Tool for correcting wax pattern and ceramic core of aero-engine blade

Abstract

The invention relates to the technical field of aero-engine blade manufacturing, in particular to a tool for aero-engine blade wax pattern and ceramic core correction, which comprises a driving frame and a cleaning assembly, the bottom of the inner side of the driving frame is fixedly connected with a base, and the top of the base is provided with the cleaning assembly for cleaning metal residues. A driving frame is arranged on the base, a downward pressing assembly is arranged at the upper end of the driving frame, a cutting-off table used for cutting off redundant metal on the periphery of a blade is arranged in the downward pressing assembly, and a storage chamber used for storing recycled metal is fixedly connected to the top of the base. The cutting-off table is used for cutting off the redundant part of the engine blade, and meanwhile the sweeping assembly is used for sweeping, storing and recycling redundant metal.

Description

Technical Field

[0001] The invention relates to the technical field of manufacturing aircraft engine blades, in particular to a tool for calibrating an aircraft engine blade wax mold and a ceramic core. Background Art

[0002] The tooling for correcting the wax mold and ceramic core of aero-engine blades is mainly used to accurately correct the wax mold and ceramic core of the blades to ensure that their dimensional accuracy and shape meet the design requirements. This tooling is usually composed of an upper correction block, a lower correction block, a support seat and an adjustment mechanism. The parts are closely matched to form a correction cavity that matches the shape of the blade wax mold and the ceramic core. The upper correction block and the lower correction block are the main parts of the tooling, and the correction cavity formed between them is completely consistent with the shape of the blade wax mold and the ceramic core.

[0003] The Chinese announcement number is: CN206122641U, which discloses a tool for calibrating a wax mold and a ceramic core of an aero-engine blade, comprising an upper calibrating mold block, a lower calibrating mold block, a support seat and an adjustment mechanism. A calibrating mold cavity matching the shape of the blade wax mold and / or the ceramic core is provided between the upper calibrating mold block and the lower calibrating mold block, the adjustment mechanism is slidably arranged on the support seat, the lower part of the lower calibrating mold block is in an arc shape, and the lower part extends into the interior of the adjustment mechanism, the adjustment mechanism is provided with a strip arc hole having the same curvature as the lower part, the lower calibrating mold block is provided with a circular hole 1 corresponding to the position of the strip arc hole, and when the lower calibrating mold block rotates relative to the adjustment mechanism, the motion trajectory of the circular hole 1 coincides with the strip arc hole, the tool for calibrating the patent can conveniently correct the blade wax mold and the ceramic core, and the structure has strong versatility;

[0004] Although the above patent uses the mold cavity that matches the upper mold block and the lower mold block to test the blade wax mold and the ceramic core, it does not take into account that the ceramic core is mostly a thin-walled or complex blade structure with a large difference in wall thickness. During the forming, demolding and cooling process of the ceramic core, due to the generation of stress, the wall thickness may be uneven. In this case, when it is processed and tested, under the influence of strong pressure, the thicker part of the outer wall will be squeezed out of a part of excess metal, which needs to be cleaned;

[0005] In view of this, we propose a tool for calibrating wax molds and ceramic cores of aircraft engine blades. Summary of the invention

[0006] The purpose of the present invention is to provide a tool for calibrating a wax mold and a ceramic core of an aircraft engine blade to solve the problems raised in the above-mentioned background technology.

[0007] To achieve the above-mentioned purpose, the present invention provides a tool for calibrating a wax mold and a ceramic core of an aeroengine blade, comprising a driving frame and a cleaning assembly, wherein the inner bottom of the driving frame is fixedly connected to a base, and the top of the base is provided with a cleaning assembly for cleaning metal residues, and the upper end of the driving frame is provided with a pressing assembly, and a cutting table for cutting off excess metal around the blade is provided in the pressing assembly, and the top of the base is fixedly connected to a storage room for storing recycled metal, wherein:

[0008] By moving the pressing assembly downward, the cutting table is used to cut off the redundant part of the engine blade, and the cleaning assembly is used to clean, store and reuse the redundant metal.

[0009] As a preferred embodiment of the present invention, the top of the driving frame is fixedly connected with an electric telescopic rod, the lower end of the electric telescopic rod is fixedly connected with a pressure plate, the inner side of the driving frame is slidably connected with a correction chamber, the top of the correction chamber is fixedly connected with an adjustment chamber, and the downward pressure assembly is arranged inside the adjustment chamber and the correction chamber.

[0010] As a preferred embodiment of the present invention, a storage groove is opened on the inner side of the storage chamber, the cleaning component is arranged on the inner side of the storage groove, and the base passes through the bottom of the storage chamber.

[0011] As a preferred embodiment of the present invention, the cleaning assembly includes a motor, the output end of the motor is fixedly connected to a No. 1 rotating rod, the outer wall of the No. 1 rotating rod is fixedly connected to a threaded protrusion, a sliding seat is provided on the outer side of the No. 1 rotating rod, the No. 1 rotating rod is rotatably connected to the inner side of the sliding seat, the top of the base is fixedly connected to a stabilizing seat, the middle outer wall of the stabilizing seat is fixedly connected to a semicircular gear, and the semicircular gear is meshingly connected to the threaded protrusion.

[0012] As a preferred embodiment of the present invention, the stabilizing seat is semicircular in shape, semicircular grooves are provided on both sides of the sliding seat, and the sliding seat is slidably connected to the outer wall of the stabilizing seat through the semicircular grooves on both sides.

[0013] As a preferred embodiment of the present invention, the stabilizing seat is rotatably connected to a No. 2 rotating rod at the center position of the circle, the sliding seat is fixedly connected to the No. 2 rotating rod by penetrating the outer wall of the stabilizing seat, both ends of the No. 2 rotating rod are fixedly connected to rotating connecting rods, and the rotating connecting rod is fixedly connected to a protruding block at the end away from the No. 2 rotating rod.

[0014] As a preferred embodiment of the present invention, a profiling platform is fixedly connected to the top of the stabilizing seat, the profiling platform is concave toward the top, a lower profiling block is fixedly connected to the top of the profiling platform, a slide rail is provided on the outer wall of the profiling platform, a sliding block is slidably connected to the inner side of the slide rail, the sliding block is rotatably connected to a telescopic connecting rod on the side away from the lower profiling block, the telescopic connecting rod is fixedly connected to the inner wall of the storage chamber at one end away from the sliding block, and a cleaning member is fixedly connected to the one end of the sliding block away from the telescopic connecting rod, wherein:

[0015] The outer wall of the telescopic connecting rod is provided with a strip hole, and the diameter of the protruding block matches the width of the strip hole.

[0016] As a preferred embodiment of the present invention, the down-pressing assembly includes a down-pressing column, which is slidably connected to the top of the regulating chamber and passes through the regulating chamber, and the outer wall of the lower end of the down-pressing column is fixedly connected with raised columns distributed oppositely on both sides.

[0017] As a preferred embodiment of the present invention, an upper limit platform, a lower limit platform and a second interlaced column are arranged below the lower pressure column, the upper limit platform is two semi-cylinders slidably connected to each other by a transverse column, and a No. 1 inclined surface is provided between the upper limit platforms on both sides, one side close to the other, and the outer walls of the upper limit platforms on both sides are movably connected to the limiting parts, and the bottoms of the upper limit platforms on both sides are fixedly connected to the No. 1 interlaced column, the No. 1 interlaced column passes through the lower limit platform, and the No. 1 interlaced column is provided with a spring on the outer wall of the part below the lower limit platform, wherein:

[0018] A second inclined surface is provided on the top of the lower limit platform.

[0019] As a preferred embodiment of the present invention, a No. 2 interpenetrating column is slidably connected to the center position of the lower limit platform, and an upper correction block is fixedly connected to the bottom of the No. 2 interpenetrating column. The upper correction block and the lower correction block are respectively fitted with each other on one side close to each other, and a cutting table is provided on the outer wall of the upper correction block, and the cutting table is fixedly connected to the inner side of the correction chamber.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. In the tooling for calibrating the wax mold and ceramic core of the aircraft engine blade, the electric telescopic rod is extended and drives the pressure plate to move downward. After the lower pressure plate moves down to the top of the lower pressure column and drives the lower pressure column to move downward together, the raised column at the lower end of the lower pressure column penetrates into between the upper limit platform and the lower limit platform, and drives the No. 2 insertion rod to move downward. At this time, the raised column is against the top of the lower limit platform, and drives the lower limit platform and the No. 2 insertion rod to move downward together, and the No. 2 insertion rod will push the upper correction block downward to calibrate the engine blade.

[0022] 2. In the tooling for calibrating the wax mold and ceramic core of the aircraft engine blade, during the downward movement of the lower pressure column, the upper half of the lower pressure column will push the upper limit platforms on both sides downward. At this time, the limit members of the upper limit platforms on both sides are against the bottom of the adjustment chamber and expand outward. After the upper limit platforms are blocked by the limit members and stop moving downward, the upper calibration block stops at the same time, so that the upper calibration block and the lower calibration block are squeezed to calibrate the engine blade. At this time, the cutting table cuts off the excess metal part of the blade to finally complete the calibration.

[0023] 3. In the tooling for calibrating the wax mold and ceramic core of the aircraft engine blade, the No. 1 rotating rod is driven by the motor to drive the threaded protrusion to rotate. At this time, the threaded protrusion is restricted by the semicircular gear and the sliding seat of the stabilizing table. The sliding seat will slide on the semicircular outer wall of the stabilizing table, and the sliding seat will drive the No. 2 rotating rod and the rotating connecting rod to rotate at the same angle. At this time, the raised column on the rotating connecting rod will slide in the strip hole on the telescopic connecting rod, and drive the sliding block and the cleaning piece to slide toward the inclined side, which can make the excess metal slide on the calibration table into the storage room, and can make the difficult-to-remove parts be swept into the storage room, so that the excess metal can be processed and reused later. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is an overall three-dimensional schematic diagram of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0025] Figure 2 It is an overall cross-sectional view of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0026] Figure 3 It is an overall longitudinal cross-sectional view of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0027] Figure 4 It is a three-dimensional schematic diagram of the internal distribution of the tooling for the engine blade wax mold and the ceramic core calibration of the present invention;

[0028] Figure 5 It is a three-dimensional schematic diagram of the pressing assembly of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0029] Figure 6 It is a three-dimensional schematic diagram of the downward pressing assembly of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0030] Figure 7 It is a three-dimensional schematic diagram of the cleaning assembly of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0031] Figure 8 It is a three-dimensional schematic diagram of the cleaning assembly of the tooling for adjusting the engine blade wax mold and ceramic core of the present invention;

[0032] Fig. 9 A three-dimensional schematic diagram of the details of the cleaning assembly of the tooling for calibrating the engine blade wax mold and ceramic core of the present invention;

[0033] The meaning of each number in the figure is:

[0034] 1. Driving frame; 11. Base; 12. Electric telescopic rod; 121. Pressing plate; 13. Correction room; 14. Adjustment room; 2. Storage room; 21. Storage tank;

[0035] 3. Cleaning assembly; 31. Motor; 311. Sliding seat; 32. No. 1 rotating rod; 321. Threaded protrusion; 33. Stable seat; 331. Semicircular gear; 34. No. 2 rotating rod; 341. Rotating connecting rod; 342. Protruding block; 35. Profiling table; 351. Lower profiling block; 352. Slide rail; 353. Sliding block; 354. Telescopic connecting rod; 3541. Strip hole; 36. Cleaning piece;

[0036] 4. Pressing assembly; 41. Pressing column; 411. Raised column; 42. Upper limit platform; 421. Inclined surface No. 1; 422. Limiting piece; 423. Inserted column No. 1; 424. Spring; 43. Lower limit platform; 431. Inclined surface No. 2; 44. Inserted column No. 2; 45. Upper block; 46. Cutting platform. DETAILED DESCRIPTION

[0037] The following will be combined with the accompanying drawings in the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0039] Embodiment 1

[0040] See also Figure 1-Figure 9As shown, this embodiment provides a tool for calibrating aero-engine blade wax molds and ceramic cores, including a drive frame 1 and a cleaning assembly 3. The inner bottom of the drive frame 1 is fixedly connected to a base 11, and the top of the base 11 is provided with a cleaning assembly 3 for cleaning metal residues. The upper end of the drive frame 1 is provided with a pressing assembly 4, and the pressing assembly 4 is provided with a cutting table 46 for cutting off excess metal around the blade. The top of the base 11 is fixedly connected to a storage chamber 2 for storing reused metal, wherein: by moving the pressing assembly 4 downward, the cutting table 46 is used to complete the removal of the excess part of the engine blade, and at the same time, the cleaning assembly 3 is used to complete the cleaning, storage and reuse of the excess metal.

[0041] like Figure 1-Figure 4 As shown, the top of the driving frame 1 is fixedly connected with an electric telescopic rod 12, the lower end of the electric telescopic rod 12 is fixedly connected with a pressure plate 121, the inner side of the driving frame 1 is slidably connected with a correction chamber 13, the top of the correction chamber 13 is fixedly connected with an adjustment chamber 14, the pressing assembly 4 is arranged on the inner side of the adjustment chamber 14 and the correction chamber 13, a storage groove 21 is opened on the inner side of the storage chamber 2, the cleaning assembly 3 is arranged on the inner side of the storage groove 21, and the base 11 passes through the bottom of the storage chamber 2.

[0042] like Figure 4-Figure 7 As shown, the pressing assembly 4 includes a pressing column 41, which is slidably connected to the top of the regulating chamber 14 and passes through the regulating chamber 14. The outer wall of the lower end of the pressing column 41 is fixedly connected with raised columns 411 relatively distributed on both sides. An upper limit platform 42, a lower limit platform 43 and a second interlaced column 44 are arranged below the pressing column 41. The upper limit platform 42 is two semi-cylinders slidably connected to each other through a transverse column. A No. 1 inclined surface 421 is provided between the upper limit platforms 42 on both sides, one side close to each other. The outer walls of the upper limit platforms 42 on both sides are movably connected with a limiting piece 422. The bottoms of the upper limit platforms 42 on both sides are fixedly connected with a No. 1 interlaced column 423. The No. 1 interlaced column 423 passes through the lower limit platform 43. The No. 1 insertion column 423 is provided with a spring 424 on the outer wall below the lower limit platform 43, wherein: a No. 2 inclined surface 431 is provided on the top of the lower limit platform 43, and the No. 2 insertion column 44 is slidably connected to the center position of the lower limit platform 43, and the bottom of the No. 2 insertion column 44 is fixedly connected to the upper correction block 45, and the upper correction block 45 and the lower correction block 351 respectively fit each other on one side close to each other, and a cutting table 46 is provided on the outer wall of the upper correction block 45, and the cutting table 46 is fixedly connected to the inner side of the correction chamber 13.

[0043] It can be seen from this that when the engine blades need to be corrected, Figure 1-5As shown, after the staff places the engine blade on the lower proofing block 351, the whole device is started. First, the electric telescopic rod 12 extends and drives the pressure plate 121 to move downward, and at the same time, the driving frame 1 drives the correction chamber 13 to move downward. After the lower pressure plate 121 moves down to the top of the lower pressure column 41 and drives the lower pressure column 41 to move downward together, the raised column 411 at the lower end of the lower pressure column 41 penetrates into between the upper limit platform 42 and the lower limit platform 43, and drives the No. 2 interlaced column 44 to move downward. At this time, the raised column 411 is against the top of the lower limit platform 43, and drives the lower limit platform 43 to move downward together with the No. 2 interlaced column 44, and the No. 2 interlaced column 44 will push the upper proofing block 45 downward. At this time, the upper proofing block 45 overlaps with the engine blade placed on the lower proofing block 351 to proofread the engine blade.

[0044] At the same time, in the process of the lower pressure column 41 moving downward, the upper half of the lower pressure column 41 will push the upper limit platforms 42 on both sides downward. At this time, the limit members 422 of the upper limit platforms 42 on both sides abut against the bottom of the regulating chamber 14 and expand outward until they abut against the inner wall of the regulating chamber 14. After the upper limit platform 42 is blocked by the limit members 422 and stops moving downward, the upper correction block 45 also stops squeezing the upper correction block 45 and the lower correction block 351 to correct the engine blades. After being squeezed, a part of the thicker wall thickness of the blade will be squeezed out. At this time, the driving frame 1 drives the cutting platform 46 in the correction chamber 13 to cut off the excess metal part of the blade, and finally completes the correction.

[0045] Embodiment 2

[0046] In order to realize the metal cleaning of the redundant part in the first embodiment, as Figure 7-Figure 9 As shown, the cleaning assembly 3 includes a motor 31, the output end of the motor 31 is fixedly connected to a No. 1 rotating rod 32, the outer wall of the No. 1 rotating rod 32 is fixedly connected to a threaded protrusion 321, a sliding seat 311 is arranged on the outer side of the No. 1 rotating rod 32, the No. 1 rotating rod 32 is rotatably connected to the inner side of the sliding seat 311, the top of the base 11 is fixedly connected to a stabilizing seat 33, the middle outer wall of the stabilizing seat 33 is fixedly connected to a semicircular gear 331, and the semicircular gear 331 is meshed and connected with the threaded protrusion 321 The stabilizing seat 33 is semicircular in shape, and semicircular grooves are provided on both sides of the sliding seat 311. The sliding seat 311 is slidably connected to the outer wall of the stabilizing seat 33 through the semicircular grooves on both sides. The center position of the stabilizing seat 33 is rotatably connected to the No. 2 rotating rod 34. The sliding seat 311 is fixedly connected to the No. 2 rotating rod 34 by penetrating the outer wall of the stabilizing seat 33. Both ends of the No. 2 rotating rod 34 are fixedly connected to a rotating connecting rod 341, and the rotating connecting rod 341 is fixedly connected to a protruding block 342 at the end away from the No. 2 rotating rod 34.

[0047] like Figure 8-Figure 9As shown, the top of the stabilizing seat 33 is fixedly connected with a profiling platform 35, and the profiling platform 35 is concave toward the top. The top of the profiling platform 35 is fixedly connected with a lower profiling block 351. The outer wall of the profiling platform 35 is provided with a slide rail 352, and the inner side of the slide rail 352 is slidably connected with a sliding block 353. The sliding block 353 is rotatably connected with a telescopic link 354 on the side away from the lower profiling block 351, and the telescopic link 354 is fixedly connected to the inner wall of the storage chamber 2 at one end away from the sliding block 353. The sliding block 353 is fixedly connected with a cleaning piece 36 at one end away from the telescopic link 354, wherein: the outer wall of the telescopic link 354 is provided with a strip hole 3541, and the diameter of the protruding block 342 matches the width of the strip hole 3541.

[0048] From this we can see that Figure 7-Figure 9 As shown, after the engine blades are calibrated, the driving frame 1 will drive the entire pressing assembly 4 to move up to the top. At this time, the first rotating rod 32 drives the threaded protrusion 321 to rotate under the drive of the motor 31. At this time, the threaded protrusion 321 is restricted by the semicircular gear 331, and under the restriction of the stable seat 33 on the sliding seat 311, the sliding seat 311 will slide on the semicircular outer wall of the stable seat 33. At the same time, during the sliding process of the sliding seat 311, the second rotating rod 34 will be driven to rotate, and its angle is the same as the sliding seat 311 in the stable At the same angle of the sliding position of the seat 33, the second rotating rod 34 will drive the rotating connecting rod 341 to rotate at the same angle at the same time. At this time, the protruding block 342 on the rotating connecting rod 341 will slide in the bar hole 3541 on the telescopic connecting rod 354, and drive the sliding block 353 and the cleaning member 36 to slide toward the inclined side together. On the one hand, it can make the excess metal slide on the profiling table 35 into the storage chamber 2, and on the other hand, it can make some parts that are difficult to remove after just being cut off be swept into the storage chamber 2, so that the excess metal can be processed and reused later.

[0049] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the present invention and are not intended to limit the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A tool for calibrating a wax mold and a ceramic core of an aircraft engine blade, comprising a drive frame (1) and a cleaning assembly (3), characterized in that: The bottom inner side of the driving frame (1) is fixedly connected to a base (11), the top of the base (11) is provided with a cleaning assembly (3) for cleaning metal residues, the upper end of the driving frame (1) is provided with a pressing assembly (4), the pressing assembly (4) is provided with a cutting table (46) for cutting off excess metal around the blade, and the top of the base (11) is fixedly connected to a storage chamber (2) for storing recycled metal, wherein: By moving the pressing assembly (4) downward, the cutting table (46) is used to cut off the redundant part of the engine blade, and the cleaning assembly (3) is used to clean, store and reuse the redundant metal.

2. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 1, characterized in that: The top of the driving frame (1) is fixedly connected to an electric telescopic rod (12), the lower end of the electric telescopic rod (12) is fixedly connected to a pressing plate (121), the inner side of the driving frame (1) is slidably connected to a correction chamber (13), the top of the correction chamber (13) is fixedly connected to an adjustment chamber (14), and the pressing assembly (4) is arranged inside the adjustment chamber (14) and the correction chamber (13).

3. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 1, characterized in that: A storage groove (21) is provided on the inner side of the storage chamber (2), the cleaning assembly (3) is arranged on the inner side of the storage groove (21), and the base (11) passes through the bottom of the storage chamber (2).

4. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 3, characterized in that: The cleaning assembly (3) comprises a motor (31), the output end of the motor (31) is fixedly connected to a first rotating rod (32), the outer wall of the first rotating rod (32) is fixedly connected to a threaded protrusion (321), a sliding seat (311) is arranged on the outer side of the first rotating rod (32), the first rotating rod (32) is rotatably connected to the inner side of the sliding seat (311), the top of the base (11) is fixedly connected to a stabilizing seat (33), the middle outer wall of the stabilizing seat (33) is fixedly connected to a semicircular gear (331), and the semicircular gear (331) is meshingly connected to the threaded protrusion (321).

5. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 4, characterized in that: The stabilizing seat (33) is semicircular in shape, and semicircular grooves are provided on both sides of the sliding seat (311). The sliding seat (311) is slidably connected to the outer wall of the stabilizing seat (33) via the semicircular grooves on both sides.

6. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 4, characterized in that: The center position of the stable seat (33) is rotatably connected to a second rotating rod (34); the sliding seat (311) is fixedly connected to the second rotating rod (34) by penetrating the outer wall of the stable seat (33); both ends of the second rotating rod (34) are fixedly connected to rotating connecting rods (341); and the rotating connecting rod (341) is fixedly connected to a protruding block (342) at one end away from the second rotating rod (34).

7. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 6, characterized in that: The top of the stabilizing seat (33) is fixedly connected to a profiling platform (35), the profiling platform (35) is concave toward the top, the top of the profiling platform (35) is fixedly connected to a lower profiling block (351), the outer wall of the profiling platform (35) is provided with a slide rail (352), the inner side of the slide rail (352) is slidably connected to a sliding block (353), the sliding block (353) is rotatably connected to a telescopic connecting rod (354) at a side away from the lower profiling block (351), the telescopic connecting rod (354) is fixedly connected to the inner wall of the storage chamber (2) at one end away from the sliding block (353), and the sliding block (353) is fixedly connected to a cleaning member (36) at one end away from the telescopic connecting rod (354), wherein: The outer wall of the telescopic connecting rod (354) is provided with a strip-shaped hole (3541), and the diameter of the protruding block (342) matches the width of the strip-shaped hole (3541).

8. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 7, characterized in that: The pressing assembly (4) includes a pressing column (41), the pressing column (41) is slidably connected to the top of the regulating chamber (14) and passes through the regulating chamber (14), and the outer wall of the lower end of the pressing column (41) is fixedly connected to protruding columns (411) distributed oppositely on both sides.

9. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 8, characterized in that: An upper limit platform (42), a lower limit platform (43) and a second interpenetrating column (44) are arranged below the lower pressure column (41); the upper limit platform (42) is two semi-cylinders slidably connected to each other through a transverse column; a first inclined surface (421) is provided between the upper limit platforms (42) on both sides, one side close to the other; the outer walls of the upper limit platforms (42) on both sides are movably connected to the limit members (422); the bottoms of the upper limit platforms (42) on both sides are fixedly connected to the first interpenetrating column (423); the first interpenetrating column (423) passes through the lower limit platform (43); a spring (424) is sleeved on the outer wall of the first interpenetrating column (423) located below the lower limit platform (43), wherein: A second inclined surface (431) is provided on the top of the lower limit platform (43).

10. The tooling for calibrating the wax mold and ceramic core of an aircraft engine blade according to claim 8, characterized in that: The center position of the lower limit platform (43) is slidably connected to a second insertion column (44), and the bottom of the second insertion column (44) is fixedly connected to an upper correction block (45), and the upper correction block (45) and the lower correction block (351) are respectively fitted with each other on one side close to the other, and the outer wall of the upper correction block (45) is provided with a cutting platform (46), and the cutting platform (46) is fixedly connected to the inner side of the correction chamber (13).

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