CN116728089A - Laser cutting-broaching combined machining method and device for turbine disc mortises - Google Patents
Laser cutting-broaching combined machining method and device for turbine disc mortises Download PDFInfo
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- CN116728089A CN116728089A CN202310964427.2A CN202310964427A CN116728089A CN 116728089 A CN116728089 A CN 116728089A CN 202310964427 A CN202310964427 A CN 202310964427A CN 116728089 A CN116728089 A CN 116728089A
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- turbine disc
- broaching
- laser cutting
- disc blank
- laser
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- 238000003754 machining Methods 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000003698 laser cutting Methods 0.000 claims abstract description 40
- 238000001816 cooling Methods 0.000 claims abstract description 23
- 238000005520 cutting process Methods 0.000 claims abstract description 19
- 238000001931 thermography Methods 0.000 claims abstract description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 16
- 239000002131 composite material Substances 0.000 claims description 15
- 238000006073 displacement reaction Methods 0.000 claims description 11
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- 239000007788 liquid Substances 0.000 claims description 8
- 229910052757 nitrogen Inorganic materials 0.000 claims description 8
- 229910000601 superalloy Inorganic materials 0.000 claims description 5
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 150000001875 compounds Chemical class 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 238000003672 processing method Methods 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 239000002184 metal Substances 0.000 abstract description 6
- 229910052751 metal Inorganic materials 0.000 abstract description 6
- 239000013078 crystal Substances 0.000 description 8
- 230000008602 contraction Effects 0.000 description 5
- 239000007921 spray Substances 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000003746 surface roughness Effects 0.000 description 2
- 230000003685 thermal hair damage Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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
- B23K26/0093—Working by laser beam, e.g. welding, cutting or boring combined with mechanical machining or metal-working covered by other subclasses than B23K
Abstract
The invention discloses a turbine disk mortise laser cutting-broaching combined machining method and device, comprising a frame, a workbench, a laser cutting module, a broaching machining module, a thermal imaging instrument and a cooling device, wherein the workbench, the laser cutting module, the broaching machining module, the thermal imaging instrument and the cooling device are arranged on the frame; the workbench is used for fixing the turbine disc blank and driving the turbine disc blank to rotate around the axis; the laser cutting module is used for carrying out preliminary processing cutting on the turbine disc blanks; the broaching processing module is used for further cutting the turbine disc blank processed by the laser cutting module; the thermal imager is used for collecting the temperature of the turbine disc blank; the cooling device is used for cooling the turbine disc blank subjected to laser cutting. According to the characteristics of metal adopted by the turbine disc blank, the surface temperature of the turbine disc to be processed is reduced to a specified temperature; the turbine disc blank is in a softened state, and the broaching tool performs broaching on the turbine disc blank in the state, so that the problem that the broaching tool is worn too quickly due to too high metal hardness is avoided.
Description
Technical Field
The invention belongs to the technical field of turbine disc machining and manufacturing, and particularly relates to a turbine disc mortise laser cutting-broaching composite machining method and device.
Background
The turbine disk is an important part of the aero-engine, and is connected with the turbine blades through mortise and tenon joints to form a turbine rotor, the working environment is extremely severe, the turbine rotor is subjected to the impact of high-temperature high-pressure fuel gas, centrifugal force, cold-hot alternation, stress circulation, vibration fatigue and the like of the blades and the turbine disk, and the turbine disk of the hot end part of the aero-engine has high processing requirement quality, high reliability and good fatigue resistance. The turbine disk mainly comprises a disk body and tens of fir-type mortises uniformly distributed on the periphery of the disk rim, wherein the mortises have complex structures and high requirements on form and position tolerances, and bring great challenges to processing and manufacturing.
The processing technology of the turbine disk mortise structure is complex, and the processing requirements of the turbine disk mortise structure can be met by corresponding rough and finish machining after preliminary slotting is finished. The conventional machining methods, such as milling, broaching, grinding and the like, all have the problems of complex cutter shape, small cutter rigidity, easy loss and the like; when wire-cut electric discharge machining is adopted, the machining efficiency is low, and a recast layer, a heat affected zone and the like are easy to generate on the surface of a workpiece; and after the heat affected zone is further processed, the volume of the turbine disc is reduced due to expansion and contraction of metal, and internal stress is generated by the metal, so that the surface of the alloy is provided with slits and cracks.
Disclosure of Invention
The invention aims to provide a turbine disc mortise laser cutting-broaching combined machining method and device.
In a first aspect, the invention provides a machining method of a turbine disc mortise laser cutting-broaching composite machining device. The method comprises the following specific steps:
step one, fixing a turbine disc blank; carrying out laser processing on the surface of the turbine disc blank so as to generate a plurality of mortises uniformly distributed along the circumferential direction of the axis of the turbine disc blank on the turbine disc blank;
step two, cooling the outer side end part of the turbine disc blank to enable the temperature of the inner side surface of each mortise on the turbine disc blank to be reduced to 1080-1100 ℃;
and thirdly, carrying out broaching processing on the inner side surface of each mortise on the turbine disc blank, wherein the cutting depth is 0.5-1 mm, and obtaining the processed turbine disc.
Preferably, in the first step, YAG laser is used for laser cutting, the wavelength is 1060nm, the pulse width is 10, the laser power is 30W, and the laser radius is 0.1mm.
Preferably, in the second step, the temperature of the inner side surface of each tongue-and-groove on the turbine disc blank is synchronously reduced by spraying liquid nitrogen to the outer side end part of the turbine disc blank to cool and rotating the turbine disc blank around the axis.
Preferably, the turbine disc blank is made of nickel-based superalloy.
Preferably, in the first step, the distance between the laser head for laser processing and the turbine disc blank is 10cm.
Preferably, the temperature of the mortise is adjusted to 1080 ℃ in the second step.
In a second aspect, the present invention provides a combined laser cutting and broaching apparatus for use in performing a combined laser cutting and broaching method for a turbine disc dovetail as described in the first aspect; the composite processing device comprises a frame, a workbench, a laser cutting module, a broaching processing module, a thermal imaging instrument and a cooling device, wherein the workbench, the laser cutting module, the broaching processing module, the thermal imaging instrument and the cooling device are arranged on the frame; the workbench is used for fixing the turbine disc blank and driving the turbine disc blank to rotate around the axis; the laser cutting module is used for carrying out preliminary processing cutting on the turbine disc blanks; the broaching processing module is used for further cutting the turbine disc blank processed by the laser cutting module; the thermal imager is used for collecting the temperature of the turbine disc blank; the cooling device is used for cooling the turbine disc blank subjected to laser cutting.
Preferably, the laser cutting module comprises a displacement driving mechanism and a laser emitter arranged on the displacement driving mechanism; the displacement driving mechanism is used for driving the laser emitter to move.
Preferably, the workbench comprises a processing base, a motor and a turntable; the processing base is fixed on the frame; the turntable and the processing base form a revolute pair; the motor is installed in the processing base, and the output shaft of motor is fixed with the revolving stage.
Preferably, the broaching module comprises a driving element and a broaching tool, wherein the driving element is used for driving the broaching tool to reciprocate along the axial direction of the turbine disc blank.
The invention has the beneficial effects that:
1. the invention adopts a composite processing mode of laser cutting and broaching cutting; after laser cutting processing, cooling the surface of the turbine disc blank, and cooling the turbine disc blank 3 to approximately 1080 ℃; when the temperature of the turbine disk blank 3 is in the range of 980-1080 ℃, the crystal phase of the turbine disk blank exhibits a Body Centered Cubic (BCC); when the temperature of the turbine disk blank 3 is more than 1080 ℃, the crystal phase of the turbine disk blank exhibits a face-centered cubic phase (FCC); BCC structures generally have higher hardness and strength than FCC structures. Therefore, when the crystal phase of the turbine disc blank 3 presents a BCC structure, the difficulty of cutting is greatly increased, resulting in increased loss of the tool and reduced machining precision.
2. In the invention, the turbine disc blank 3 after laser cutting is subjected to cooling treatment, and broaching treatment is carried out after the turbine disc blank is cooled to 1080 ℃; the dimensional change caused by expansion and contraction after cooling the turbine disc blank 3 can cause surface quality problems such as increased dimensional deviation, increased surface roughness, surface cracks, thermal damage and the like of the turbine disc after processing.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of the position of a laser transmitter relative to a turbine disk blank in accordance with the present invention;
FIG. 3 is a schematic view of a dovetail groove formed in a turbine disk blank according to the present invention;
FIG. 4 is a schematic diagram of a laser transmitter of the present invention transmitting laser of different power and radius on a turbine disk blank;
fig. 5 is a schematic view of the machining position of the broach tool according to the present invention.
1, processing a base; 2. a turntable; 3. turbine disk blanks; 4. a laser emitter; 5. a tongue and groove; 6. broaching tools.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in FIG. 1, the device and the method for the combined machining of the turbine disc mortises by laser cutting and broaching comprise a machine frame, a workbench, a laser cutting module, a broaching module, a thermal imager and a cooling device, wherein the workbench, the laser cutting module, the broaching module, the thermal imager and the cooling device are arranged on the machine frame. The laser cutting module is used for performing preliminary processing cutting on the turbine disc blank 3. The broaching processing module is used for further cutting the turbine disc blank 3 processed by the laser cutting module. The workbench comprises a processing base 1, a motor and a rotary table 2. The processing base 1 is fixed on the frame. The turntable 2 and the processing base 1 form a revolute pair. The motor is installed in processing base 1, and the output shaft of motor is fixed with revolving stage 2. During processing, the turbine disc blank 3 is placed on the turntable 2, and the position of the turbine disc blank is fixed through the turntable 2.
As shown in fig. 2 and 3, the laser cutting module includes a displacement driving mechanism, and a laser transmitter 4 mounted on the displacement driving mechanism. The displacement driving mechanism is used for driving the laser emitter 4 to move in the vertical direction and any direction in the same plane. During processing, the distance between the laser head of the laser transmitter 4 and the turbine disc blank 3 is 10cm, and the displacement driving mechanism drives the laser transmitter 4 to cut at the speed of 100 cm/min. During machining, presetting a tooth top contour line required to be machined and generated on the surface of a turbine disc blank, and setting a machining path of laser cutting; the distance between the machining path of the laser cutting and the tooth crest contour line is 0.1mm. After laser cutting, a plurality of mortises 5 uniformly distributed along the circumferential direction of the axis are formed on the turbine disc blank 3. The laser cutting module is used for carrying out rough machining treatment on the turbine disc blank 3, so that the cutting amount required in broaching is reduced, and the abrasion to a cutter in the broaching module is reduced.
The detection surface of the thermal imager is opposite to the outer cutting edge of the turbine disc blank 3, and the thermal imager is used for detecting and displaying the temperature of the surface of the turbine disc blank 3 in real time. The cooling device comprises an air supply pipe and a liquid nitrogen spray head communicated with the air supply pipe. The injection surface of the liquid nitrogen spray head is opposite to the outer side edge of the turbine disc blank 3. By spraying liquid nitrogen onto the surface of the turbine disc blank 3, the temperature of the turbine disc blank 3 raised due to laser cutting is quickly lowered to a preset temperature. The preset temperature was 1080 ℃.
As shown in fig. 5, the broaching module includes a driving element and a broaching tool 6, where the driving element is used to drive the broaching tool 6 to reciprocate along the axial direction of the turbine disc blank 3, so as to complete the cutting of the reserved allowance of the turbine disc blank 3. After the turbine disc blank 3 is cooled, the broaching module performs broaching along the edge of the turbine disc mortise 5, and the broaching module cuts out the depth distance l in the radial direction of the turbine disc blank 3. The broaching processing module is used for further cutting the cooled turbine disc blank 3, so that heat energy generated during laser cutting is avoided, and heat expansion and cold contraction of metal are avoided, so that the processing precision of the turbine disc blank 3 is affected.
The metal adopted by the turbine disc blank 3 is nickel-based superalloy, and the concrete mark is 718; after laser cutting, the surface of the mortise formed on the turbine disc blank 3 is at a high temperature close to the melting point, so that the mortise is difficult to quickly cool to room temperature; the blank temperature of the turbine disc blank 3 has a great influence on the machining precision during broaching; the method comprises the following steps:
on the one hand, when broaching is performed at an excessively high temperature, dimensional changes caused by expansion with heat and contraction with cold after cooling the turbine disc blank 3 can cause surface quality problems such as increased dimensional deviation, increased surface roughness, surface cracks, thermal damage and the like of the turbine disc after processing.
On the other hand, the turbine disc blank 3 has different crystalline phases in different temperature ranges, and the processing difficulty of the different crystalline phases is different; when the temperature of the turbine disk blank 3 is in the range of 980-1080 ℃, the crystal phase of the turbine disk blank exhibits a Body Centered Cubic (BCC); when the temperature of the turbine disk blank 3 is more than 1080 ℃, the crystal phase of the turbine disk blank exhibits a face-centered cubic phase (FCC); BCC structures generally have higher hardness and strength than FCC structures. Therefore, when the crystal phase of the turbine disc blank 3 presents a BCC structure, the difficulty of cutting is greatly increased, resulting in increased loss of the tool and reduced machining precision.
Therefore, the turbine disc blank 3 is cooled to be close to 1080 ℃ after laser cutting, the influence of expansion with heat and contraction with cold can be reduced as much as possible, the crystal phase of the broached turbine disc blank 3 is ensured to present a face-centered cubic phase (FCC), the service life of a cutter is effectively prolonged, and the machining precision of the turbine disc is improved. Therefore, in the embodiment, liquid nitrogen is used for cooling the turbine disc blank 3 subjected to laser cutting to a temperature of 1080-1100 ℃ (preferably 1080 ℃), so as to achieve the optimal processing effect.
YAG laser (infrared laser) is selected, the wavelength is 1060nm, the pulse width is 10, the laser power is 30w, and the laser radius is 0.1mm; the laser power is 40w, and the laser radius is 0.1mm; the laser power is 30W, and the laser radius is 0.2mm; the laser power is 40w, and the laser radius is four groups of lasers with different powers of 0.2 mm. A laser cutting simulation was performed on the turbine disc blank 3. According to the properties of the nickel-base superalloy 718 alloy. A cut turbine disk is defined. The cut turbine disk had a conductivity of 10.1W/(mK) and a density of about 8.2g/cm at room temperature 3 The specific heat capacity was about 427J/(kg.K) at room temperature, and the Young's modulus was about 204GPa. The thermal expansion coefficient is 13.3X10-6/K in the range of room temperature to 650 ℃. A heat transfer (transient) analysis step was created with a time length set to 1s and an incremental step size of 0.01. The ambient temperature was set to 20 ℃. The heat flux load q applied to the surface of the turbine disk being cut is calculated according to equation 1:
where P represents the laser power, R is the laser radius, R is the radial distance between any point in the turbine disc and the laser center position, and a is the laser energy absorption (a=0.7).
The results are shown in FIG. 4, wherein the laser powers of (a), (b), (c) and (d) are 30W, and the laser radius is 0.1mm; the laser power is 40W, and the laser radius is 0.1mm; the laser power is 30W, and the laser radius is 0.2mm; the laser power is 40w, and the laser radius is 0.2mm respectively. In fig. 4, lighter color indicates higher processing temperature. As can be seen from the images (a), (b), (c) and (d) in fig. 4, the temperature of the laser center is 1328 ℃ when the laser power is 30W and the laser radius is 0.1mm, and the closest temperature to the nickel-based superalloy crystal phase is face-centered cubic (FCC): 1080-1100 ℃.
The method for processing the turbine disc by using the turbine disc mortise laser cutting-broaching composite processing device comprises the following steps:
step one, mounting a turbine disc blank 3 on a turntable 2.
Step two, presetting an outline of a tooth top on the surface of a turbine disc blank 3, and setting a processing path of a laser transmitter 4; the distance between the tooth top contour line and the machining path is 1mm.
And thirdly, driving the laser emission to move along the machining edge of the turbine disc blank 3 by the displacement driving mechanism. The laser transmitter 4 emits laser, and the surface of the turbine disc blank 3 is cut by the laser at the cutting speed of 280cm/min to generate the mortise 5.
Step four, the motor drives the turbine disc blank 3 fixed on the turntable 2 to rotate; meanwhile, the liquid nitrogen nozzle sprays liquid nitrogen to the turbine disc blank 3, so that the surface temperature of the turbine disc blank 3 is uniformly cooled to 1080 ℃.
Step five, driving the broaching tool 6 to reciprocate at a speed of 1m/min by the driving element, and broaching the inner side surface of the mortise by the broaching tool 6; and cut to a depth of 0.5mm to 1mm. Simultaneously, the motor drives the turbine disc blank 3 to rotate, and broaching and cutting of reserved allowance on the turbine disc blank 3 are completed, so that the machined turbine disc is obtained.
Claims (10)
1. A turbine disk mortise laser cutting-broaching composite processing method; the method is characterized in that: the method comprises the following steps:
step one, fixing a turbine disc blank (3); carrying out laser processing on the surface of the turbine disc blank (3) to generate a plurality of mortises (5) on the turbine disc blank (3) which are uniformly distributed along the circumferential direction of the axis of the turbine disc blank (3);
step two, cooling the outer side end part of the turbine disc blank (3) to enable the temperature of the inner side surface of each mortise (5) on the turbine disc blank (3) to be reduced to 1080-1100 ℃;
and thirdly, carrying out broaching processing on the inner side surface of each mortise (5) on the turbine disc blank (3) to obtain the processed turbine disc, wherein the cutting depth is 0.5-1 mm.
2. The turbine disc dovetail slot laser cutting-broaching composite machining method of claim 1, wherein: in the first step, YAG laser is selected for laser cutting, the wavelength is 1060nm, the pulse width is 10, the laser power is 30W, and the laser radius is 0.1mm.
3. The turbine disc dovetail slot laser cutting-broaching composite machining method of claim 1, wherein: in the second step, liquid nitrogen is injected to the outer side end part of the turbine disc blank (3) to cool, and the turbine disc blank (3) rotates around the axis, so that the temperature of the inner side surface of each mortise (5) on the turbine disc blank (3) is synchronously lowered.
4. The turbine disc dovetail slot laser cutting-broaching composite machining method of claim 1, wherein: the material adopted by the turbine disc blank (3) is nickel-based superalloy.
5. The turbine disc dovetail slot laser cutting-broaching composite machining method of claim 1, wherein: in the first step, the distance between a laser head for laser processing and the turbine disc blank (3) is 10cm.
6. The turbine disc dovetail slot laser cutting-broaching composite machining method of claim 1, wherein: and in the second step, the temperature of the mortise (5) is regulated to 1080 ℃.
7. The utility model provides a turbine dish tongue-and-groove laser cutting-broaching combined machining device which characterized in that: a method for performing a turbine disk dovetail slot laser cutting-broaching compound machining method of claim 1; the composite processing device comprises a frame, a workbench, a laser cutting module, a broaching processing module, a thermal imaging instrument and a cooling device, wherein the workbench, the laser cutting module, the broaching processing module, the thermal imaging instrument and the cooling device are arranged on the frame; the workbench is used for fixing the turbine disc blank (3) and driving the turbine disc blank (3) to rotate around the axis; the laser cutting module is used for carrying out preliminary processing cutting on the turbine disc blank (3); the broaching processing module is used for further cutting the turbine disc blank (3) processed by the laser cutting module; the thermal imager is used for collecting the temperature of the turbine disc blank (3); the cooling device is used for cooling the turbine disc blank (3) subjected to laser cutting.
8. The turbine disc mortise laser cutting-broaching composite machining device according to claim 7, characterized in that: the laser cutting module comprises a displacement driving mechanism and a laser emitter (4) arranged on the displacement driving mechanism; the displacement driving mechanism is used for driving the laser emitter (4) to move.
9. The turbine disc mortise laser cutting-broaching composite machining device according to claim 7, characterized in that: the workbench comprises a processing base (1), a motor and a rotary table (2); the processing base (1) is fixed on the frame; the turntable (2) and the processing base (1) form a revolute pair; the motor is arranged in the processing base (1), and an output shaft of the motor is fixed with the turntable (2).
10. The turbine disc mortise laser cutting-broaching composite machining device according to claim 7, characterized in that: the broaching module comprises a driving element and a broaching tool (6), wherein the driving element is used for driving the broaching tool (6) to reciprocate along the axial direction of the turbine disc blank (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310964427.2A CN116728089A (en) | 2023-08-02 | 2023-08-02 | Laser cutting-broaching combined machining method and device for turbine disc mortises |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310964427.2A CN116728089A (en) | 2023-08-02 | 2023-08-02 | Laser cutting-broaching combined machining method and device for turbine disc mortises |
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| Publication Number | Publication Date |
|---|---|
| CN116728089A true CN116728089A (en) | 2023-09-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310964427.2A Pending CN116728089A (en) | 2023-08-02 | 2023-08-02 | Laser cutting-broaching combined machining method and device for turbine disc mortises |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116728089A (en) |
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2023
- 2023-08-02 CN CN202310964427.2A patent/CN116728089A/en active Pending
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