Assembly equipment for aero-engine rotary body part

Abstract

The invention discloses assembly equipment for aero-engine rotary body parts, and relates to the field of aero-engine production process equipment design, the assembly equipment comprises an assembly frame, an assembly table is fixedly arranged on the surface of the assembly frame, a manipulator assembly station is arranged on one side of the assembly table, and the bottom of the assembly frame is covered with a supporting table; a supporting column is fixedly mounted at the bottom of the supporting table, a mounting frame is fixedly mounted on the supporting column, and a speed reducer is fixedly connected to the mounting frame. According to the assembly equipment for the rotary body part of the aero-engine, an initial fixing groove A, an initial fixing groove B, a blade seat, a blade tail and a butt joint auxiliary column set are combined together to form an impeller and blade positioning structure, a large number of impellers are all accurately installed on the outer sides of the impellers at a time, compared with one-by-one blade clamping, the assembly steps and time are greatly reduced, and the assembly efficiency is improved. And the method is particularly suitable for large-scale production, and the production cycle of the aero-engine can be effectively shortened.

Description

Technical Field

[0001] The invention relates to the field of aircraft engine production process equipment design, in particular to an assembly device for aircraft engine rotary body parts. Background Art

[0002] At present, the most common way to assemble aircraft engine connection bolts is to use sockets, wrenches or pneumatic tools for pre-assembly, and finally tighten the bolts manually with the help of standard tools such as torque wrenches. This process has at least the following three defects: 1. There are many assembly processes, many types of tools, and low assembly efficiency; 2. Manual counting and inspection are used, which is prone to quality problems such as missing assembly and torque errors; 3. The assembly process has poor repeatability and the assembly data is not traceable;

[0003] To solve the above problems, after searching, a Chinese patent with the announcement number CN111843418A discloses an assembly device for an aircraft engine rotary body part, wherein the assembly device includes a tightening mechanism, a support turntable and a control assembly, and the control lines of the tightening mechanism and the support turntable are connected to the control assembly; the aircraft engine rotary body part fixed on the support turntable is tightened according to regulations by the tightening mechanism under the control of the control assembly and the cooperation of the support turntable, and the adjustable support assembly includes an adjustable support frame, an adjusting member and a locking member, and the adjustable support frame preliminarily adjusted in place is locked by the locking member; during the assembly process of the aircraft engine rotary body part, the tightening shaft supported on the adjustable support frame is precisely adjusted by the adjusting member to tighten the tightening work of the connecting bolts, and the control line of the adjusting member is connected to the control assembly;

[0004] When the above-mentioned assembly equipment is in use, when the rotating body structure (impeller, blades) of the aircraft engine is assembled, the blades are grouped and marked according to the model, size and installation position of the blades for accurate installation; the blades are installed one by one in the corresponding slots of the impeller, usually by the tenon and the tenon groove matching method; during installation, it is necessary to ensure that the tenon of the blade and the tenon groove of the impeller are tightly matched without gap or looseness, and at the same time, attention should be paid to the correct installation angle and direction of the blade; a locking device (such as a locking plate, a locking wire, etc.) is used to fix the installed blades to prevent the blades from being displaced or vibrated when the engine is running; in the above-mentioned installation process, a large number of blades need to be clamped and fixed one by one in the installation groove opened on the outer side of the impeller circumference. Clamping the blades one by one is a relatively cumbersome and time-consuming process, which requires the operator to have a high degree of patience and meticulousness, which will lead to a slow overall assembly speed and affect production efficiency. Especially in large-scale production, this inefficiency problem will be more obvious; therefore, there is an urgent need for an assembly device for the rotating body parts of an aircraft engine to solve the above-mentioned defects. Summary of the invention

[0005] The object of the present invention is to provide an assembly device for aircraft engine rotary parts to solve the defects mentioned in the above background technology.

[0006] To achieve the above-mentioned purpose, an assembly device for a rotating body part of an aircraft engine is provided, comprising an assembly rack, an assembly table is fixedly arranged on the surface of the assembly rack, a manipulator assembly station is arranged on one side of the assembly table, the bottom of the assembly rack is covered with a support table, a support column is fixedly installed on the bottom of the support table, a mounting rack is fixedly installed on the support column, a reducer is fixedly connected to the mounting rack, a driving gear is fixedly installed on the end of the output shaft of the reducer, blades are arranged on the surface of the assembly table, and an impeller is arranged on the blades.

[0007] Furthermore, the assembly frame is a circular structure made of engineering plastic material, and the support platform at the bottom of the assembly frame is circular, and the axial sections of the support platform and the assembly frame are concentric circle structures; five groups of limit seats are evenly installed on the bottom of the assembly frame, and a ring-shaped limit track is opened on the surface of the support platform, and the axial sections of the limit track and the support platform are concentric circle structures, the sizes of the limit seats and the limit track are matched, and the five groups of limit seats are all slidably set inside the limit track; the cross-sections of the limit seats and the limit track are both dovetail-shaped.

[0008] Furthermore, five groups of assembly tables are evenly installed on the surface of the assembly rack, the distance between two adjacent groups of assembly tables is consistent, the assembly tables are circular structures, two groups of countersunk holes are opened on the five groups of assembly tables, the five groups of assembly tables cover the surface of the assembly rack and are fixed by countersunk holes and bolts; the five groups of assembly tables are arranged in a plum blossom shape.

[0009] Furthermore, the structures of the five groups of assembly tables are consistent. The assembly tables are detachable structures on the surface of the assembly frame. The assembly tables are rotated through a reducer, a driving gear and a passive gear. The passive gear is fixedly connected to the circumferential inner wall surface of the assembly frame. The sizes of the driving gear and the passive gear are matched. The driving gear and the passive gear are meshed and connected, and a servo motor is arranged on the reducer.

[0010] Furthermore, the five sets of assembly tables rotate at an angle of 72 degrees each time, and the assembly tables are arranged directly below the assembly station of the manipulator.

[0011] Furthermore, the surface of the assembly table is provided with a plurality of groups of blade positioning grooves, the blade positioning grooves include a preliminary groove A and a preliminary groove B, one end of the blade is fixedly mounted with a blade seat, the end of the blade away from the blade seat is fixedly provided with a blade tail, and a plurality of groups of wheel grooves are evenly provided on the circumferential outer wall of the impeller; a docking auxiliary column group is fixedly provided in the middle of the assembly table; the preliminary groove A and the preliminary groove B are both provided on the surface of the assembly table.

[0012] Further, the number of the blades is consistent with the number of the blade positioning grooves. Multiple groups of blades are positioned and placed on the assembly table through the blade positioning grooves, and the impeller is installed on the assembly table through the docking auxiliary column group; the axial sections of the impeller, the blades and the assembly table are concentric circle structures.

[0013] Further, one end of the blade is clamped inside the initial fixing groove B through the blade tail, and the other end of the blade is clamped inside the initial fixing groove A through the blade seat. The depths of the initial fixing groove A and the initial fixing groove B are the same.

[0014] Further, the sizes of the wheel groove and the blade seat are adapted to each other. The blade seat is clamped inside the wheel groove. At the same time, multiple groups of mounting holes are evenly formed in the wheel groove. The blade seat is inserted into the wheel groove and fixed by bolts.

[0015] Further, the docking auxiliary column group includes five positioning columns fixedly connected to the middle of the surface of the assembly table, and the distribution positions of the five positioning columns are consistent with the distribution positions in the middle of the impeller. At the same time, the impeller is clamped on the surface of the assembly table through the docking auxiliary column group and is positioned and installed with the blades.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] 1. In the present invention, one end of the blade is clamped inside the initial fixing groove B through the blade tail, and the other end of the blade is clamped inside the initial fixing groove A through the blade seat; a large number of blades are quickly positioned and installed on the upper surface of the assembly table; the mounting hole positions on the impeller are inserted into the docking auxiliary column group. At this time, a large number of wheel grooves on the outer circumference of the impeller are respectively clamped on a large number of blade seats, and then the fixing structure is used for fixing work; the initial fixing groove A, the initial fixing groove B, the blade seat, the blade tail and the docking auxiliary column group are combined together to form the positioning structure of the impeller and the blades, realizing the accurate installation of a large number of impellers on the outside of the impeller at one time. Compared with clamping the blades one by one, the assembly steps and time are greatly reduced, and the production efficiency is significantly improved. It is especially suitable for large-scale production and can effectively shorten the production cycle of aeroengines;

[0018] 2. The present invention uses five groups of assembly tables to rotate at an angle of 72 degrees each time. When the assembly table moves to the bottom of the robot assembly station, the assembly table is in a state where the rotating body parts need to be assembled; the five groups of assembly tables are used alternately, and when the assembly table is not at the bottom of the robot assembly station, a large number of blades can be pre-installed on the surface of the assembly table; the five groups of assembly tables are used alternately, and when one assembly table is assembling the rotating body parts under the robot assembly station, other assembly tables can pre-install the blades at the same time, thereby realizing the parallelization of assembly work, reducing waiting time, and improving the overall assembly efficiency; when the assembly table is not at the bottom of the robot assembly station, the blades are pre-installed, which can make full use of the time gap between the movement of the assembly table and the work of the robot, making the entire assembly process more compact, effectively improving production efficiency, and shortening the production cycle of the product; the assembly of the rotating body parts is divided into two different stages and carried out at different positions, which helps to optimize the assembly workflow, make the work of each station more professional and standardized, reduce the complexity of operation, and improve the stability of assembly quality; by reasonably arranging the workflow;

[0019] 3. The present invention allows operators to work alternately between different assembly tables. After completing the assembly of the rotating body parts on one group of assembly tables, they can turn to the next group of rotating body parts for assembly work; avoiding long-term continuous single assembly operation, thereby reducing labor intensity, reducing operator fatigue, and helping to improve work accuracy and quality; the alternating use of five groups of assembly tables improves the equipment utilization rate of the robot assembly station and the assembly table, avoids equipment idle time, gives full play to the performance of the equipment, and reduces production costs; when the assembly frame is rotating, five groups of limit seats are arranged at the bottom, the sizes of the limit seats and the limit rails are matched, and the five groups of limit seats are all slidably arranged inside the limit rails; the assembly frame can be limited and guided during movement to ensure the stability of the assembly frame during circular motion. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a front view schematic diagram of the structure of the present invention;

[0021] Figure 2 A side view of the structure of the present invention;

[0022] Figure 3 A bottom view of the structure of the present invention;

[0023] Figure 4 A top view of the structure of the present invention;

[0024] Figure 5 is a cross-sectional view of the structure of the present invention;

[0025] Figure 6 This is a schematic diagram of the surface installation structure of the structural assembly platform of the present invention;

[0026] Figure 7 This is a bottom view of the assembly of the impeller and blades of the structure of the present invention.

[0027] [reference numerals]

[0028] 1. Assembly frame; 11. Support table; 12. Limit seat; 13. Limit track; 2. Assembly table; 21. Initial groove A; 22. Initial groove B; 23. Docking auxiliary column group; 3. Support column; 4. Mounting frame; 5. Reducer; 51. Driving gear; 52. Passive gear; 6. Impeller; 61. Wheel groove; 7. Blade; 71. Impeller seat; 72. Impeller tail; 8. Manipulator assembly station. DETAILED DESCRIPTION

[0029] Specific implementation method 1: Please refer to Figure 1-Figure 7 The present invention provides a technical solution: an assembly device for an aircraft engine rotating body part, comprising an assembly rack 1, an assembly table 2 is fixedly arranged on the surface of the assembly rack 1, a manipulator assembly station 8 is arranged on one side of the assembly table 2, the bottom of the assembly rack 1 is covered with a support table 11, a support column 3 is fixedly installed on the bottom of the support table 11, a mounting rack 4 is fixedly installed on the support column 3, a reducer 5 is fixedly connected to the mounting rack 4, a driving gear 51 is fixedly installed on the output shaft end of the reducer 5, a blade 7 is arranged on the surface of the assembly table 2, and an impeller 6 is arranged on the blade 7.

[0030] Working principle: When actually using the blades, a large number of blades 7 to be assembled are first placed on the upper surface of the assembly table 2. A plurality of groups of initial grooves A21 and initial grooves B22 are evenly arranged on the assembly table 2. By setting the initial grooves A21 and initial grooves B22, the blades 7 can be quickly and accurately positioned and installed on the upper surface of the assembly table 2. The specific method is: the blade 7 is clamped in the interior of the initial groove B22 through the blade tail 72 at one end, and the blade 7 is clamped in the interior of the initial groove A21 through the blade seat 71 at the other end; in this way, a large number of blades 7 are quickly positioned and installed on the upper surface of the assembly table 2. At this time, the impeller 6 can be grabbed by a manipulator, or moved manually, and the installation holes on the impeller 6 are plugged into the docking auxiliary column group 23. At this time, a large number of wheel grooves 61 on the outer side of the circumference of the impeller 6 are respectively clamped on a large number of blade seats 71, so that a large number of impellers 6 can be accurately installed on the outer side of the impeller 6 at one time, and then the fixing structure is used for fixing. The initial groove A21, the initial groove B22, the blade seat 71, the blade tail 72 and the docking auxiliary column group 23 are combined together to form the positioning structure of the impeller 6 and the blade 7. Compared with clamping the blades 7 one by one, the assembly steps are greatly reduced. The invention can significantly improve production efficiency and time, and is particularly suitable for large-scale production, and can effectively shorten the production cycle of aircraft engines; the positioning structure can ensure that each blade 7 is accurately installed at the predetermined position, and ensure the consistency of parameters such as the angle and position of the blade 7 installation, which is conducive to improving the performance stability and reliability of the aircraft engine; it can make the airflow inside the engine more uniform, reduce the airflow turbulence caused by the installation deviation of the blade 7, and thus improve the efficiency and thrust of the engine; it does not require the operator to have extremely high manual assembly skills and rich experience to accurately install the blades 7 one by one, reduce the impact of human factors on the assembly quality, reduce the training cost and difficulty of the operator, and new employees can participate in the operation after relatively simple training; due to the high installation accuracy and good consistency of the blade 7, it is easier to establish a unified inspection standard during quality inspection, and it is also easier to use automated inspection equipment for rapid and accurate inspection, which can timely discover potential installation defects and improve the product quality control level; when the engine is repaired, if the blade 7 needs to be replaced, due to the high installation accuracy and the use of a fixed structure, it is relatively easy to disassemble and replace the blade 7, and the damaged blade 7 can be quickly located and replaced, reducing the maintenance time and cost, and improving the maintainability and availability of the engine;After a group of rotating body parts: impeller 6 and blades 7 are assembled, the external switch of reducer 5 is started, and the output shaft of reducer 5 drives driving gear 51 to rotate, and driving gear 51 is meshed and connected with passive gear 52, driving passive gear 52 to rotate, and passive gear 52 can drive assembly frame 1 to rotate, and five groups of assembly tables 2 are evenly installed on passive gear 52, and the angle of rotation of five groups of assembly tables 2 each time is 72 degrees. When assembly table 2 moves to the bottom of manipulator assembly station 8, this assembly table 2 is in a state where rotating body parts need to be assembled; five groups of assembly tables 2 are used alternately, and when assembly table 2 is not at the bottom of manipulator assembly station 8, a large number of blades 7 can be pre-installed on the surface of assembly table 2; five groups of assembly tables 2 are used alternately, and when one assembly table 2 is assembling rotating body parts under manipulator assembly station 8, other assembly tables 2 can simultaneously pre-install blades 7, so as to realize parallel assembly work. Reduce waiting time and improve overall assembly efficiency; pre-install the blade 7 when the assembly table 2 is not at the bottom of the manipulator assembly station 8, which can make full use of the time gap between the movement of the assembly table 2 and the operation of the manipulator, making the entire assembly process more compact, effectively improving production efficiency, and shortening the production cycle of the product; dividing the assembly of the rotating body parts into two different stages and performing them at different positions helps to optimize the assembly workflow, make the work of each station more professional and standardized, reduce the complexity of operations, and improve the stability of assembly quality; by reasonably arranging the workflow, operators can work alternately between different assembly tables 2, avoiding long-term continuous single assembly operations, thereby reducing labor intensity, reducing operator fatigue, and helping to improve work accuracy and quality; the alternating use of five groups of assembly tables 2 improves the equipment utilization rate of the manipulator assembly station 8 and the assembly table 2, avoids equipment idle time, gives full play to the performance of the equipment, and reduces production costs;

[0031] When the assembly frame 1 is rotating, five groups of limit seats 12 are arranged at the bottom, the sizes of the limit seats 12 and the limit rails 13 are adapted, and the five groups of limit seats 12 are all slidably arranged inside the limit rails 13; the assembly frame 1 can be limited and guided during movement to ensure the stability of the assembly frame 1 during circular motion; when the reducer 5 drives the driving gear 51, the passive gear 52 and the assembly frame 1 to rotate, a servo motor is arranged on the reducer 5, and the step angle of the assembly frame 1 can be adjusted by programming the servo controller on the servo motor, and the step rotation angle of the assembly frame 1 is 72 degrees; after the assembly of a group of rotating body parts on the assembly platform 2 is completed, the next group of rotating body parts can be assembled.

[0032] Specific implementation method 2: This implementation method is a further limitation of specific implementation method 1. The assembly frame 1 is a circular structure made of engineering plastic material, and the support platform 11 at the bottom of the assembly frame 1 is a circular setting, and the axial section of the support platform 11 and the assembly frame 1 is a concentric circle structure; five groups of limit seats 12 are evenly installed at the bottom of the assembly frame 1, and a ring-shaped limit track 13 is opened on the surface of the support platform 11. The axial section of the limit track 13 and the support platform 11 is a concentric circle structure, the sizes of the limit seats 12 and the limit track 13 are matched, and the five groups of limit seats 12 are all slidably set inside the limit track 13; the cross-sections of the limit seats 12 and the limit track 13 are both dovetail-shaped.

[0033] Specific implementation method three: This implementation method is a further limitation of specific implementation method two. Five groups of assembly tables 2 are evenly installed on the surface of the assembly frame 1. The distance between two adjacent groups of assembly tables 2 is consistent. The assembly tables 2 are circular structures. Two groups of countersunk holes are opened on the five groups of assembly tables 2. The five groups of assembly tables 2 cover the surface of the assembly frame 1 and are fixed by countersunk holes and bolts; the five groups of assembly tables 2 are arranged in a plum blossom shape.

[0034] Specific embodiment four: This embodiment is a further limitation of specific embodiment three. The structures of the five groups of assembly tables 2 are consistent. The assembly tables 2 are detachable structures on the surface of the assembly frame 1. The assembly tables 2 are rotated by the reducer 5, the driving gear 51 and the passive gear 52; the passive gear 52 is fixedly connected to the circumferential inner wall surface of the assembly frame 1, the sizes of the driving gear 51 and the passive gear 52 are matched, the driving gear 51 and the passive gear 52 are meshed and connected, and a servo motor is provided on the reducer 5.

[0035] Specific implementation mode five: This implementation mode is a further limitation of specific implementation mode four. The five sets of assembly tables 2 rotate at an angle of 72 degrees each time. The assembly tables 2 are arranged directly below the robot assembly station 8 .

[0036] Specific embodiment six: This embodiment is a further limitation of specific embodiment four, a plurality of groups of blade positioning grooves are provided on the surface of the assembly platform 2, the blade positioning grooves include a preliminary groove A21 and a preliminary groove B22, a blade seat 71 is fixedly installed at one end of the blade 7, a blade tail 72 is fixedly provided at the end of the blade 7 away from the blade seat 71, a plurality of groups of wheel grooves 61 are evenly provided on the circumferential outer wall of the impeller 6; a docking auxiliary column group 23 is fixedly provided in the middle of the assembly platform 2; the preliminary groove A21 and the preliminary groove B22 are both provided on the surface of the assembly platform 2.

[0037] Specific embodiment seven: This embodiment is a further limitation of specific embodiment six. The number of blades 7 is consistent with the number of blade positioning grooves. Multiple groups of blades 7 are positioned on the assembly table 2 through the blade positioning grooves, and the impeller 6 is installed on the assembly table 2 through the docking auxiliary column group 23; the axial section of the impeller 6, blades 7 and the assembly table 2 is a concentric circle structure.

[0038] Specific embodiment eight: This embodiment is a further limitation of specific embodiment six. The blade 7 is clamped in the interior of the preliminary groove B22 through the blade tail 72 at one end, and the blade 7 is clamped in the interior of the preliminary groove A21 through the blade seat 71 at the other end. The depths of the preliminary groove A21 and the preliminary groove B22 are consistent.

[0039] Specific embodiment nine: This embodiment is a further limitation of specific embodiment six. The wheel groove 61 is adapted to the size of the impeller 71. The impeller 71 is snapped into the inside of the wheel groove 61. At the same time, a plurality of groups of mounting holes are evenly arranged on the wheel groove 61. The impeller 71 is inserted into the inside of the wheel groove 61 and fixed by bolts.

[0040] Specific embodiment ten: This embodiment is a further limitation of specific embodiment six. The docking auxiliary column group 23 includes five groups of positioning columns fixedly connected to the middle part of the surface of the assembly platform 2, and the distribution positions of the five groups of positioning columns are consistent with the distribution positions of the middle part of the impeller 6. At the same time, the impeller 6 is clamped on the surface of the assembly platform 2 through the docking auxiliary column group 23 and positioned and installed with the blade 7.

Claims

1. An assembly device for an aircraft engine rotary body component, comprising an assembly stand (1), characterized in that: An assembly platform (2) is fixedly arranged on the surface of the assembly frame (1), a manipulator assembly station (8) is arranged on one side of the assembly frame (2), the bottom of the assembly frame (1) is covered with a support platform (11), a support column (3) is fixedly installed on the bottom of the support platform (11), a mounting frame (4) is fixedly installed on the support column (3), a reducer (5) is fixedly connected to the mounting frame (4), a driving gear (51) is fixedly installed on the end of the output shaft of the reducer (5), a blade (7) is arranged on the surface of the assembly frame (2), and an impeller (6) is arranged on the blade (7).

2. The assembly equipment for aircraft engine rotating parts according to claim 1, characterized in that: The assembly frame (1) is a circular structure made of engineering plastic material, and the support platform (11) at the bottom of the assembly frame (1) is circularly arranged, and the axial sections of the support platform (11) and the assembly frame (1) are concentric structures; five groups of limit seats (12) are evenly installed at the bottom of the assembly frame (1), and a ring-shaped limit track (13) is provided on the surface of the support platform (11), and the axial sections of the limit track (13) and the support platform (11) are concentric structures, the sizes of the limit seats (12) and the limit track (13) are matched, and the five groups of limit seats (12) are all slidably arranged inside the limit track (13); the cross sections of the limit seats (12) and the limit track (13) are both dovetail-shaped.

3. The assembly equipment for aircraft engine rotating parts according to claim 2, characterized in that: Five groups of assembly platforms (2) are evenly mounted on the surface of the assembly rack (1), the distance between two adjacent groups of assembly platforms (2) is the same, the assembly platforms (2) are of a circular structure, two groups of countersunk holes are opened on the five groups of assembly platforms (2), the five groups of assembly platforms (2) cover the surface of the assembly rack (1) and are fixed by countersunk holes and bolts; the five groups of assembly platforms (2) are arranged in a plum blossom shape.

4. The assembly equipment for aircraft engine rotating parts according to claim 3, characterized in that: The five groups of assembly platforms (2) have the same structure. The assembly platforms (2) are detachable structures on the surface of the assembly frame (1). The assembly platforms (2) are rotated by means of a reducer (5), a driving gear (51) and a passive gear (52). The passive gear (52) is fixedly connected to the circumferential inner wall surface of the assembly frame (1). The sizes of the driving gear (51) and the passive gear (52) are matched. The driving gear (51) and the passive gear (52) are meshed and connected. A servo motor is arranged on the reducer (5).

5. The assembly equipment for aircraft engine rotating parts according to claim 4, characterized in that: The five sets of assembly tables (2) rotate at an angle of 72 degrees each time, and the assembly tables (2) are arranged directly below the robot assembly station (8).

6. An assembly device for aircraft engine rotary parts according to any one of claims 1 or 4, characterized in that: The surface of the assembly platform (2) is provided with a plurality of blade positioning grooves, the blade positioning grooves comprising a preliminary positioning groove A (21) and a preliminary positioning groove B (22); a blade seat (71) is fixedly mounted on one end of the blade (7); a blade tail (72) is fixedly arranged on the end of the blade (7) away from the blade seat (71); and a plurality of wheel grooves (61) are evenly arranged on the circumferential outer wall of the impeller (6); a docking auxiliary column group (23) is fixedly arranged in the middle of the assembly platform (2); and the preliminary positioning groove A (21) and the preliminary positioning groove B (22) are both arranged on the surface of the assembly platform (2).

7. The assembly equipment for aircraft engine rotary parts according to claim 6, characterized in that: The number of the blades (7) is consistent with the number of the blade positioning grooves; multiple groups of blades (7) are positioned on the assembly platform (2) through the blade positioning grooves; the impeller (6) is installed on the assembly platform (2) through a docking auxiliary column group (23); and the axial sections of the impeller (6), the blades (7) and the assembly platform (2) are concentric circle structures.

8. An assembly device for aircraft engine rotary parts according to any one of claims 6 or 7, characterized in that: The blade (7) is clamped in the interior of the initial groove B (22) through a blade tail (72) at one end, and the blade (7) is clamped in the interior of the initial groove A (21) through a blade seat (71) at the other end. The depths of the initial groove A (21) and the initial groove B (22) are consistent.

9. The assembly equipment for aircraft engine rotary parts according to claim 6, characterized in that: The wheel groove (61) is matched with the size of the impeller (71), and the impeller (71) is clamped inside the wheel groove (61). At the same time, a plurality of groups of mounting holes are evenly arranged on the wheel groove (61), and the impeller (71) is inserted into the wheel groove (61) and fixed by bolts.

10. The assembly equipment for aircraft engine rotating parts according to claim 6, characterized in that: The docking auxiliary column group (23) comprises five groups of positioning columns fixedly connected to the middle of the surface of the assembly platform (2), and the distribution positions of the five groups of positioning columns are consistent with the distribution positions of the middle of the impeller (6). At the same time, the impeller (6) is clamped on the surface of the assembly platform (2) through the docking auxiliary column group (23) and is positioned and installed with the blade (7).

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