CN113926872A - Clamp for extrusion strengthening of high-strength alloy turbine disc hole structure - Google Patents
Clamp for extrusion strengthening of high-strength alloy turbine disc hole structure Download PDFInfo
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- CN113926872A CN113926872A CN202111026795.XA CN202111026795A CN113926872A CN 113926872 A CN113926872 A CN 113926872A CN 202111026795 A CN202111026795 A CN 202111026795A CN 113926872 A CN113926872 A CN 113926872A
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- hole structure
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- 238000001125 extrusion Methods 0.000 title claims abstract description 63
- 238000005728 strengthening Methods 0.000 title claims abstract description 49
- 239000000956 alloy Substances 0.000 title claims abstract description 36
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 34
- 230000007246 mechanism Effects 0.000 claims abstract description 23
- 238000003754 machining Methods 0.000 abstract description 17
- 238000012545 processing Methods 0.000 abstract description 16
- 238000000034 method Methods 0.000 description 21
- 230000008569 process Effects 0.000 description 16
- 238000005553 drilling Methods 0.000 description 14
- 238000004080 punching Methods 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 2
- 229910052721 tungsten Inorganic materials 0.000 description 2
- 239000010937 tungsten Substances 0.000 description 2
- 229910000997 High-speed steel Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000012459 cleaning agent Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000000641 cold extrusion Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
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- 230000001050 lubricating effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/02—Making uncoated products
- B21C23/04—Making uncoated products by direct extrusion
- B21C23/14—Making other products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C23/00—Extruding metal; Impact extrusion
- B21C23/21—Presses specially adapted for extruding metal
- B21C23/212—Details
-
- 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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Drilling And Boring (AREA)
Abstract
The invention relates to a clamp for extrusion strengthening of a high-strength alloy turbine disc hole structure, which comprises a base, wherein a bottom plate is arranged on the base, a disc-shaped indexing mechanism is arranged on the bottom plate, the indexing mechanism is coaxially connected with a disc-shaped clamping device, and the clamping device is used for clamping and fixing a turbine disc to be processed. According to the clamp for extruding and strengthening the hole structure of the high-strength alloy turbine disc, the turbine disc can be perfectly matched and clamped through the upper profiling clamping piece and the lower profiling clamping piece, so that the turbine disc is prevented from being worn and damaged by the clamp in the machining process; the turbine disc is driven to automatically index and rotate by 360 degrees through the indexing mechanism, so that accurate positioning can be realized; the inclination angle of the base can be adjusted through the liftable support legs, so that the processing of the inclined hole is completed.
Description
Technical Field
The invention relates to the field of aero-engine turbine disc hole extrusion strengthening, in particular to a clamp for extrusion strengthening of a high-strength alloy turbine disc hole structure.
Background
The hole-containing structure is a characteristic structure commonly used for connection and oil transportation on disc parts such as a turbine disc, an oil thrower and the like of an aircraft engine, works in complex environments such as thermal-mechanical coupling and the like, has the characteristics of high form and position precision, high reliability and long service life, and becomes one of bottlenecks restricting the research and development of the engine.
The turbine disc is used as a disc part commonly used for an aircraft engine and is subjected to high stress cyclic loads under the working conditions of starting and stopping and different rotating speeds during service, so that a low-cycle fatigue failure mode exists. Connecting holes (including straight holes and inclined holes) with different sizes are generally uniformly distributed on a turbine disc part, the hole structure is easy to generate larger stress concentration at the hole wall due to the discontinuity of geometric shapes, a crack source is easy to generate at the hole wall under the action of dynamic alternating load, the crack gradually expands along with the loading process, and when the crack expands to the critical length, the part can be damaged.
The hole extrusion strengthening process is the most widely applied technical means for prolonging the fatigue life of the connecting hole internationally at present, and is often used for strengthening the hole wall after drilling and reaming of the turbine disc. The traditional aeroengine turbine disk is usually made of high-strength alloy materials for meeting the strength requirement, and is fixed by a common clamp when drilling and reaming are carried out on the traditional aeroengine turbine disk, but the following problems are often caused: 1) the common fixture generally adopts fixed clamping to ensure that parts do not move in the drilling and reaming processes, but in the hole extrusion process, because the downward feeding force is large, the hardness of the high-strength alloy material is high, the extrusion rod is bent to a certain degree during extrusion, if the fixed clamping is adopted, the coaxiality of the hole cannot be ensured, and in the extrusion process, the extrusion rod can be broken under the action of the large feeding force; 2) the common clamp clamps parts, so that burrs are inevitably generated at the inlet and outlet of the extruded hole, if the burrs are removed, a machining procedure is added, if the burrs are not removed, the machining quality is influenced, and the fatigue life of the machined hole is influenced to a certain extent; 3) the common clamp is generally designed as a special clamp, namely, the common clamp is only suitable for clamping a single workpiece and has no universality.
Disclosure of Invention
The invention aims to provide a clamp for extrusion strengthening of a hole structure of a high-strength alloy turbine disc, so as to meet the requirement of the hole extrusion strengthening of the high-strength alloy turbine disc.
In order to achieve the purpose, the invention provides a fixture for extrusion strengthening of a high-strength alloy turbine disc hole structure, which comprises a base, wherein a bottom plate is arranged on the base, a disc-shaped indexing mechanism is arranged on the bottom plate, the indexing mechanism is coaxially connected with a disc-shaped clamping device, and the clamping device is used for clamping and fixing a turbine disc to be machined.
Furthermore, indexing mechanism includes the dabber and with the worm gear subassembly that the dabber links to each other, the worm gear subassembly cover is located in a shell.
Further, the clamping device comprises two copying clamping pieces with central shaft holes, the shaft holes are matched with the core shaft, and the two copying clamping pieces are respectively attached to the upper surface and the lower surface of the turbine disc to be processed and are compressed tightly through the end covers at the free ends of the core shaft.
Furthermore, the two copying clamping pieces are respectively provided with copying grooves matched with the upper surface and the lower surface of the turbine disc and are provided with straight holes and inclined holes which are circumferentially distributed along the central shaft hole.
Furthermore, the base is provided with a lifting support leg, a support plate is fixed on the base, and the support plate supports the bottom plate.
Furthermore, the two support plates are oppositely arranged on two opposite sides of the base.
Further, the supporting plate has a groove, and both sides of the bottom plate are respectively inserted into the groove of the supporting plate and locked by a locking screw.
Furthermore, the supporting feet are oil cylinders or crossed arm lifting platforms.
Furthermore, a driving device is arranged on the bottom plate and connected with the worm and gear assembly.
Furthermore, a supporting drill bushing is arranged on the bottom plate, one end of the supporting drill bushing is fixed on the bottom plate, and the other end of the supporting drill bushing is in contact with the lower surface of the profiling clamping piece below.
According to the clamp for extruding and strengthening the hole structure of the high-strength alloy turbine disc, the turbine disc can be perfectly matched and clamped through the upper profiling clamping piece and the lower profiling clamping piece, the turbine disc is prevented from being worn and damaged by the clamp in the machining process, and different profiling clamping pieces can be adopted according to the type of the hole structure on the turbine disc; the turbine disc is driven to automatically index and rotate by 360 degrees through the indexing mechanism, so that accurate positioning can be realized; the inclination angle of the base can be adjusted through the liftable support legs, so that the processing of the inclined hole is completed. The fixture provided by the invention can be matched with a turbine disk hole strengthening process to form a turbine disk hole drilling-reaming-detecting-extruding integrated processing device and a stable and reliable micropore strengthening process, so that a smooth surface grain refinement layer with high hardness and high surface compression stress is generated on the inner wall of a large hole of a turbine disk, and the problem of short high-temperature fatigue life of the traditional turbine disk hole drilling-reaming processing is solved.
Drawings
FIG. 1 is a schematic structural view of a high-strength alloy turbine disk according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a fixture for extrusion strengthening of a high-strength alloy turbine disk hole structure according to an embodiment of the present invention;
FIG. 3 is an exploded view of a fixture for extrusion strengthening of a high strength alloy turbine disk orifice structure according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of an indexing mechanism of the fixture for extrusion strengthening of a high-strength alloy turbine disc hole structure, provided by the embodiment of the invention;
FIG. 5 is a side view of the indexing mechanism of FIG. 4;
FIG. 6 is a cross-sectional view A-A of FIG. 5;
FIG. 7 is a front view of a fixture for extrusion strengthening of a high strength alloy turbine disk orifice structure according to an embodiment of the present invention;
FIG. 8 is an enlarged view of portion B of FIG. 7;
FIG. 9 is an enlarged view of section C of FIG. 7;
FIG. 10 is a side view of a fixture for high strength alloy turbine disk orifice structure crush reinforcement provided in accordance with an embodiment of the present invention showing the movable floor, base and support plate;
FIG. 11 is a cross-sectional view D-D of FIG. 10;
FIG. 12 is an enlarged view of section E of FIG. 11;
FIG. 13 is a process flow diagram for high strength alloy turbine disk hole strengthening provided in an embodiment of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1, a plurality of connection holes 91 are uniformly formed in the high-strength alloy turbine disk 9 along the circumferential direction, and these connection holes 91 may be of type I: straight bore, also type II: the diameter of the inclined hole and the connecting hole 91 can be set according to actual requirements.
As shown in fig. 2 and 3, an embodiment of the present invention provides a fixture for extrusion strengthening of a high-strength alloy turbine disk hole structure, including a plurality of liftable support legs 1, a base 3, a support plate 4, a movable base plate 6, an indexing mechanism, a lower profiling clamping member 8 and an upper profiling clamping member 10, where the plurality of liftable support legs 1 are uniformly arranged at the bottom end of the base 3, and the base 3 can be inclined at any angle by the cooperation of the plurality of liftable support legs 1; the supporting plates 4 are fixed on the base 3 through bolts, the movable bottom plates 6 are arranged on the supporting plates 4, for example, the two supporting plates 4 are oppositely arranged on two sides of the base 3, and the two sides of the movable bottom plates 6 are correspondingly connected with the two supporting plates 4 respectively; the upper profiling clamping piece 10 and the lower profiling clamping piece 8 are manufactured by respectively following the structures of the upper surface and the lower surface of the turbine disc 9, and are provided with profiling grooves, so that the turbine disc 9 can be clamped by the upper profiling clamping piece 10 and the lower profiling clamping piece 8 and fastened by screws after being clamped, and a sandwich structure is formed; the indexing mechanism is arranged on the movable bottom plate 6 and is connected with the sandwich structure through a shaft, so that the sandwich structure can be driven to rotate by 360 degrees, and the indexing of the turbine disc 9 is realized.
The liftable supporting leg 1 can be an oil cylinder, and is connected with the base 3 through an oil cylinder connecting piece 2, specifically, the oil cylinder is connected with the oil cylinder connecting piece 2 through a pin shaft, and the oil cylinder connecting piece 2 is connected with the base 3 through a bolt, so that the oil cylinder is fixedly connected with the base 3. The oil cylinders can be uniformly distributed on the lower surface of the base 3, and the base 3 can be inclined at any angle by adjusting the telescopic amount of each oil cylinder. The liftable supporting leg 1 may also be a cross arm lifting platform or other types of lifting structures as long as the lifting function can be realized, and the invention is not limited thereto.
As shown in fig. 4-6, the indexing mechanism includes a housing 15, worm and gear assemblies and a mandrel 19, the worm and gear assemblies are all disposed in the housing 15, and the housing 15 is used for protecting the worm and gear assemblies; the worm and gear assembly comprises a worm 14 and a worm wheel 18 which are meshed with each other, wherein the worm 14 is in transition fit connection with the shell 15 through a bearing 17, and the spindle 19 is connected with the worm wheel 18 through a flat key, so that the spindle 19 can rotate along with the worm wheel 18.
The mandrel 19 passes through the axial hole of the sandwich structure consisting of the upper copying clamping piece 10, the turbine disk 9 and the lower copying clamping piece 8, so that the sandwich structure can rotate along with the mandrel 19.
As shown in fig. 7-9, the mandrel 19 is located at the center of the sandwich structure, and the upper copying clamp 10 is provided with an end cap 16, and when the mandrel 19 passes through the sandwich structure, the end cap 16 and the mandrel 19 are tightly connected by a pin, so that the sandwich structure is connected with the mandrel 19 without being separated from the mandrel 19 from above, and thus, the sandwich structure can rotate synchronously with the mandrel 19.
The indexing mechanism may also be a ratchet mechanism, as long as the mechanism can drive the sandwich structure to rotate 360 degrees, which is not limited in the present invention.
The movable base plate 6 may also be provided with a drive means 12 connected to the worm 14 for driving the worm 14 in rotation, thereby driving the worm wheel 18 in rotation and causing the mandrel 19, the upper copying clamp 10, the turbine disc 9 and the lower copying clamp 8 to rotate in synchronism.
Preferably, the driving device 12 is a stepping motor, which is connected to the worm 14 through a belt 13, the stepping motor mainly functions to provide a torque, the belt 13 drives the worm 14 to rotate, the worm 14 drives the worm wheel 18 to rotate, the worm wheel 19 drives the spindle 19 to rotate, and the spindle 19 drives the turbine disc 9 to rotate, so as to realize indexing of the turbine disc.
Specifically, the movable bottom plate 6 may be provided with a fixing seat 11 for installing a fixed driving device 12, the fixing seat 11 is connected to the movable bottom plate 6 through a bolt, and the driving device 12 is installed on the fixing seat 11.
In a possible embodiment, the movable bottom plate 6 is further provided with a supporting drill sleeve 7, the bottom of the supporting drill sleeve is welded on the movable bottom plate 6, and the top of the supporting drill sleeve is in contact with the lower copying clamping piece 8 and is used for supporting a sandwich structure consisting of the lower copying clamping piece 8, the turbine disc 9 and the upper copying clamping piece 10, so that the supporting function can be realized when the turbine disc 9 is drilled and reamed, and the cutter is prevented from being broken due to the fact that a cantilever structure taking a central shaft as an end point is formed at the drilling and reaming positions. The supporting drill bushings 7 can be arranged in a plurality of numbers and are evenly distributed along the circumferential direction of the turbine disc 9, so that the sandwich structure is more stable.
As shown in fig. 10 to 12, the movable base 6 is connected at both ends thereof to the support plate 4, respectively, and its degree of freedom is limited by the locking screws 5. Specifically, a groove (not shown in the figure) can be formed in the support plate 4, the movable bottom plate 6 is inserted into the groove, so that the movable bottom plate 6 is connected with the support plate 4, at the moment, the movable bottom plate 6 can move slightly in the groove, namely, slightly move along the directions of x and y axes, and therefore when the hole is extruded and strengthened, the clamp can achieve self-centering, and can prevent the extrusion rod from being broken due to the reaction force of the high-strength alloy under large feeding force while ensuring the coaxiality of the hole. When drilling or reaming, the movable bottom plate 6 and the support plate 4 can be locked by the locking screw 5, so that the movable bottom plate 6 cannot move, and the processing precision of the hole is ensured.
As shown in fig. 13, the process for strengthening the multiple types of holes of the high-strength alloy turbine disc by using the fixture of the present invention comprises the following steps:
s1: mounting a turbine disc;
clamping the turbine disc 9 by the upper profiling clamping piece 10 and the lower profiling clamping piece 8 and placing the turbine disc at the installation position of the shell 15 of the indexing mechanism, connecting the end cover 16 with the core shaft 19 by using a screw, detecting end face runout and circumferential runout after installation, and carrying out fine adjustment to ensure that the error of the end face runout and the circumferential runout of the installed turbine disc is within +/-0.01 mm; the methods of end face run-out detection and circumference run-out detection are the prior art, and are not described herein again.
S2: positioning a numerical control machine;
after the turbine disk 9 is installed, positioning of the numerical control machine tool is carried out, and the relative position relation between the turbine disk 9 and the machine tool is established.
S3: positioning holes to be machined in the turbine disc;
according to the distance and the angle between the hole to be machined and the end face of the turbine disc, the lifting support leg 1 is utilized to adjust the inclination angle of the base 3, so that the inclination angle of the end face (namely the upper surface) of the turbine disc is adjusted, for example, when the hole to be machined is a straight hole, the base 3 and the end face of the turbine disc are adjusted to be horizontal, and when the hole to be machined is inclined by 10 degrees, the base 3 and the end face of the turbine disc are adjusted to be inclined by 10 degrees; the indexing mechanism is utilized to drive the turbine disc 9 to rotate, so that the position of a hole to be machined is adjusted, namely the hole to be machined is rotated to a machining position, and the machining tool is moved to the first hole machining position of the turbine disc.
S4: positioning hole punching
Because the processed turbine disk is made of high-hardness high-temperature nickel-based alloy, in order to avoid the problem that the drill bit directly drills a hole to cause a larger position error, a positioning hole needs to be drilled, and in the embodiment, the used positioning drill is a tungsten steel coating centering drill. Before punching the positioning hole, the locking screw 5 needs to be locked, so that the movable bottom plate 6 is prevented from moving to influence the punching precision during punching.
S5: drilling
In the embodiment, the drilling tool adopts a high-speed steel drill, the drilling speed is 900-1200 r/min, and the feeding speed is not more than 0.5 mm/s.
S6: reaming
In the embodiment, the reaming cutter adopts a tungsten steel reamer, the reaming speed is 500-600 r/min, and the feeding speed is not more than 1 mm/s.
S7: bore diameter detection
In order to ensure the extrusion uniformity, the inner diameter of the hole after reaming on the turbine disc is detected by a plug gauge, and an extrusion tool with the best extrusion amount is selected according to the detected inner diameter.
S8: hole extrusion reinforcement
The extrusion strengthening tool adopts a multi-micro-bump bushing rotary extrusion strengthening tool, the extrusion rate range is 2.4% -5%, and before extrusion, the locking screw 5 needs to be unscrewed so that the movable bottom plate 6 can slightly move on the x axis and the y axis to realize self-centering of the clamp; in the extrusion process, the rotating speed of a main shaft is 66-132 r/min, the feeding speed of the strengthening tool is not more than 0.2mm/s, the strengthening tool needs to be completely withdrawn from a hole every time the strengthening tool is fed for 1mm, a high-pressure cleaning agent is sprayed out from a cleaning nozzle to remove impurity particles on the surface of the strengthening tool before the strengthening tool enters the small deep hole again, a cold extrusion lubricant is sprayed out from a lubricating nozzle, and finally, the extrusion is carried out again until the extrusion strengthening of all the holes is completed.
S9: deburring and polishing
Because the upper profiling clamping piece 10 and the lower profiling clamping piece 8 are profiling structures of the turbine disc 9, holes with the same diameter as holes to be machined on the turbine disc are formed in the upper profiling clamping piece, burrs can fall off in the machining process, generated burrs are few, and after extrusion strengthening of all the holes on the turbine disc is completed, the flexible ball head grinding head is adopted to simply grind and polish the hole opening.
The following will specifically describe the method for extruding and strengthening the hole structure of the turbine disk according to the present invention by taking the processing of straight holes and inclined holes as examples.
Firstly, straight hole processing:
the user can adjust the processing station number according to the equipment condition, and in the embodiment, four processing stations are arranged, so that four holes can be simultaneously processed. Because the straight hole is processed, the lifting support leg 1 does not need to be adjusted. Firstly, clamping a turbine disc 9, firstly installing the turbine disc 9 into an upper profiling clamping piece 10 and a lower profiling clamping piece 8, connecting the upper profiling clamping piece 10 and the lower profiling clamping piece 8 through screws, and locking the turbine disc 9 to form a sandwich structure; then, mounting the sandwich structure on a designated area of the mandrel 19, and connecting the end cover 16 and the mandrel 19 through screws so that the sandwich structure can rotate along with the mandrel 19; and after the turbine disc 9 is clamped, hole positioning, drilling and reaming are carried out, wherein the rotating speed of a drilling bit is 1200r/min, the feeding speed is 0.15mm/s, the rotating speed of a reaming reamer is 660r/min, and the feeding speed is 0.15 mm/s. Use the plug gauge to measure the aperture, the extrusion hole extrusion that the selective extrusion rate is 2% strengthens the instrument and extrudees the hole behind the reamed hole, release locking screw 5 before the extrusion, make portable bottom plate 6 portable when the extrusion, realize the self-centering of extrusion strengthening hole in-process device, can prevent again that the extrusion stick from appearing the fracture under great feed force when guaranteeing the hole axiality, and portable bottom plate 6 bottom is equipped with bearing structure, can prevent effectively that portable bottom plate 6 from crooked under the condition of great feed force, influence the machining precision. The rotating speed of the extrusion strengthening tool of the extrusion hole is 80r/min, the feeding speed is 0.15mm/s, and meanwhile, the sufficient lubrication in the extrusion process is ensured. After the extrusion is finished, the locking screw 5 is locked (to the initial position), the movable bottom plate 6 is fixed, the driving device 12 of the indexing mechanism is started, the rotation is carried out for 22.5 degrees, and the processing technology is repeated. And 4 times of circulation, the turbine disc completes machining, and compared with single-station machining, the time is saved by four times.
After the machining is finished, the form and position tolerance of the upper hole of the extruded and reinforced part is verified by using a plug gauge and a dial indicator, and the obtained result is good, so that the clamp suitable for extruding and reinforcing the high-strength alloy turbine disc hole structure meets the straight hole machining requirement of integrating drilling, reaming and extruding.
Secondly, processing inclined holes:
before the turbine disc 9 is clamped, the liftable support legs 1 are adjusted, and the plurality of liftable support legs 1 are matched to realize that the base 3 is inclined by a specified angle so as to meet the processing requirement; then clamping a turbine disk 9, firstly installing the turbine disk 9 into an upper copying clamping piece 10 and a lower copying clamping piece 8, and connecting the upper copying clamping piece 10 and the lower copying clamping piece 8 through screws to lock the turbine disk 9; secondly, the upper copying clamping piece 10 and the lower copying clamping piece 8 are arranged in a designated area on a mandrel 19, and an end cover 16 and the mandrel 19 are connected through screws, so that the upper copying clamping piece 10 and the lower copying clamping piece 8 with the turbine disc 9 can rotate along with the mandrel 19; and after the turbine disc 9 is clamped, hole positioning, drilling and reaming are carried out, wherein the rotating speed of a drilling bit is 1200r/min, the feeding speed is 0.15mm/s, the rotating speed of a reaming reamer is 660r/min, and the feeding speed is 0.15 mm/s. The method comprises the steps of measuring the aperture by using a plug gauge, selecting an extrusion hole extrusion strengthening tool with the extrusion rate of 2% to extrude a reamed hole, releasing a locking screw before extrusion, enabling a movable bottom plate 6 to be movable during extrusion, realizing self-centering of the device in the process of extruding and strengthening the hole, ensuring the coaxiality of the hole and preventing an extrusion rod from being broken under a large feeding force; the rotating speed of the extrusion strengthening tool of the extrusion hole is 80r/min, the feeding speed is 0.15mm/s, and simultaneously, the sufficient lubrication in the extrusion process is ensured; after the extrusion is finished, the locking screw 5 is locked (to the initial position), the movable bottom plate 6 is fixed, the driving device 12 of the indexing mechanism is started, the rotation is carried out for 22.5 degrees, and the processing technology is repeated. And (5) circulating for 20 times, and finishing the machining of the oblique hole of the turbine disc.
After the machining is finished, the form and position tolerance of the upper hole of the extruded and reinforced part is verified by using a plug gauge and a dial indicator, and the obtained result is good, so that the clamp suitable for extruding and reinforcing the high-strength alloy turbine disc hole structure meets the requirements of drilling, reaming and extruding integrated oblique hole machining.
According to the clamp for extruding and strengthening the hole structure of the high-strength alloy turbine disc, the turbine disc can be perfectly matched and clamped through the upper profiling clamping piece and the lower profiling clamping piece, the turbine disc is prevented from being worn and damaged by the clamp in the machining process, and different profiling clamping pieces can be adopted according to the type of the hole structure on the turbine disc; the turbine disc is driven to automatically index and rotate by 360 degrees through the indexing mechanism, so that accurate positioning can be realized; the inclination angle of the base 3 can be adjusted through the liftable supporting legs 1, so that the processing of the inclined hole is completed. The fixture is matched with a turbine disc hole strengthening process to form a turbine disc hole drilling-reaming-detecting-extruding integrated processing device and a stable and reliable micropore strengthening process, and the fixture and the process can enable the inner wall of a large hole of a turbine disc to generate a smooth surface grain refinement layer with high hardness and high surface compression stress, so that the problem of short high-temperature fatigue life of the traditional turbine disc hole drilling-reaming processing is solved.
The above embodiments are merely preferred embodiments of the present invention, which are not intended to limit the scope of the present invention, and various changes may be made in the above embodiments of the present invention. All simple and equivalent changes and modifications made according to the claims and the content of the specification of the present application fall within the scope of the claims of the present patent application. The invention has not been described in detail in order to avoid obscuring the invention.
Claims (10)
1. The fixture for the extrusion strengthening of the high-strength alloy turbine disc hole structure is characterized by comprising a base, wherein a bottom plate is arranged on the base, a disc-shaped indexing mechanism is arranged on the bottom plate, the indexing mechanism is coaxially connected with a disc-shaped clamping device, and the clamping device is used for clamping and fixing a turbine disc to be machined.
2. The fixture for high-strength alloy turbine disc hole structure extrusion strengthening of claim 1, wherein the indexing mechanism comprises a mandrel and a worm and gear assembly connected with the mandrel, and the worm and gear assembly is sleeved in a shell.
3. The clamp for the extrusion strengthening of the hole structure of the high-strength alloy turbine disc as claimed in claim 2, wherein the clamping device comprises two copying clamping pieces with central shaft holes, the shaft holes are matched with the mandrel, and the two copying clamping pieces respectively fit the upper surface and the lower surface of the turbine disc to be processed and are pressed tightly through end covers at the free ends of the mandrel.
4. The clamp for the extrusion strengthening of the hole structure of the high-strength alloy turbine disc as claimed in claim 3, wherein the two copying clamping pieces are respectively provided with copying grooves matched with the upper surface and the lower surface of the turbine disc and are provided with straight holes and inclined holes which are circumferentially arranged along the central shaft hole.
5. The clamp for the extrusion strengthening of the hole structure of the high-strength alloy turbine disc as claimed in claim 1, wherein the base is provided with a lifting leg, a support plate is fixed on the base, and the support plate supports the bottom plate.
6. The clamp for the extrusion strengthening of the hole structure of the high-strength alloy turbine disc as claimed in claim 5, wherein the two support plates are oppositely arranged on two opposite sides of the base.
7. The clamp for high-strength alloy turbine disc hole structure extrusion strengthening of claim 6, wherein the supporting plate has a groove, and both sides of the bottom plate are respectively inserted into the groove of the supporting plate and locked by locking screws.
8. The clamp for high-strength alloy turbine disc hole structure extrusion strengthening of claim 5, wherein the support leg is a cylinder or a cross arm lifting platform.
9. The clamp for the extrusion strengthening of the hole structure of the high-strength alloy turbine disc as claimed in claim 2, wherein a driving device is arranged on the bottom plate, and the driving device is connected with the worm and gear assembly.
10. The clamp for high-strength alloy turbine disc hole structure extrusion strengthening of claim 1, wherein a support drill bushing is arranged on the bottom plate, one end of the support drill bushing is fixed on the bottom plate, and the other end of the support drill bushing is in contact with the lower surface of the profiling clamping piece below.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111026795.XA CN113926872A (en) | 2021-09-02 | 2021-09-02 | Clamp for extrusion strengthening of high-strength alloy turbine disc hole structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111026795.XA CN113926872A (en) | 2021-09-02 | 2021-09-02 | Clamp for extrusion strengthening of high-strength alloy turbine disc hole structure |
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