CN218411100U

CN218411100U - Aeroengine rotor measuring device that beats

Info

Publication number: CN218411100U
Application number: CN202222521546.4U
Authority: CN
Inventors: 张瑞杰; 韩晓娇; 何应杰; 路德双; 柳小洁; 张伟东
Original assignee: Tianjin Zhongjing Micro Instrument Equipment Co ltd
Current assignee: Tianjin Zhongjing Micro Instrument Equipment Co ltd
Priority date: 2022-09-20
Filing date: 2022-09-20
Publication date: 2023-01-31
Anticipated expiration: 2032-09-20

Abstract

The utility model provides an aeroengine rotor measuring device that beats, supporting mechanism lower extreme sliding connection is to the platform upper end, supporting mechanism upper end roll connection is to the piece periphery that awaits measuring, and the fixed one end that connects to the connecting piece of the one end of piece that awaits measuring, the other end of connecting piece sets up the gas foot dish, the first end of gas foot dish sets up spherical groove, the one end gomphosis of ball screw to spherical inslot, ball screw's other end fixed connection is to supporting mechanism, the piece that awaits measuring loops through connecting piece and gas foot dish flexonics to rotary power, and rotary power periphery is through axial thrust mechanism sliding connection to platform upper end. An aeroengine rotor measuring device that beats, the mode that combines through software, hardware has realized the rotor high accuracy measurement of beating of big span twin-cylinder benchmark, has solved the difficult problem of twin-cylinder benchmark location, axial locking and error compensation.

Description

Aeroengine rotor measuring device that beats

Technical Field

The utility model belongs to engine rotor measures the field, especially relates to an aeroengine rotor measuring device that beats.

Background

The engine in the prior art is obvious in structural difference with the existing engine model, in the design concept, the assembly process needs to be taken as a key measure for controlling the quality of the engine, a large number of parameters need to be ensured in the assembly process, and particularly, the end jump and the column jump of the rotor need to be measured and adjusted on line in the rotor assembly process, so that the assembly quality of the rotor is ensured. When the aspect ratio formed by the rotation diameter and the axial length of the measured part of the engine rotor is close and the size of the positioning reference journal is only small, the ratio of the size of the positioning reference journal to the rotation diameter of the measured part even reaches 10:1, when a vertical measuring method is adopted, the installation of the rotor is extremely difficult when a double-cylindrical surface reference aligning with a large span is used, the shaft necks which can be clamped at the two ends of a measured piece are too small, the rotation is unstable, and the measured piece has the risk of damage, so the conventional measuring device is not suitable for measuring the rotor runout of the engine with the same model.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model aims at providing an aeroengine rotor measuring device that beats to but solve prior art measuring device surveyed a both ends centre gripping axle journal undersize, unstable during the gyration, surveyed the problem that has the risk of damage.

In order to achieve the above purpose, the technical scheme of the utility model is realized like this:

the utility model provides an aeroengine rotor measuring device that beats, which comprises a platform, supporting mechanism, axial thrust mechanism, air foot dish and measuring mechanism, supporting mechanism lower extreme sliding connection is to the platform upper end, the supporting mechanism upper end roll connection is to the piece periphery that awaits measuring, and the fixed one end cover of the piece that awaits measuring connects to the one end of connecting piece, the other end of connecting piece sets up the air foot dish, the first end of air foot dish sets up spherical groove, the one end gomphosis of spherical screw rod is to spherical inslot, the other end fixed connection of spherical screw rod is to supporting mechanism, the piece that awaits measuring loops through connecting piece and air foot dish flexonics to rotary power, and rotary power periphery is through axial thrust mechanism sliding connection to the platform upper end, the spherical screw rod does not interfere rotary power and drives the piece rotation that awaits measuring, rotary power and measuring mechanism signal connection to controller.

Furthermore, the rotary power is an air-floating rotary table, a through hole is formed in the middle of the air-floating rotary table, one end of the spherical screw penetrates through the through hole and then is fixedly connected to the axial thrust mechanism, a connecting seat is fixedly installed at one end of the air-floating rotary table, one end of the connecting rod is hinged to the connecting seat, the other end of the connecting rod is rotatably sleeved to the inner ring of the fisheye bearing, and the periphery of the fisheye bearing is fixedly connected to the periphery of the connecting piece.

Furthermore, an electromagnetic module is arranged on the axial thrust mechanism, the electromagnetic module is connected to the controller in a signal mode, the electromagnetic module is used for attracting the connecting piece in a magnetic mode, a plurality of first air blowing holes are uniformly distributed in the air foot disc, an air passage of the air foot disc is communicated to the compressor, the compressor provides compressed air for the first air blowing holes through the air passage, the compressed air forms first air buoyancy force for the connecting piece, and an air film can be formed between the air foot disc and the connecting piece due to the first air buoyancy force and the magnetic yoke suction force.

Further, axial thrust mechanism includes first slip table and slide rail, and electromagnetic module is installed respectively to first slip table upper end, and the one end installation rotary power of electromagnetic module, rotary power fixed connection is passed to the one end of spherical screw rod to electromagnetic module, and first slip table lower extreme is equipped with the spout, and in the peripheral sliding connection of slide rail to the spout, and slide rail downside fixed connection to platform upper end, slide rail upside along axial equipartition second gas hole, and the second gas hole communicates to the compressor through the gas circuit, and the compressor provides compressed air to the second gas hole through the gas circuit, compressed air forms the second air buoyancy to first slip table, first slip table gravity can be overcome to second air buoyancy makes first slip table suspend.

Further, supporting mechanism's quantity is two, and two supporting mechanism parallel arrangement each other, and every supporting mechanism includes first Y to supporting, second slip table and follow-up shaft, and first Y is to supporting the lower extreme and passing through second slip table sliding connection to platform upper end, and first Y is to supporting the upper end and rotating and cup jointing the follow-up shaft, and the quantity of follow-up shaft is two, two follow-up shaft parallel arrangement each other, and the equal roll connection in periphery of every follow-up shaft is to the periphery of awaiting measuring, and first Y can drive awaiting measuring Y to go up and down to supporting.

Further, measuring mechanism's quantity is two, two measuring mechanism parallel arrangement each other, and every measuring mechanism all is located one side of awaiting measuring the piece, measuring mechanism includes second Y to supporting, the third slip table, the fourth slip table, support arm and micro displacement sensor, second Y passes through third slip table sliding connection to platform upper end to supporting the lower extreme, one side sliding connection of third slip table to one side of fourth slip table, the support arm is installed to the one end of fourth slip table, and the micro displacement sensor is installed to the one end of support arm, micro displacement sensor signal connection to controller, micro displacement sensor is used for detecting the peripheral relative position of piece that awaits measuring, the fourth slip table can be gone up and down along Y on the third slip table, and the fourth slip table can drive the support arm and slide along Z, the support arm can adjust the peripheral angle of micro displacement sensor relatively awaiting measuring.

Compared with the prior art, an aeroengine rotor measuring device that beats have following beneficial effect: the part to be measured is connected to the rotating power through the connecting piece and the air foot disc in a flexible mode, the air foot disc is connected to the supporting mechanism through the spherical screw rod, the angle of the air foot disc can be changed, high-precision measurement of rotor jumping of the large-span double-cylindrical-surface reference is achieved through a software and hardware combination mode, and the problems of double-cylindrical-surface reference positioning, axial stopping and error compensation are solved.

Drawings

The accompanying drawings, which form a part hereof, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without undue limitation. In the drawings:

fig. 1 is a schematic structural diagram of an aircraft engine rotor runout measuring device according to an embodiment of the present invention;

fig. 2 is a schematic front view of an aircraft engine rotor runout measuring device according to an embodiment of the present invention;

fig. 3 is a schematic structural view of an axial thrust mechanism, a connecting member and a rotary power assembly according to an embodiment of the present invention;

fig. 4 is a schematic structural diagram of a supporting mechanism according to an embodiment of the present invention;

fig. 5 is a schematic structural diagram of a measuring mechanism according to an embodiment of the present invention.

Description of reference numerals:

1-a platform; 2-a support mechanism; 21-first Y-support; 22-a second ramp; 23-a follower shaft; 3-axial thrust mechanism; 31-an electromagnetic module; 32-a first slide; 33-a slide rail; 4-air foot plate; 5-a measuring mechanism; 51-second Y-direction support; 52-third slide table; 53-fourth ramp; 54-a support arm; 541-an arm; 542-two arms; 543-fastening bolt; 55-micro displacement sensor; 6-connecting piece; 7-a spherical screw; 8-rotational power; 81-a connecting seat; 82-a connecting rod; 83-fisheye bearing; 9-shock pad.

Detailed Description

It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, are not to be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate a number of the indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

As shown in fig. 1-5, an aircraft engine rotor runout measuring device comprises a platform 1, a supporting mechanism 2, an axial thrust mechanism 3, a gas-foot disk 4 and a measuring mechanism 5, wherein the lower end of the supporting mechanism 2 is slidably connected to the upper end of the platform 1, the upper end of the supporting mechanism 2 is connected to the periphery of a piece to be measured in a rolling manner, one end of the piece to be measured is fixedly sleeved and connected to one end of a connecting piece 6, the other end of the connecting piece 6 is provided with the gas-foot disk 4, the first end of the gas-foot disk 4 is provided with a spherical groove, one end of a spherical screw 7 is embedded into the spherical groove, the other end of the spherical screw 7 is fixedly connected to the supporting mechanism 2, the piece to be measured is flexibly connected to a rotating power 8 through the connecting piece 6 and the gas-foot disk 4 in turn, and the periphery of the rotating power 8 is slidably connected to the upper end of the platform 1 through the axial thrust mechanism 3, the spherical screw 7 does not interfere the rotating power 8 to drive the to-be-measured piece to rotate, the rotating power 8 and the measuring mechanism 5 are in signal connection with the controller, the control mode of the embodiment is controlled by the controller, a control circuit of the controller can be realized by simple programming of technicians in the field, the power supply also belongs to the common knowledge in the field, the control mode and the circuit connection are not explained in detail herein, the to-be-measured piece is flexibly connected to the rotating power 8 through the connecting piece 6 and the air foot disc 4 in sequence, the air foot disc 4 is connected to the supporting mechanism 2 through the spherical screw 7 with the angle changeable, the large-span double-cylindrical-surface-based rotor runout high-precision measurement is realized through the combination of software and hardware, and the problems of double-cylindrical-surface reference positioning, axial stopping and error compensation are solved.

The rotary power 8 is an air-floating rotary table in the prior art, a through hole is arranged in the middle of the air-floating rotary table, one end of the spherical screw 7 penetrates through the through hole and then is fixedly connected to the axial thrust mechanism 3, a connecting seat 81 is fixedly installed at one end of the air-floating rotary table, one end of a connecting rod 82 is hinged to the connecting seat 81, the other end of the connecting rod 82 is rotatably sleeved to the inner ring of a fisheye bearing 83, and the periphery of the fisheye bearing 83 is fixedly connected to the periphery of the connecting piece 6.

As shown in fig. 3, an electromagnetic module 31 is arranged on the axial thrust mechanism 3, and the electromagnetic module 31 is in the prior art, the electromagnetic module 31 is in signal connection with the controller, the electromagnetic module 31 is used for magnetically attracting the connecting piece 6, a plurality of first air blowing holes are uniformly distributed on the air foot disc 4, an air passage of the air foot disc 4 is communicated to the compressor, the compressor provides compressed air to the first air blowing holes through the air passage, the compressed air forms a first air buoyancy force for the connecting piece 6, and the air film can be formed between the air foot disc 4 and the connecting piece 6 due to the first air buoyancy force and the magnetic yoke attraction force.

The axial thrust mechanism 3 comprises a first sliding table 32 and a sliding rail 33, an electromagnetic module 31 is respectively installed at the upper end of the first sliding table 32, a rotary power 8 is installed at one end of the electromagnetic module 31, one end of a spherical screw 7 penetrates through the rotary power 8 and is fixedly connected to the electromagnetic module 31, a sliding groove is formed in the lower end of the first sliding table 32, the periphery of the sliding rail 33 is slidably connected to the sliding groove, the lower side of the sliding rail 33 is fixedly connected to the upper end of the platform 1, second air blowing holes are uniformly distributed in the upper side of the sliding rail 33 along the axial direction, the second air blowing holes are communicated to a compressor through an air passage, the compressor provides compressed air for the second air blowing holes through the air passage, the compressed air forms second air buoyancy to the first sliding table 32, and a permanent magnet is installed between the first sliding table 32 and the sliding rail 33, so that magnetic attraction exists between the first sliding table 32 and the sliding rail 33, and the second air buoyancy can overcome the gravity and the magnetic attraction of the first sliding table 32 to suspend the first sliding table 32 so that the sliding rail can slide without friction.

As shown in fig. 1, the number of the supporting mechanisms 2 is two, and the two supporting mechanisms 2 are arranged in parallel, the two supporting mechanisms 2 can slide on the platform 1 along the X direction for adapting to the pieces to be tested with different specifications, each supporting mechanism 2 comprises a first Y-direction support 21, a second sliding table 22 and a follower shaft 23, the lower end of the first Y-direction support 21 is connected to the upper end of the platform 1 in a sliding manner through the second sliding table 22, the upper end of the first Y-direction support 21 is rotatably sleeved with the follower shaft 23, the number of the follower shafts 23 is two, the two follower shafts 23 are arranged in parallel, the periphery of each follower shaft 23 is connected to the periphery of the piece to be tested in a rolling manner, as shown in fig. 4, first Y is to supporting 21 including first extension board, the second extension board, first slide rail 33, first slider and promote the motor, first extension board lower extreme fixed connection is to 1 upper end of platform, first extension board one side sets up first slide rail 33, one side of second extension board is peripheral through first slider sliding connection to first slide rail 33, and second extension board lower extreme fixed connection promotes the movable rod of motor, and it is the push rod motor of prior art to promote the motor, follow-up shaft 23 is installed to the upper end of second extension board, it can promote second extension board and follow-up shaft 23 along Y in proper order to promote the motor, first Y is to supporting 21 can driving the Y of awaiting measuring to go up and down promptly, it is connected to the controller to promote motor signal.

The quantity of measuring mechanism 5 is two, two measuring mechanism 5 are parallel to each other, and every measuring mechanism 5 all is located one side of the piece that awaits measuring, measuring mechanism 5 includes that the second Y supports 51, third slip table 52, fourth slip table 53, support arm 54 and micro displacement sensor 55, the second Y supports 51 lower extreme and passes through third slip table 52 sliding connection to platform 1 upper end to the support, third slip table 52 one side sliding connection to one side of fourth slip table 53, support arm 54 is installed to the one end of fourth slip table 53, and the one end of support arm 54 installs micro displacement sensor 55, micro displacement sensor 55 signal connection to controller, micro displacement sensor 55 is used for detecting the peripheral relative position of the piece that awaits measuring, third slip table 52 and fourth slip table 53 are the push rod or the rodless cylinder of prior art, and all set up electromagnetic switch on third slip table 52 and the fourth slip table 53, electromagnetic switch signal connection to the controller, fourth slip table 53 can go up and down along the Y on third slip table 52, and fourth slip table 53 can drive support arm 54 along the Z to the slip, the peripheral angle that the relative micro displacement sensor 55 that awaits measuring can adjust.

The support arm 54 includes an arm 541, two arms 542 and fastening bolt 543, one end fixed connection to one side of fourth slip table 53 of an arm 541, the other end of an arm 541 is equipped with first screw hole, the one end installation micro-displacement sensor 55 of two arms 542, the other end of two arms 542 is equipped with the second screw hole, fastening bolt 543 threaded connection in proper order is in first screw hole, be used for the relative position of fixed an arm 541 and two arms 542 in the second screw hole, micro-displacement sensor 55 can adjust the relative angle and the distance with the piece that awaits measuring promptly through two arms 542.

When implementing as shown in fig. 2, platform 1 lower extreme sets up shock pad 9, and shock pad 9 has multiple implementation mode, and this embodiment is height-adjustable's lower extreme, and lower extreme of lower margin sets up buffering bubble cotton or rubber.

The working process of the aircraft engine rotor runout measuring device comprises the following steps:

(1) According to the axial span of the two measuring references of the rotor to be detected, a worker preliminarily adjusts the relative span of the two measuring mechanisms 5 and the supporting mechanism 2 and locks the relative span to meet the supporting span requirement of the measured piece;

(2) Setting a height adjusting value according to the size of a shaft neck at a reference position of a rotor to be detected, adjusting Y-direction support through supporting height, and controlling a push rod motor to automatically adjust the center height and lock through a controller so as to meet the supporting concentricity of a detected piece;

(3) A connecting piece 6 for mounting the end part of the tested piece;

(4) Mounting the tested piece and the connecting piece 6 to corresponding positions of the platform 1, and respectively supporting the benchmarks on the periphery of a rotating shaft at the upper end of a first Y-direction support 21;

(5) Moving the axial thrust mechanism 3 towards the center direction of the platform 1 until the air foot is attached to the end face of the connecting piece 6;

(6) The air is introduced into the air foot disc 4 through a compressor, and an air film is formed between the air foot disc 4 and the connecting piece 6 through the combined action of air floatation and a magnetic yoke, so that axial stopping is realized;

(7) Marking zero positions of the two reference positions and adjusting the two reference end measuring sensors to press the meter;

(8) Adjusting a supporting arm 54 on the measuring mechanism 5 to enable a micro-displacement sensor 55 to approach a measured position, and finely adjusting the sensor and the pressure gauge;

(9) Rotating the measured piece to rotate the measured piece to complete the jump measurement of the position;

(10) And repeating the steps 8-9 to finish the measurement of the runout of the rest positions of the measured piece.

The measuring device realizes supporting and rotation through the mode of the rotating shaft and the roller of the piece to be measured, the concentricity of two supporting ends is ensured through installation and adjustment of workers, the supporting span is ensured through adjusting the axial distance of the movable supporting end when the reference supporting span of different pieces to be measured is different, and the axial movement realization mode of the movable supporting end is a high-precision air floatation linear guide rail. The motion adjustment on the height of the supporting end is determined by a precise lead screw, the motor output drives the lead screw to move after speed reduction and force increase, and pushes the supporting sliding plate to move up and down, wherein the control of the adjustment precision is realized by absolute value linear gratings in a closed loop feedback mode, the adjustment capacity can reach micron level, the support is a double-cylinder support, two groups of support heights can be independently adjusted, the support is suitable for supporting shaft diameters of different sizes at two ends of a measured piece, the locking after adjustment is realized by a magnetic yoke method, no magnetic leakage exists, the reliability of the adjustment of the height of the supporting end is ensured, the locking of the axial position of the measured piece is realized by the structure shown in the figure 3 during end face jumping measurement, an air foot disk 4 is distributed between a connecting piece 6 and an electromagnet, meanwhile, a permanent magnet is arranged between the first sliding table 32 and the sliding rail 33, so that magnetic attraction exists between the first sliding table 32 and the sliding rail 33, the sliding rail 33 overcomes the magnetic yoke and the magnetic force through air blowing, the sliding rail 4 is in a friction-free air floatation state, therefore, the first sliding table 32 can conveniently drag the air foot disk 4 drives the end face of the air foot disk 4 to be attached to the end face of the connecting piece to the connecting piece, the axial air film, the axial air supply clearance is ensured, and the axial displacement of the air film is effectively measured, and the axial clearance is effectively limited, and the air film is also ensured, and the axial displacement of the air film is formed under the air supply.

The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an aeroengine rotor measuring device that beats which characterized in that: including platform (1), supporting mechanism (2), axial thrust mechanism (3), air foot dish (4) and measuring mechanism (5), supporting mechanism (2) lower extreme sliding connection is to platform (1) upper end, supporting mechanism (2) upper end rolling connection is to the piece periphery that awaits measuring, and the fixed one end cover of the piece that awaits measuring connects to the one end of connecting piece (6), the other end of connecting piece (6) sets up air foot dish (4), the first end of air foot dish (4) sets up spherical groove, the one end gomphosis of spherical screw rod (7) is to spherical inslot, the other end fixed connection of spherical screw rod (7) is to supporting mechanism (2), the piece that awaits measuring loops through connecting piece (6) and air foot dish (4) flexonics to rotary power (8), and rotary power (8) periphery is through axial thrust mechanism (3) sliding connection to platform (1) upper end, spherical screw rod (7) do not interfere rotary power (8) and drive the piece that awaits measuring and rotate, rotary power (8) and measuring mechanism (5) signal connection to controller.

2. An aircraft engine rotor runout measuring device according to claim 1, characterised in that: the rotary power (8) is an air-flotation rotary table, a through hole is formed in the middle of the air-flotation rotary table, one end of the spherical screw (7) penetrates through the through hole and then is fixedly connected to the axial thrust mechanism (3), a connecting seat (81) is fixedly installed at one end of the air-flotation rotary table, one end of a connecting rod (82) is hinged to the connecting seat (81), the other end of the connecting rod (82) is rotatably sleeved to an inner ring of a fisheye bearing (83), and the periphery of the fisheye bearing (83) is fixedly connected to the periphery of the connecting piece (6).

3. An aircraft engine rotor runout measuring device according to claim 1, characterised in that: the axial thrust mechanism (3) is provided with an electromagnetic module (31), the electromagnetic module (31) is in signal connection with the controller, the electromagnetic module (31) is used for magnetically attracting the connecting piece (6), a plurality of first air blowing holes are uniformly distributed in the air foot disc (4), an air path of the air foot disc (4) is communicated to the compressor, the compressor provides compressed air to the first air blowing holes through the air path, the compressed air forms first air buoyancy to the connecting piece (6), and the air film is formed between the air foot disc (4) and the connecting piece (6) due to the first air buoyancy and the magnetic yoke suction.

4. An aircraft engine rotor runout measuring device according to claim 3, characterised in that: axial thrust mechanism (3) are including first slip table (32) and slide rail (33), electromagnetic module (31) is installed respectively to first slip table (32) upper end, rotatory power (8) are installed to the one end of electromagnetic module (31), the one end of spherical screw rod (7) is passed rotatory power (8) fixed connection to electromagnetic module (31), first slip table (32) lower extreme is equipped with the spout, slide rail (33) periphery sliding connection is in the spout, and slide rail (33) downside fixed connection to platform (1) upper end, slide rail (33) upside is along axial equipartition second gas blow hole, second gas blow hole communicates to the compressor through the gas circuit, the compressor provides compressed air to second gas blow hole through the gas circuit, compressed air forms the second gas buoyancy to first slip table (32), first slip table (32) gravity can be overcome to second gas buoyancy makes first slip table (32) suspend.

5. An aircraft engine rotor runout measuring device according to claim 1, characterised in that: supporting mechanism (2) include first Y to supporting (21), second slip table (22) and follow-up axle (23), first Y is to supporting (21) lower extreme through second slip table (22) sliding connection to platform (1) upper end, first Y is to supporting (21) upper end rotation and cup jointing follow-up axle (23), and the quantity of follow-up axle (23) is two, two follow-up axle (23) parallel arrangement each other, the periphery of every follow-up axle (23) all roll connection to the periphery of awaiting measuring, and first Y can drive awaiting measuring Y to go up and down to supporting (21).

6. An aircraft engine rotor runout measuring device according to claim 1, characterised in that: measuring mechanism (5) all are located one side of awaiting measuring the piece, measuring mechanism (5) include that the second Y is to supporting (51), third slip table (52), fourth slip table (53), support arm (54) and micro displacement sensor (55), the second Y is to supporting (51) lower extreme through third slip table (52) sliding connection to platform (1) upper end, one side sliding connection of third slip table (52) to one side of fourth slip table (53), support arm (54) are installed to the one end of fourth slip table (53), and one end installation micro displacement sensor (55) of support arm (54), micro displacement sensor (55) signal connection is to the controller, micro displacement sensor (55) are used for detecting the peripheral relative position of piece that awaits measuring, fourth slip table (53) can go up and down along the Y on third slip table (52), and fourth slip table (53) can drive support arm (54) and slide along the Z, support arm (54) micro displacement sensor (55) can adjust the peripheral angle of the piece that awaits measuring relatively.