galvanometer according to scanning result, thus adjusting the position of focus, so that the blade surface processed
So that blade surface pass size and hole site precise control all in high-power iraser focus, to reach drilling hole
Wall is relatively smooth, and boring rear blade intensity keeps higher, the processing effect of pass size and position holding high levels.
On the basis of above-described embodiment, the optical axis rotation that described focus lamp 5 is located around it, go out through described focus lamp 5
The described pulsed infrared laser penetrated rotates around described optical axis.
On the basis of above-described embodiment, described pulsed infrared laser passes through the optical gate 2 setting gradually, beam expanding lens 3, reflection
Described focus lamp 5 is entered after mirror 4.
Wherein preferably, in order to remove the dust in the course of processing and residue, to described gas turbine blades surface
While specified location is holed, also include：
By being arranged on scavenger system 9 blow gas of sample fixed platform side；
By being arranged on the dust-precipitating system 10 that matches with described scavenger system 9 of described sample fixed platform opposite side, receive
Collect the gas through described sample fixed station 11 of described scavenger system 9 blowout.
Wherein preferably, in order to protect to gas turbine blades, carry out in the profile to gas turbine blades surface
Before scanning, also include：
In the surface-coated protective layer of described gas turbine blades, and fill Teflon in the inside of described gas turbine blades
Grand material.
Although being described in conjunction with the accompanying embodiments of the present invention, those skilled in the art can be without departing from this
Various modifications and variations are made, such modification and modification each fall within by claims in the case of bright spirit and scope
Within limited range.
Claims (10)
1. a kind of laser hole drilling system of gas turbine blades is it is characterised in that include：Control system, IRDS and
Hole-drilling system；Described hole-drilling system includes：For the infrared laser launching pulsed infrared laser and the focusing setting gradually
Mirror, galvanometer and telecentricity field lens；Described pulsed infrared laser focuses on after the focus lamp, galvanometer and the telecentricity field lens that set gradually
Described gas turbine blades surface；
Described IRDS is used under the control of described control system, and the profile on gas turbine blades surface is swept
Retouch；
Described control system is used for the profile according to described gas turbine blades surface, controls deflection angle and the control of described galvanometer
Make described galvanometer and telecentricity field lens in the vertical direction moves, to adjust the focus focusing on described gas turbine blades surface
Position, holes to the specified location on described gas turbine blades surface.
2. device according to claim 1 is it is characterised in that the optical axis rotation that is located around it of described focus lamp, Jing Guosuo
The described pulsed infrared laser stating focus lamp outgoing rotates around described optical axis.
3. device according to claim 1 is it is characterised in that described hole-drilling system also includes：With described infrared laser
The beam expanding lens that is connected with the outfan of described optical gate of optical gate of outfan linking be connected with the outfan of described beam expanding lens
Reflecting mirror；
Described pulsed infrared laser through setting gradually described optical gate, beam expanding lens, enter described focus lamp after reflecting mirror.
4. device according to claim 1 is it is characterised in that also include：Sample fixed platform, it is separately positioned on described sample
The scavenger system of product fixed platform both sides and dust-precipitating system；
Described scavenger system is used for blow gas；Described dust-precipitating system is matched with described scavenger system, for blowing described in collecting
The gas through described sample fixed station of gas system blowout.
5. device according to claim 1 is it is characterised in that the surface of described gas turbine blades scribbles Protection glue, institute
The inside stating gas turbine blades is filled with teflon material.
6. a kind of laser hole drilling system of the gas turbine blades described in employing claim 1-5 any one is to gas turbine leaf
Piece carries out the method for laser drill it is characterised in that including：
Control IRDS that the profile on described gas turbine blades surface is scanned；
Control infrared laser transmitting pulsed infrared laser；Wherein, described pulsed infrared laser through setting gradually focus lamp,
Described gas turbine blades surface is focused on after galvanometer and telecentricity field lens；
According to the profile on described gas turbine blades surface, control the deflection angle of galvanometer and control described galvanometer and telecentricity field lens
In the vertical direction moves, to adjust the position of the focus focusing on described gas turbine blades surface, to described gas turbine
The specified location of blade surface is holed.
7. method according to claim 6 is it is characterised in that the optical axis rotation that is located around it of described focus lamp, Jing Guosuo
The described pulsed infrared laser stating focus lamp outgoing rotates around described optical axis.
8. method according to claim 6 it is characterised in that described pulsed infrared laser through setting gradually optical gate,
Described focus lamp is entered after beam expanding lens, reflecting mirror.
9. method according to claim 6 is it is characterised in that enter in the specified location to described gas turbine blades surface
While row boring, also include：
By being arranged on the scavenger system blow gas of sample fixed platform side；
By being arranged on the dust-precipitating system that matches with described scavenger system of described sample fixed platform opposite side, blow described in collection
The gas through described sample fixed station of gas system blowout.
10. method according to claim 6 is it is characterised in that be scanned in the profile to gas turbine blades surface
Before, also include：
In the surface-coated protective layer of described gas turbine blades, and fill polytetrafluoroethylene material in the inside of described gas turbine blades
Material.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201611103992.6A CN106392342A (en) | 2016-12-05 | 2016-12-05 | Laser drilling device and method for gas turbine blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611103992.6A CN106392342A (en) | 2016-12-05 | 2016-12-05 | Laser drilling device and method for gas turbine blade |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109014623A (en) * | 2018-09-13 | 2018-12-18 | 苏州新火花机床有限公司 | A kind of numerical control ultra-short pulse laser micro hole machining device |
| CN110523715A (en) * | 2019-08-28 | 2019-12-03 | 中国人民解放军国防科技大学 | Method and device for ultrafast laser cleaning of surface of aluminum alloy reflector |
| CN113798701A (en) * | 2021-09-28 | 2021-12-17 | 北京理工大学珠海学院 | Gas turbine blade punching method and gas turbine blade punching system |
| CN113909248A (en) * | 2021-09-24 | 2022-01-11 | 华中科技大学 | Mobile three-dimensional dust removal device for multi-galvanometer SLM (Selective laser melting) forming equipment and application thereof |
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