Measuring device and measuring system for low-vortex rotor and stator assembly of aero-engine

Abstract

The utility model relates to the technical field of precise instruments, in particular to an aero-engine low-vortex rotor and stator assembly measuring device and measuring system. The measuring device comprises a measuring base, the measuring base is provided with a stator mounting seat and a rotor mounting seat, the stator mounting seat is used for mounting a stator casing, and the rotor mounting seat is used for mounting a rotor; the high-precision dense ball shaft system is arranged in the middle of the measuring base and comprises a torque motor, a main shaft, an axial support, a radial support and a shaft sleeve, the torque motor is connected with the main shaft, the axial support is arranged at one end of the main shaft, the radial support is arranged on the outer wall of the main shaft in a sleeving mode, and the shaft sleeve is arranged on the radial support in a sleeving mode; the measuring mechanism is arranged on the high-precision dense bead shaft system; and the lifting push rod device is arranged in the measuring base, and the lifting push rod device is suitable for being connected with the stator casing. Blade assembly and rotor and stator coaxiality measurement are unified, and the assembly efficiency and the assembly precision are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of precision instruments, in particular to an aircraft engine low-vortex stator assembly measuring device and a measuring system. Background Art

[0002] During the assembly of low-pressure turbine rotor blades of aircraft engines, it is necessary to repeatedly and accurately lift the stator casing to insert the blades into the tenon grooves of the blade disk, and at the same time strictly control the coaxiality of the rotor and stator. Due to the large weight and high coaxiality requirements of aircraft engine rotors and stators, it is difficult to simultaneously take into account large-mass, high-precision repeated axial movement and high-precision coaxial assembly in the assembly of low-pressure turbine blades.

[0003] In addition, operations such as inserting the blade disk into the blade disk groove and installing the lock piece bring impact, which requires the assembly tooling to have high rigidity and impact resistance. However, the current split assembly of the low-pressure turbine of the aircraft engine cannot meet the requirements of high-precision coaxiality, and the assembly efficiency is low and the precision is poor. Utility Model Content

[0004] Therefore, the technical problem to be solved by the utility model is to overcome the problem that the split assembly of the low-pressure turbine of an aircraft engine in the prior art cannot meet the requirements of high-precision coaxiality, and has low assembly efficiency and poor accuracy, thereby providing an aircraft engine low-turbulence stator assembly measurement device and measurement system.

[0005] In order to solve the above technical problems, the utility model provides an aircraft engine low-turbulence stator assembly measuring device, comprising: a measuring base, on which a stator mounting seat and a rotor mounting seat are provided, the stator mounting seat is used to install the stator casing, and the rotor mounting seat is used to install the rotor; a high-precision bead-threaded shaft system, arranged in the middle of the measuring base, the high-precision bead-threaded shaft system comprises a torque motor and a main shaft, an axial support, a radial support, and a bushing, the torque motor is connected to the main shaft, the axial support is arranged at one end of the main shaft, the radial support sleeve is arranged on the outer wall of the main shaft, and the bushing is sleeved on the radial support; a measuring mechanism, arranged on the high-precision bead-threaded shaft system; a lifting push rod device, arranged in the measuring base, and the lifting push rod device is suitable for connecting with the stator casing.

[0006] Furthermore, the measuring mechanism includes a measuring rotating shaft and a stator measuring piece, a rotor measuring piece, a stator inductance displacement sensor, and a rotor inductance position sensor; the measuring rotating shaft is arranged on the high-precision bead-series shaft system, the stator measuring piece and the rotor measuring piece are arranged on the measuring rotating shaft, the stator inductance displacement sensor is arranged on the stator measuring piece, and the rotor inductance displacement sensor is arranged on the rotor measuring piece.

[0007] Furthermore, the stator measuring part includes a stator measuring cross arm, a stator universal joint frame, and a locking part. The stator universal joint frame is arranged on the stator measuring cross arm. The locking part is used to lock the stator measuring cross arm and the measuring rotating axis. The stator inductive displacement sensor is arranged on the stator universal joint frame.

[0008] Furthermore, the rotor measuring component comprises a rotor measuring bracket and a rotor universal joint meter bracket, the rotor universal joint meter bracket is arranged on the rotor measuring bracket, and the rotor inductive displacement sensor is arranged on the rotor universal joint meter bracket.

[0009] Furthermore, there are a plurality of lifting push rod devices, and the plurality of lifting push rod devices are arranged at intervals along the measuring base.

[0010] Furthermore, the lifting push rod device includes a servo motor and a worm gear mechanism, a lifting guide column, and a limit switch. The servo motor is connected to the worm gear mechanism, and the lifting guide column is connected to the worm gear mechanism and the limit switch.

[0011] Furthermore, a plurality of stator positioning blocks and stator limiting pressure plates are provided on the stator mounting seat, the lifting push rod device is connected to the stator positioning block, and the stator limiting pressure plate is provided on the stator positioning block.

[0012] Furthermore, a rotor positioning ring and a rotor locking mechanism are provided on the rotor mounting seat, and the rotor locking mechanism is provided on the rotor positioning ring.

[0013] Furthermore, the measuring base includes: a cast iron base, the stator mounting seat and the rotor mounting seat are arranged on the cast iron base, the cast iron base is provided with a mounting hole, and the lifting push rod device is arranged in the mounting hole; an adjustable foot is arranged at the bottom of the cast iron base.

[0014] The utility model also provides an aircraft engine low vortex stator assembly measurement system, comprising an aircraft engine low vortex stator assembly measurement device.

[0015] The technical solution of the utility model has the following advantages:

[0016] The utility model provides an aircraft engine low-turbulence stator assembly measuring device, comprising: a measuring base, wherein a stator mounting seat and a rotor mounting seat are provided on the measuring base, wherein the stator mounting seat is used to mount a stator casing, and the rotor mounting seat is used to mount a rotor; a high-precision bead-threaded shaft system, which is arranged in the middle of the measuring base, wherein the high-precision bead-threaded shaft system comprises a torque motor and a main shaft, an axial support, a radial support, and a shaft sleeve, wherein the torque motor is connected to the main shaft, the axial support is arranged at one end of the main shaft, the radial support sleeve is arranged on the outer wall of the main shaft, and the shaft sleeve is sleeved on the radial support; a measuring mechanism, which is arranged on the high-precision bead-threaded shaft system; a lifting push rod device, which is arranged in the measuring base, and the lifting push rod device is suitable for being connected to the stator casing.

[0017] By setting up the measuring base, installation positions are provided for the stator mounting seat and the rotor mounting seat, as well as the high-precision bead-threaded shaft system; at the same time, the high-precision bead-threaded shaft system includes a torque motor and a main shaft, an axial support, a radial support, and a sleeve. The main shaft is matched with the sleeve through the radial support and the axial support, and the main shaft is connected to the torque motor to realize the electrical control rotation of the main shaft. A measuring mechanism is set on the high-precision bead-threaded shaft system, and the measuring mechanism can be used to measure the runout value of the stator casing and the rotor, as well as the rotation reference of the coaxiality.

[0018] Among them, the axial support, main shaft, and shaft sleeve form a rotating pair to provide a reference for measuring the axial rotation; the radial support main shaft and shaft sleeve form a rotating pair to provide a reference for measuring the radial rotation.

[0019] The low-turbulence stator assembly measuring device for aircraft engines can achieve high-precision axial and radial positioning and fixed installation of the rotor and stator casing. The lifting push rod device drives the stator casing to move axially to achieve high-precision reciprocating motion. The high-precision bead-filled shaft system and measuring mechanism measure the coaxiality of the rotor in real time during assembly, and the measuring base provides a stable support for the measurement assembly.

[0020] It solves the problem of not being able to simultaneously take into account high-precision repeated axial motion and high-precision coaxiality assembly during the assembly of low-pressure turbine rotor blades in aircraft engines, unifies blade assembly and rotor-stator coaxiality measurement, and improves assembly efficiency and assembly accuracy. It is suitable for scenes such as rotor-stator assembly in turbine machinery such as aircraft engines, gas turbines, and ship engines, and improves assembly accuracy and assembly efficiency.

[0021] The utility model summary is provided to introduce a selection of concepts in a simplified form, which will be further described in the following detailed description. The utility model summary is not intended to identify key features or essential features of the present disclosure, nor is it intended to limit the scope of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 A schematic diagram of the structure of the low-vortex stator assembly measuring device for an aircraft engine provided by the utility model;

[0024] Figure 2 A schematic diagram of the structure of a measuring base of a low-turbulence stator assembly measuring device for an aircraft engine provided by the utility model;

[0025] Figure 3 A schematic diagram of the structure of a high-precision bead-filled shaft system of an aircraft engine low-turbulence stator assembly measurement device provided by the utility model;

[0026] Figure 4 A structural schematic diagram of a lifting push rod device of an aircraft engine low-turbulence stator assembly measuring device provided by the utility model;

[0027] Figure 5 The utility model provides a schematic diagram of the structure of the measuring mechanism of the low-turbulence stator assembly measuring device for an aircraft engine.

[0028] Description of reference numerals:

[0029] 1. Measuring base; 2. Measuring mechanism; 3. High-precision bead-filled shaft system; 4. Stator mounting seat; 41. Rotor mounting seat; 5. Lifting push rod device; 6. Axial support; 7. Radial support; 8. Bushing; 9. Spindle; 10. Torque motor; 11. Servo motor; 12. Limit switch; 13. Worm gear mechanism; 14. Stator limit pressure plate; 15. Rotor locking mechanism; 16. Lifting ring; 17. Stator positioning block; 18. Rotor positioning ring; 19. Cast iron base; 20. Adjustable foot; 21. Stator inductance displacement sensor; 22. Stator universal joint frame; 23. Locking piece; 24. Stator measurement cross arm; 25. Measuring rotary shaft; 26. Connecting flange; 27. Rotor inductance displacement sensor; 28. Rotor measurement bracket; 29. ​​Rotor universal joint frame; 30. Mounting hole; 31. Lifting guide column. DETAILED DESCRIPTION

[0030] In the following, only some exemplary embodiments are briefly described. As those skilled in the art will appreciate, the described embodiments may be modified in various ways without departing from the spirit or scope of the present disclosure. Therefore, the drawings and descriptions are considered to be exemplary and non-restrictive in nature.

[0031] In the description of the present disclosure, 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 positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the present disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present disclosure. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present disclosure, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0032] In the description of the present disclosure, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or can communicate with each other; it can be directly connected, or indirectly connected through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present disclosure can be understood according to specific circumstances.

[0033] In the present disclosure, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply means that the first feature is lower in level than the second feature.

[0034] The disclosure below provides many different embodiments or examples to realize different structures of the present disclosure. In order to simplify the disclosure of the present disclosure, the parts and settings of specific examples are described below. Of course, they are only examples, and the purpose is not to limit the present disclosure. In addition, the present disclosure can repeat reference numbers and / or reference letters in different examples, and this repetition is for the purpose of simplicity and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present disclosure provides various specific examples of processes and materials, but those of ordinary skill in the art can be aware of the application of other processes and / or the use of other materials.

[0035] The preferred embodiments of the present disclosure are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present disclosure, and are not used to limit the present disclosure.

[0036] See also Figures 1 to 5 As shown, the utility model provides an aircraft engine low-turbulence stator assembly measuring device, comprising: a measuring base 1, on which a stator mounting seat 4 and a rotor mounting seat 41 are provided, the stator mounting seat 4 is used to install the stator casing, and the rotor mounting seat 41 is used to install the rotor; a high-precision dense bead shaft system 3, arranged in the middle of the measuring base 1, the high-precision dense bead shaft system 3 comprises a torque motor 10 and a main shaft 9, an axial support 6, a radial support 7, and a sleeve 8, the torque motor 10 is connected to the main shaft 9, the axial support 6 is arranged at one end of the main shaft 9, the radial support 7 is sleeved on the outer wall of the main shaft 9, and the sleeve 8 is sleeved on the radial support 7; a measuring mechanism 2, arranged on the high-precision dense bead shaft system 3; a lifting push rod device 5, arranged in the measuring base 1, and the lifting push rod device 5 is suitable for connecting with the stator casing.

[0037] By setting the measuring base 1, a mounting position is provided for the stator mounting seat 4 and the rotor mounting seat 41, as well as the high-precision bead-threaded shaft system 3; at the same time, the high-precision bead-threaded shaft system 3 includes a torque motor 10 and a main shaft 9, an axial support 6, a radial support 7, and a sleeve 8. The main shaft 9 is matched with the sleeve 8 through the radial support 7 and the axial support 6, and the main shaft 9 is connected to the torque motor 10 to realize the electrical control rotation of the main shaft 9. A measuring mechanism 2 is set on the high-precision bead-threaded shaft system 3, and the measuring mechanism 2 can be used to measure the runout value of the stator casing and the rotor, as well as the rotation reference of the coaxiality.

[0038] Among them, the axial support 6, the main shaft 9, and the sleeve 8 form a rotating pair to provide a reference for measuring the axial rotation; the radial support 7, the main shaft 9, and the sleeve 8 form a rotating pair to provide a reference for measuring the radial rotation.

[0039] The low-turbulence stator assembly and measurement device for aircraft engines can realize high-precision axial and radial positioning and fixed installation of the rotor and the stator casing. The lifting push rod device 5 drives the stator casing to move axially to achieve high-precision reciprocating motion. The high-precision bead shaft system 3 and the measuring mechanism 2 measure the coaxiality of the rotor in real time during assembly, and the measuring base 1 provides a stable support for the measurement assembly.

[0040] It solves the problem of not being able to simultaneously take into account high-precision repeated axial motion and high-precision coaxiality assembly during the assembly of low-pressure turbine rotor blades in aircraft engines, unifies blade assembly and rotor-stator coaxiality measurement, and improves assembly efficiency and assembly accuracy. It is suitable for scenes such as rotor-stator assembly in turbine machinery such as aircraft engines, gas turbines, and ship engines, and improves assembly accuracy and assembly efficiency.

[0041] In some optional embodiments, the measuring mechanism 2 includes a measuring rotating shaft 25 and a stator measuring piece, a rotor measuring piece, a stator inductance displacement sensor 21, and a rotor inductance position sensor; the measuring rotating shaft 25 is arranged on the high-precision dense bead shaft system 3, the stator measuring piece and the rotor measuring piece are arranged on the measuring rotating shaft 25, the stator inductance displacement sensor 21 is arranged on the stator measuring piece, and the rotor inductance displacement sensor 27 is arranged on the rotor measuring piece.

[0042] The measuring mechanism 2 is used to measure the coaxiality between the rotor and the stator, wherein the stator measuring piece and the rotor measuring piece are arranged on the measuring rotating shaft 25, and the stator inductive displacement sensor 21 and the stator measuring piece are used to measure the runout of the stator casing; the rotor inductive displacement sensor 27 and the rotor measuring piece are used to measure the runout of the rotor.

[0043] The measuring rotary shaft 25 is connected to the upper end of the high-precision bead-threaded shaft system 3 via a connecting flange 26 .

[0044] Specifically, the stator measuring part includes a stator measuring cross arm 24, a stator universal joint frame 22, and a locking piece 23. The stator universal joint frame 22 is arranged on the stator measuring cross arm 24. The locking piece 23 is used to lock the stator measuring cross arm 24 and the measuring rotating shaft 25. The stator inductive displacement sensor 21 is arranged on the stator universal joint frame 22.

[0045] The stator measuring cross arm 24 is connected to the measuring rotary shaft 25 through the locking piece 23, and the setting position of the stator measuring cross arm 24 is locked by the locking piece 23. Then the position of the stator inductance displacement sensor 21 is adjusted by using the stator universal joint table frame 22, and the stator center is fitted by the least square method.

[0046] The rotor measuring component includes a rotor measuring bracket 28 and a rotor universal joint meter bracket 29 . The rotor universal joint meter bracket 29 is arranged on the rotor measuring bracket 28 , and the rotor inductive displacement sensor 27 is arranged on the rotor universal joint meter bracket 29 .

[0047] The rotor measuring bracket 28 is connected to the measuring rotary shaft 25, and the position of the rotor inductive displacement sensor 27 is adjusted by using the rotor universal joint table bracket 29. The difference between the rotor center, the stator center and the rotor center in the same coordinate system, that is, the coaxiality deviation, is fitted by the least squares method.

[0048] In some optional embodiments, there are multiple lifting push rod devices 5, and the multiple lifting push rod devices 5 are arranged at intervals along the measuring base 1.

[0049] There are three lifting push rod devices 5 , and two adjacent lifting push rod devices 5 are assembled on the measuring base 1 at a circumferential interval of 120°.

[0050] In this embodiment, the lifting push rod device 5 includes a servo motor 11 and a worm gear mechanism 13, a lifting guide column 31, and a limit switch 12. The servo motor 11 is connected to the worm gear mechanism 13, and the lifting guide column 31 is connected to the worm gear mechanism 13 and the limit switch 12.

[0051] The servo motor 11 drives the worm gear mechanism 13 to rotate, thereby realizing precise electric control of the height difference between the stator casing and the rotor; the worm gear mechanism 13 drives the lifting guide column 31 to perform lifting movement, and the limit switch 12 is connected to the lifting guide column 31, and the limit switch 12 plays a role in protecting the lifting stroke of the lifting guide column 31.

[0052] In some optional embodiments, the stator mounting seat 4 is provided with a plurality of stator positioning blocks 17 and a stator limiting pressure plate 14 , the lifting push rod device 5 is connected to the stator positioning block 17 , and the stator limiting pressure plate 14 is provided on the stator positioning block 17 .

[0053] A stator casing is arranged on the stator positioning block 17, and axial positioning and locking are achieved through the stator limit pressure plate 14. The rotor positioning ring 18 and the stator positioning block 17 can be replaced according to different stop sizes.

[0054] The rotor mounting seat 41 is provided with a rotor positioning ring 18 and a rotor locking mechanism 15 , and the rotor locking mechanism 15 is provided on the rotor positioning ring 18 .

[0055] The axial positioning and locking of the rotor positioning ring 18 is achieved by the rotor locking mechanism 15 , and the rotor positioning ring 18 and the stator positioning block 17 can be replaced according to different stop sizes.

[0056] In some optional embodiments, the measuring base 1 includes: a cast iron base 19, the stator mounting seat 4 and the rotor mounting seat 41 are arranged on the cast iron base 19, the cast iron base 19 is provided with a mounting hole 30, and the lifting push rod device 5 is arranged in the mounting hole 30; an adjustable foot 20 is arranged at the bottom of the cast iron base 19.

[0057] By arranging the stator mounting seat 4 and the rotor mounting seat 41 on the cast iron base 19, installation positions are provided for the stator mounting seat 4 and the rotor mounting seat 41. At the same time, a mounting hole 30 is arranged on the cast iron base 19, and the lifting push rod device 5 can be placed in the mounting hole 30, so as to facilitate the connection between the lifting push rod device 5 and the stator positioning block 17. An adjustable foot 20 is arranged at the bottom of the cast iron base 19, so as to realize the support of the cast iron base 19.

[0058] At the same time, a lifting ring 16 is also provided on the cast iron base 19, and the lifting ring 16 can be used to drive the cast iron base 19 to move, thereby increasing the portability of the aircraft engine low-turbulence stator assembly measurement system.

[0059] The utility model also provides an aircraft engine low vortex stator assembly measurement system, comprising the aircraft engine low vortex stator assembly measurement device.

[0060] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention of the utility model.

Claims

1. An aircraft engine low turbulence stator assembly measurement device, characterized in that: include: A measuring base (1), wherein a stator mounting seat (4) and a rotor mounting seat (41) are provided on the measuring base (1), wherein the stator mounting seat (4) is used for mounting a stator casing, and the rotor mounting seat (41) is used for mounting a rotor; A high-precision bead-threaded shaft system (3) is arranged in the middle of the measuring base (1), and the high-precision bead-threaded shaft system (3) comprises a torque motor (10) and a main shaft (9), an axial support (6), a radial support (7), and a shaft sleeve (8), wherein the torque motor (10) is connected to the main shaft (9), the axial support (6) is arranged at one end of the main shaft (9), the radial support (7) is sleeved on the outer wall of the main shaft (9), and the shaft sleeve (8) is sleeved on the radial support (7); A measuring mechanism (2) is arranged on the high-precision bead-type shaft system (3); A lifting push rod device (5) is arranged in the measuring base (1), and the lifting push rod device (5) is suitable for connecting with the stator casing.

2. The aircraft engine low turbulence stator assembly measuring device according to claim 1, characterized in that: The measuring mechanism (2) comprises a measuring rotary shaft (25) and a stator measuring piece, a rotor measuring piece, a stator inductive displacement sensor (21), and a rotor inductive displacement sensor; the measuring rotary shaft (25) is arranged on the high-precision bead-type shaft system (3), the stator measuring piece and the rotor measuring piece are arranged on the measuring rotary shaft (25), the stator inductive displacement sensor (21) is arranged on the stator measuring piece, and the rotor inductive displacement sensor (27) is arranged on the rotor measuring piece.

3. The aircraft engine low turbulence stator assembly measuring device according to claim 2, characterized in that: The stator measuring component comprises a stator measuring cross arm (24), a stator universal joint meter frame (22), and a locking component (23); the stator universal joint meter frame (22) is arranged on the stator measuring cross arm (24); the locking component (23) is used to lock the stator measuring cross arm (24) and the measuring rotary shaft (25); and the stator inductive displacement sensor (21) is arranged on the stator universal joint meter frame (22).

4. The aircraft engine low turbulence stator assembly measuring device according to claim 2, characterized in that: The rotor measuring component comprises a rotor measuring bracket (28) and a rotor universal joint meter bracket (29); the rotor universal joint meter bracket (29) is arranged on the rotor measuring bracket (28); and the rotor inductive displacement sensor (27) is arranged on the rotor universal joint meter bracket (29).

5. The low-turbulence stator assembly measuring device for an aircraft engine according to any one of claims 1 to 4, characterized in that: The lifting push rod device (5) comprises a plurality of lifting push rod devices (5), and the plurality of lifting push rod devices (5) are arranged at intervals along the measuring base (1).

6. The aircraft engine low turbulence stator assembly measuring device according to claim 5, characterized in that: The lifting push rod device (5) comprises a servo motor (11) and a worm gear mechanism (13), a lifting guide column (31), and a limit switch (12); the servo motor (11) is connected to the worm gear mechanism (13); and the lifting guide column (31) is connected to the worm gear mechanism (13) and the limit switch (12).

7. The aircraft engine low turbulence stator assembly measuring device according to claim 6, characterized in that: A plurality of stator positioning blocks (17) and a stator limiting pressure plate (14) are provided on the stator mounting seat (4), the lifting push rod device (5) is connected to the stator positioning block (17), and the stator limiting pressure plate (14) is provided on the stator positioning block (17).

8. The aircraft engine low turbulence stator assembly measuring device according to claim 7, characterized in that: The rotor mounting seat (41) is provided with a rotor positioning ring (18) and a rotor locking mechanism (15), and the rotor locking mechanism (15) is provided on the rotor positioning ring (18).

9. The aircraft engine low turbulence stator assembly measurement device according to claim 1, characterized in that: The measuring base (1) comprises: A cast iron base (19), the stator mounting seat (4) and the rotor mounting seat (41) are arranged on the cast iron base (19), the cast iron base (19) is provided with a mounting hole (30), and the lifting push rod device (5) is arranged in the mounting hole (30); An adjustable foot (20) is arranged at the bottom of the cast iron base (19).

10. An aircraft engine low-turbine stator assembly measurement system, characterized in that: The invention comprises the aircraft engine low-spindle stator assembly measuring device according to any one of claims 1 to 9.

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