Clamping tool for machining air compressor disc of aero-engine

By designing a clamping tool for aircraft engine compressor discs, the problems of high processing difficulty and limited performance improvement in traditional processing methods are solved, and stable clamping and finishing of multi-stage compressor discs are achieved, which improves the overall performance of the engine.

CN222754615UActive Publication Date: 2025-04-15CHANGCHUN CNC MACHINE TOOL
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Patent Information

Application Number
CN202421506299.3
Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
Filing Date
2024-06-28
Publication Date
2025-04-15
Estimated Expiration
2034-06-28

AI Technical Summary

Technical Problem

The processing of aircraft engine compressor plates is difficult, and traditional mechanical bolt connection and electron beam welding methods have problems such as increased weight, high residual stress and difficult welding of different materials, which restricts the improvement of engine performance.

Method used

A clamping tool for processing compressor discs for aircraft engines is designed, including a clamping frame housing, a first clamping mechanism, a tool positioning disk, a fixed support disk, a second clamping mechanism, a clamping drive mechanism, a floating support seat and a clamping spring coil. The stable clamping of the compressor discs at all levels is achieved through the clamping drive mechanism and the clamping spring coil, which facilitates finishing.

Benefits of technology

The clamping tool can effectively clamp multi-stage compressor discs of different thicknesses, simplifying the processing process, reducing processing difficulty, improving processing accuracy and efficiency, and thus improving the thrust-to-weight ratio and performance of the aircraft engine.

✦ Generated by Eureka AI based on patent content.

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Abstract

The utility model discloses a clamping tool for machining an aero-engine compressor disc. The clamping tool comprises a clamping frame shell, a first clamping jaw mechanism, a tool positioning disc, a fixed supporting disc, a second clamping jaw mechanism, a clamping driving mechanism, a floating supporting seat and a clamping spring ring. The first clamping jaw mechanism, the tool positioning disc, the fixed supporting disc, the second clamping jaw mechanism, the clamping driving mechanism, the floating supporting base and the clamping spring ring are arranged in the clamping frame shell. The clamping driving mechanism supports the inner end face of a tailstock of the gas compressor disc through a floating supporting seat. The clamping driving mechanism is provided with a locking nut; the locking nut rotates to drive the second clamping jaw mechanism to retract into or stretch out of the clamping frame shell, so that the second clamping jaw mechanism can clamp the outer end face of each stage of compressor disc of the compressor disc of the engine through the clamping spring ring. Friction welding, electroplating and other finish machining can be conveniently carried out on the multi-stage compressor discs with different thicknesses.
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Description

Technical Field

[0001] The utility model belongs to the technical field, and in particular relates to a clamping tool for machining an aero-engine compressor disc. Background Art

[0002] As an important component of an aircraft engine, the compressor is a mechanical device that transmits mechanical energy to the gas, completes the gas medium compression process in the engine's thermodynamic cycle, and increases the gas pressure. The compressor is mainly composed of a low-pressure compressor and a high-pressure compressor. As an important component of the compressor, the compressor disc is made of titanium alloy, high-temperature alloy, and powder high-temperature alloy from the first to the tenth stage. The traditional connection between the discs at each stage is mechanical bolt connection and electron beam welding. However, the mechanical connection causes the compressor disc to be thick and high in quality, which increases the overall weight of the engine; while the electron beam welding method has high residual stress after welding, and it is difficult to weld dissimilar materials. The thick compressor disc, too many connecting parts between the discs at each stage, and the difficulty of processing are not conducive to the improvement of the thrust-to-weight ratio and performance of the aircraft engine; they seriously restrict the improvement of the overall performance of the aircraft engine. Summary of the invention

[0003] The purpose of the present invention is to solve the above-mentioned problem and to provide a clamping tool for processing an aircraft engine compressor disc.

[0004] A clamping tool for processing an aero-engine compressor disc comprises: a clamping frame shell 1, a first clamping mechanism 2, a tool positioning plate 3, a fixed support plate 4, a second clamping mechanism 5, a clamping drive mechanism 6, a floating support seat 7, and a clamping spring ring 8; the clamping frame shell 1 is provided with a first sliding sleeve opening 12 and a second sliding sleeve opening 13; the first clamping mechanism 2 is sleeved in the first sliding sleeve opening 12; the tool positioning plate 3, the fixed support plate 4 and the second clamping mechanism 5 are sequentially connected and sleeved in the first clamping mechanism 2; one end of the clamping drive mechanism 6 is sleeved in the second sliding sleeve opening 13; the clamping drive mechanism 6 supports the inner end surface of the tail seat 91 of the compressor disc through the floating support seat 7; the clamping drive mechanism 6 is provided with a locking nut 64; the locking nut 64 is rotated to drive the second clamping mechanism 5 to move in the first sliding sleeve opening 12, so that the second clamping mechanism 5 can clamp the outer end surfaces of the compressor discs of each stage of the engine through the clamping spring ring 8.

[0005] The front end of the clamping frame shell 1 is a spherical rotating body, and the rear end of the clamping frame shell 1 is provided with a tooling fixed clamping part 11; the tooling fixed clamping part 11 is fixed on the processing fixed bracket; a bolt locking hole 121 is provided at the inner axis of the first sliding sleeve 12; a plurality of annular arrays of clamping claw sliding parts 122 are provided on the outer side of the first sliding sleeve 12; the sides of the plurality of clamping claw sliding parts 122 are provided with inclined first T-shaped sliding rails 123; the inclination angles of the plurality of first T-shaped sliding rails 123 intersect on the axis line of the clamping frame shell 1.

[0006] The first clamping claw mechanism 2 comprises: an outward-moving clamping claw sleeve 21 and an outward-moving clamping claw 22. The outward-moving clamping claw sleeve 21 is sleeved in the first sliding sleeve opening 12. A plurality of clamping claw connecting sleeve openings 212 arranged in a circular array are provided on the side of the outward-moving clamping claw sleeve 21. The clamping claw connecting sleeve openings 212 are all provided with outward-moving clamping claws 22. A plurality of outward-moving clamping claws 22 are clamped on the outer end surface of the clamping spring coil 8.

[0007] The second clamping claw mechanism 5 includes: an inward-moving clamping claw sleeve 51 and an inward-moving clamping claw 52; the inward-moving clamping claw sleeve 51 is an annular component; the inward-moving clamping claw sleeve 51 is fixed to the end face of the tooling positioning plate 3 by bolts; a plurality of second T-shaped sliding rails 511 are provided on the inner ring edge of the inward-moving clamping claw sleeve 51; a second T-shaped slide groove is provided on the outer side of the inward-moving clamping claw 52, ​​and the second T-shaped slide groove is sleeved on the second T-shaped sliding rail 511; the second T-shaped sliding rail 511 is inclined, and the inclination angles of the plurality of second T-shaped sliding rails 511 intersect on the axial center line of the clamping frame housing 1.

[0008] The tooling positioning plate 3 and the fixed support plate 4 are both provided with shaft sleeve through holes with the same inner diameter at the center; the tooling positioning plate 3 is sleeved in the outward clamping claw sleeve 21; the edge of the tooling positioning plate 3 and the outward clamping claw sleeve 21 are clearance-matched; the inward clamping claw sleeve 51 and the fixed support plate 4 are fixed to the same side end surface of the tooling positioning plate 3 by bolts.

[0009] The clamping drive mechanism 6 includes: a nut sleeve 61, a screw rod 62, a screw rod connecting plate 63, a locking nut 64, and a sliding sleeve; the inner side of the nut sleeve 61 is threadedly connected to the outer side of the screw rod 62; the screw rod connecting plate 63 is locked and connected to the nut sleeve 61; the locking nut 64 is fixed to the middle part of the shaft sleeve 631; the clamping frame housing 1 is also provided with a connecting locking screw 18, which passes through the screw rod connecting plate 63 and the screw rod 62 and is locked in the bolt locking hole 121; the screw rod 62 rotates on the connecting locking screw 18 through the sliding sleeve.

[0010] The sleeve hole of the floating support seat 7 and the nut smooth axis portion of the locking nut 64 are transitionally matched.

[0011] The processing fixing bracket is a friction welding machine fixing seat or an electroplating clamping handle.

[0012] The present technical scheme provides a clamping tool for processing an aircraft engine compressor disk, comprising: a clamping frame shell 1, a first clamping jaw mechanism 2, a tool positioning disk 3, a fixed support disk 4, a second clamping jaw mechanism 5, a clamping drive mechanism 6, a floating support seat 7, and a clamping spring ring 8; the first clamping jaw mechanism 2, the tool positioning disk 3, the fixed support disk 4, the second clamping jaw mechanism 5, the clamping drive mechanism 6, the floating support seat 7, and the clamping spring ring 8 are arranged inside the clamping frame shell 1; the clamping drive mechanism 6 supports the inner end surface of the tail seat 91 of the compressor disk through the floating support seat 7; the clamping drive mechanism 6 is provided with a locking nut 64; the locking nut 64 is rotated to drive the second clamping jaw mechanism 5 to retract or extend into the clamping frame shell 1, so that the second clamping jaw mechanism 5 can clamp the outer end surfaces of each stage of the compressor disk of the engine through the clamping spring ring 8; it is convenient for friction welding and electroplating and other fine processing of multi-stage compressor disks of different thicknesses. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is an overall schematic diagram of a clamping tool for processing an aircraft engine compressor disc of the utility model;

[0014] Figure 2 This is a schematic cross-sectional view of the internal structure of a clamping tool for machining an aircraft engine compressor disc of the utility model;

[0015] Figure 3 This is a schematic diagram of the structure of a clamping frame shell of a clamping tool for machining an aircraft engine compressor disc of the utility model;

[0016] Figure 4 This is a schematic diagram of a first clamping jaw mechanism of a clamping tool for machining an aircraft engine compressor disc of the utility model;

[0017] Figure 5 This is a schematic diagram of the second clamping jaw mechanism of a clamping tool for machining an aircraft engine compressor disc of the utility model;

[0018] Figure 6 This is a schematic diagram of the clamping state of the tail plate of a clamping tool for machining an aircraft engine compressor plate of the utility model;

[0019] Figure 7 This is a schematic diagram of the clamping state of a three-stage compressor disc of a clamping tool for machining an aircraft engine compressor disc of the utility model;

[0020] Figure 8 This is a schematic diagram of the friction welding application of a clamping tool for processing an aircraft engine compressor disc of the utility model;

[0021] Fig. 9 This is a schematic diagram of the electroplating processing application of a clamping tool for processing an aircraft engine compressor disc of the utility model;

[0022] In the figure: 1, clamping frame housing, 11, tooling fixed clamping part, 12, first sliding sleeve, 121, bolt locking hole, 122, clamping claw sliding part, 123, first T-shaped sliding rail, 13, second sliding sleeve, 14, top screw through hole, 18, connecting locking screw, 2, first clamping claw mechanism, 21, outward clamping claw sleeve, 211, nut sleeve, 212, clamping claw connecting sleeve, 22, outward clamping claw, 221, first arc-shaped clamping surface, 222, first T-shaped slide groove, 223, clamping claw connecting part, 3, tooling positioning plate, 4, fixed support plate, 5, second clamping claw mechanism, 51, inward clamping claw sleeve, 511, second T-shaped sliding rail, 52, inward moving clamping claw, 6, clamping drive mechanism, 61, nut sleeve, 611, internal thread, 62, screw rod, 621, external thread, 63, screw rod connecting plate, 631, shaft sleeve, 632, connecting plate, 64, locking nut, 651, first sliding sleeve, 652, second sliding sleeve, 7, floating support seat, 8, clamping spring ring, 9, compressor disk, 91, compressor disk first disk, 92, compressor disk second disk, 93, compressor disk first disk, A1, electric spindle, A11, friction drive shaft, A12, compressor disk rotating clamping frame, A2, friction welding machine fixed seat, B1, electroplating clamping handle. DETAILED DESCRIPTION

[0023] The technical scheme will be further described clearly and completely below in conjunction with the accompanying drawings of the technical scheme. The described embodiments are only a part of the technical scheme, not all of the embodiments. Based on the technical scheme, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model.

[0024] See also Figures 1 to 7 As shown, a clamping tool for processing an aircraft engine compressor disc comprises: a clamping frame housing 1, a first clamping jaw mechanism 2, a tool positioning disc 3, a fixed support disc 4, a second clamping jaw mechanism 5, a clamping drive mechanism 6, a floating support seat 7, and a clamping spring ring 8;

[0025] The front end of the clamping frame housing 1 is a spherical rotating body, and the rear end of the clamping frame housing 1 is provided with a tool fixing clamping portion 11; the inside of the clamping frame housing 1 is provided with a first sliding sleeve opening 12 and a second sliding sleeve opening 13;

[0026] The inner diameter of the first sliding sleeve opening 12 is greater than the inner diameter of the second sliding sleeve opening 13;

[0027] The first sliding sleeve 12 is a rotary cavity, and a bolt locking hole 121 is provided at the inner axis of the first sliding sleeve 12;

[0028] The clamping frame housing 1 is further provided with a connecting locking screw 18, one end of which is provided with an external threaded portion, and the external threaded portion of the connecting locking screw 18 is locked in the bolt locking hole 121;

[0029] A plurality of clamping claw sliding parts 122 are arranged on the outer side of the first sliding sleeve 12; the plurality of clamping claw sliding parts 122 have the same structure and are arranged in a circular array with the axis of the clamping frame housing 1 as the center; the sides of the plurality of clamping claw sliding parts 122 are all provided with inclined first T-shaped sliding rails 123;

[0030] The inclination angles of the first T-shaped sliding rails 123 intersect on the axis of the clamping frame housing 1;

[0031] A top screw through hole 14 is also provided on the clamping end surface of the clamping frame housing 1; a clamping top screw is provided in the top screw through hole 14.

[0032] The first clamping jaw mechanism 2 comprises: an outward clamping jaw sleeve 21 and an outward clamping jaw 22;

[0033] The outer moving clamping claw sleeve 21 is a cover-shaped component, and the outer moving clamping claw sleeve 21 is sleeved in the first sliding sleeve opening 12;

[0034] The central part of the outer clamping claw sleeve 21 is provided with a nut sleeve 211, and the side of the outer clamping claw sleeve 21 is provided with a plurality of clamping claw connection sleeves 212 arranged in a circular array; the plurality of clamping claw connection sleeves 212 have the same structure;

[0035] The jack screw through hole 14 is provided with a clamping jack screw, and the outward clamping claw sleeve 21 moves in the first sliding sleeve opening 12 through the jack screw;

[0036] The inner side of the outward clamping jaw 22 is provided with a first arc-shaped clamping surface 221; the outer side of the outward clamping jaw 22 is provided with a first T-shaped sliding groove 222; the tail end of the outward clamping jaw 22 is provided with a clamping jaw connecting portion 223;

[0037] The first T-shaped slide groove 222 is sleeved on the first T-shaped sliding rail 123; the first T-shaped slide groove 222 and the first T-shaped sliding rail 123 have the same inclination angle;

[0038] There are a plurality of the outwardly movable clamping jaws 22 , and the plurality of the outwardly movable clamping jaws 22 are respectively sleeved in the clamping jaw connecting sleeve opening 21 through their clamping jaw connecting portions 223 .

[0039] The tooling positioning plate 3 is sleeved in the outward moving clamping claw sleeve 21; the edge of the tooling positioning plate 3 is gap-matched with the outward moving clamping claw sleeve 21; the fixed support plate 4 is fixed to the center of one side end surface of the tooling positioning plate 3 by bolt locking;

[0040] The tooling positioning plate 3 and the fixed support plate 4 are both provided with shaft sleeve through holes with the same inner diameter at the center.

[0041] The second clamping jaw mechanism 5 comprises: an inner clamping jaw sleeve 51 and an inner clamping jaw 52;

[0042] The inner moving clamping claw sleeve 51 is an annular component; the inner moving clamping claw sleeve 51 is arranged on the same side as the fixed support plate 4, and the inner moving clamping claw sleeve 51 is fixed to the end surface of the tooling positioning plate 3 by bolts; a plurality of second T-shaped sliding rails 511 are arranged on the inner ring edge of the inner moving clamping claw sleeve 51;

[0043] The second T-shaped sliding rails 511 are tilted, and the tilt angles of the second T-shaped sliding rails 511 intersect on the axis of the clamping frame housing 1;

[0044] There are several inward-moving clamping jaws 52, and the structures of the several inward-moving clamping jaws 52 are the same; a second T-shaped slide groove is provided on the outer side of the inward-moving clamping jaw 52, ​​and the second T-shaped slide groove is sleeved on the second T-shaped sliding rail 511; that is, the second T-shaped sliding rail 511 is provided with an inward-moving clamping jaw 52, ​​and the inward-moving clamping jaw 52 is sleeved on the second T-shaped sliding rail 511 through the second T-shaped slide groove on one side thereof.

[0045] The clamping drive mechanism 6 comprises: a nut sleeve 61, a screw rod 62, a screw rod connecting plate 63, a locking nut 64, and a sliding sleeve;

[0046] The outer side of the nut sleeve 61 is an optical axis surface, and the nut sleeve 61 is axially connected to the second sliding sleeve opening 13;

[0047] The inner side of the nut sleeve 61 is provided with an internal thread 611; the outer side of the screw rod 62 is provided with an external thread 621, and the inside of the screw rod 62 is provided with a stepped optical axis through hole; the internal thread 611 is threadedly connected with the external thread 621;

[0048] One side of the screw connecting plate 63 is a shaft sleeve 631, and the other end of the screw connecting plate 6 is a connecting plate 632; the shaft sleeve 631 and the connecting plate 632 are integrally formed; the connecting plate 632 is locked and connected to the nut sleeve 61 by screws; the locking nut 64 is fixed to the middle of the shaft sleeve 631;

[0049] The shaft sleeve 631 is sleeved in the shaft sleeve through holes of the tooling positioning plate 3 and the fixed support plate 4; the inner side of the screw connecting plate 63 is provided with a shaft through hole, the rod body of the connecting locking screw 18 is sleeved in the shaft through hole, and the nut 181 at one end of the connecting locking screw 18 is against the end of the shaft sleeve 631;

[0050] A nut smooth shaft portion is provided in the middle of the locking nut 64 ; one side of the nut smooth shaft portion abuts against the edge of the shaft sleeve through hole of the fixed support plate 4 .

[0051] The floating support seat 7 is provided with a sleeve hole at the center, and the nut smooth axis portion of the locking nut 64 is sleeved in the sleeve hole of the floating support seat 7;

[0052] The sliding sleeve is divided into a first sliding sleeve 651 and a second sliding sleeve 652 , which are respectively arranged at both ends of the inner diameter of the screw rod 62 ; the screw rod 62 rotates on the connecting locking screw 18 through the first sliding sleeve 651 and the second sliding sleeve 652 .

[0053] The sleeve hole of the floating support seat 7 and the nut smooth axis portion of the locking nut 64 are transitionally matched.

[0054] The clamping spring ring 8 is an annular component, and a plurality of outwardly moving clamping claws 22 are clamped on the outer end surface of the clamping spring ring 8 .

[0055] See attached Figure 6 , 7 As shown, friction welding can be performed using the clamping tool for processing an aircraft engine compressor disc described in Example 1;

[0056] A clamping tool for processing an aircraft engine compressor disc, comprising: a clamping frame shell 1, a first clamping jaw mechanism 2, a tool positioning disc 3, a fixed support disc 4, a second clamping jaw mechanism 5, a clamping drive mechanism 6, a floating support seat 7, and a clamping spring ring 8;

[0057] The friction welding machine is provided with an electric spindle A1 and a friction welding machine fixing seat A2;

[0058] The rear end of the clamping frame shell 1 is provided with a tool fixing clamping part 11; a chuck is provided on the friction welding machine fixing seat A2, and the tool fixing clamping part 11 is fixed on the friction welding machine fixing seat A2 by the chuck clamping; the inward moving clamping jaw 52 in the second clamping jaw mechanism 5 clamps the outer end surface of the compressor disk first-stage disk 91, and the inner end surface of the compressor disk first-stage disk 91 is sleeved on the fixed support disk 4; the compressor disk first-stage disk 91, the compressor disk second-stage disk 92, the compressor disk first-stage disk 93, etc. can be friction welded one by one; through multiple stages of compressor disks, it becomes a complete compressor disk 9.

[0059] The electric spindle A1 is provided with a friction drive shaft A11, and the friction drive shaft A11 is provided with a compressor disc rotating clamping frame A12, and the compressor disc to be welded is clamped on the compressor disc rotating clamping frame A12; the compressor disc rotating clamping frame A12 clamps the outer end surface of the compressor disc secondary disc 92, so that the centrifugal deformation of the compressor disc secondary disc 92 is reduced when the compressor disc secondary disc 92 rotates at a high speed;

[0060] The friction welding machine welds the compressor disc secondary disc 92 and the compressor disc primary disc 91 into shape by high-speed rotation; the compressor disc primary disc 91 and the compressor disc secondary disc 92 become one body.

[0061] After the friction welding of the compressor disc primary plate 91 and the compressor disc secondary plate 92 is completed, the locking nut 64 is rotated to retract the second clamping jaw mechanism 5 into the clamping frame housing 1; the inward clamping jaw 52 in the second clamping jaw mechanism 5 clamps the outer end surface of the compressor disc primary plate 91, and the inner end surface of the compressor disc primary plate 91 is sleeved on the fixed support plate 4;

[0062] The outward-moving clamping jaw 22 provided in the first clamping jaw mechanism 2 clamps the outer end face of the clamping spring coil 8, and the inner end face of the clamping spring coil 8 clamps the outer end face of the secondary disk 92 of the compressor disk; the friction welding machine fixing seat A2 clamps the primary disk 93 of the compressor disk, and then the friction welding machine welds the secondary disk 92 of the compressor disk and the tertiary disk 93 of the compressor disk into shape through high-speed rotation; the other disk levels of the compressor disk are friction welded in sequence.

[0063] See attached Figure 8 As shown, the clamping tool for processing the compressor disc of an aircraft engine described in Example 1 can be used for electroplating or welding point grinding;

[0064] A clamping tool for processing an aircraft engine compressor disc, wherein one end of a clamping frame shell 1 of the clamping tool is provided with a tool fixing clamping portion 11;

[0065] The electroplating clamping device is provided with an electroplating clamping handle B1, and the electroplating clamping handle B1 clamps the clamping part 11 of the tooling; the clamping tooling can perform fine processing on the compressor disk first-stage disk 91, the compressor disk second-stage disk 92, the compressor disk first-stage disk 93, etc. one by one, and the welding points between the compressor disks of each level are clamped by the clamping tooling, and then the compressor disks of each level are electroplated or the welding points are polished.

[0066] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A clamping tool for processing an aircraft engine compressor disc, comprising: A clamping frame shell (1), a first clamping jaw mechanism (2), a tool positioning plate (3), a fixed support plate (4), a second clamping jaw mechanism (5), a clamping drive mechanism (6), a floating support seat (7), and a clamping spring ring (8); characterized in that: the clamping frame shell (1) is provided with a first sliding sleeve (12) and a second sliding sleeve (13) inside; the first clamping jaw mechanism (2) is sleeved in the first sliding sleeve (12); the tool positioning plate (3), the fixed support plate (4) and the second clamping jaw mechanism (5) are sequentially connected and sleeved in The first clamping mechanism (2) has one end of a clamping drive mechanism (6) sleeved in a second sliding sleeve opening (13); the clamping drive mechanism (6) supports the inner end surface of the tail seat (91) of the compressor disk through a floating support seat (7); the clamping drive mechanism (6) is provided with a locking nut (64); the locking nut (64) is rotated to drive the second clamping mechanism (5) to retract into or extend into the first sliding sleeve opening (12), so that the second clamping mechanism (5) can clamp the outer end surface of each stage of the compressor disk of the engine through a clamping spring ring (8).

2. The clamping tool for machining an aircraft engine compressor disc according to claim 1, characterized in that: The front end of the clamping frame shell (1) is a spherical rotating body, and the rear end of the clamping frame shell (1) is provided with a tool fixing clamping part (11); the tool fixing clamping part (11) is fixed on the processing fixing bracket; a bolt locking hole (121) is provided at the inner axis of the first sliding sleeve (12); a plurality of clamping claw sliding parts (122) in an annular array are provided on the outer side of the first sliding sleeve (12); the sides of the plurality of clamping claw sliding parts (122) are all provided with inclined first T-shaped sliding rails (123); the inclination angles of the plurality of first T-shaped sliding rails (123) intersect on the axis line of the clamping frame shell (1).

3. The clamping tool for machining an aircraft engine compressor disc according to claim 2, characterized in that: The first clamping claw mechanism (2) comprises: an outward-moving clamping claw sleeve (21) and an outward-moving clamping claw (22); the outward-moving clamping claw sleeve (21) is sleeved in a first sliding sleeve opening (12); a plurality of clamping claw connecting sleeve openings (212) arranged in a circular array are provided on the side of the outward-moving clamping claw sleeve (21); outward-moving clamping claws (22) are provided at the clamping claw connecting sleeve openings (212); and the plurality of outward-moving clamping claws (22) are clamped on the outer end surface of the clamping spring coil (8).

4. The clamping tool for machining an aircraft engine compressor disc according to claim 3, characterized in that: A top screw through hole (14) is also provided on the clamping end surface of the clamping frame housing (1); a clamping top screw is provided in the top screw through hole (14), and the outwardly movable clamping claw sleeve (21) moves in the first sliding sleeve opening (12) through the top screw.

5. The clamping tool for machining an aircraft engine compressor disk according to claim 4, characterized in that: The second clamping claw mechanism (5) comprises: an inwardly moving clamping claw sleeve (51) and an inwardly moving clamping claw (52); the inwardly moving clamping claw sleeve (51) is an annular component; the inwardly moving clamping claw sleeve (51) is fixed to the end surface of the tooling positioning plate (3) by bolt locking; a plurality of second T-shaped sliding rails (511) are provided on the inner ring edge of the inwardly moving clamping claw sleeve (51); a second T-shaped sliding groove is provided on the outer side of the inwardly moving clamping claw (52), and the second T-shaped sliding groove is sleeved on the second T-shaped sliding rail (511); the second T-shaped sliding rail (511) is inclined, and the inclination angles of the plurality of second T-shaped sliding rails (511) intersect on the axis line of the clamping frame housing (1).

6. The clamping tool for machining an aircraft engine compressor disk according to claim 5, characterized in that: The tooling positioning plate (3) and the fixed support plate (4) are both provided with shaft sleeve through holes with the same inner diameter at their centers; the tooling positioning plate (3) is sleeved in the outward clamping claw sleeve (21); the edge of the tooling positioning plate (3) and the outward clamping claw sleeve (21) are clearance-matched; the inward clamping claw sleeve (51) and the fixed support plate (4) are fixed to the same side end surface of the tooling positioning plate (3) by bolt locking.

7. The clamping tool for machining an aircraft engine compressor disk according to claim 6, characterized in that: The clamping drive mechanism (6) comprises: a nut sleeve (61), a screw rod (62), a screw rod connecting plate (63), a locking nut (64), and a sliding sleeve; the inner side of the nut sleeve (61) is threadedly connected to the outer side of the screw rod (62); the screw rod connecting plate (63) is locked and connected to the nut sleeve (61); the locking nut (64) is fixed to the middle part of the shaft sleeve (631); a connecting locking screw (18) is also provided in the clamping frame housing (1), and the connecting locking screw (18) passes through the screw rod connecting plate (63) and the screw rod (62) and is locked in the bolt locking hole (121); a nut (181) provided at one end of the connecting locking screw (18) abuts against the end of the shaft sleeve (631); the screw rod (62) rotates on the connecting locking screw (18) through the sliding sleeve.

8. The clamping tool for machining an aircraft engine compressor disk according to claim 7, characterized in that: A nut smooth shaft portion is provided in the middle of the locking nut (64); one side of the nut smooth shaft portion abuts against the edge of the shaft sleeve through hole of the fixed support plate (4).

9. The clamping tool for machining an aircraft engine compressor disk according to claim 8, characterized in that: The sleeve hole of the floating support seat (7) is transitionally matched with the nut smooth axis portion of the locking nut (64).

10. The clamping tool for machining an aircraft engine compressor disc according to claim 2 or 8, characterized in that: The processing fixing bracket is a friction welding machine fixing seat or an electroplating clamping handle.