Aerial turbojet engine main shaft measuring device and use method thereof

Abstract

The invention belongs to the technical field of main shaft measurement, and discloses an aviation turbojet engine main shaft measuring device and a use method thereof. The measuring device for the main shaft of the aviation turbojet engine comprises a mounting rack, two annular plates are symmetrically and fixedly connected to the mounting rack, an annular plate is movably connected between the two annular plates, a plurality of measuring assemblies are uniformly distributed on the annular plate, and a detection rotating assembly is arranged on the mounting rack. The power output end of the detection rotating assembly is in transmission connection with the annular plate and used for driving the annular plate to rotate, a movable plate is movably connected to the inner bottom face of the mounting frame, and two main shaft locking assemblies are movably arranged on the top face of the movable plate. A transverse displacement assembly used for driving the movable plate to move horizontally and transversely is arranged on the inner bottom face of the mounting frame. According to the invention, the detection and measurement operation of the main shaft can be efficiently and accurately completed.

Description

Technical Field

[0001] The present invention belongs to the technical field of the main shaft measurement of an aero turbojet engine. Specifically, it relates to a measurement device for the main shaft of an aero turbojet engine and a method for using the same. Background Art

[0002] The main shaft of an aero turbojet engine is one of the core components of the engine. The accuracy of its main shaft directly affects the working performance, efficiency, and reliability of the engine. The main shaft has a complex three-dimensional structure (such as coaxiality, circular runout, surface integrity, etc.), and the materials are mostly difficult-to-machine materials such as superalloys and composite materials, which pose extremely high requirements for measurement technology.

[0003] Currently, most of the operations for measuring the main shaft of an aero turbojet engine in the prior art are realized by laser scanning. A laser emitter emits laser pulses towards the object to be measured. After the laser pulses hit the surface of the object, they are reflected back and received by the receiver. By measuring the time interval from the emission to the reception of the laser pulses and combining the speed of light, the distance between the surface points of the object to be measured and the measurement device is calculated. Laser scanning can quickly obtain the data of the main shaft, but affected by the reflection of the main shaft surface, material characteristics (such as coating roughness), and complex structures (such as deep grooves and edges), it is easy to generate data noise or missed measurements, which greatly limits the measurement accuracy.

[0004] The Chinese invention patent with the patent application number: CN202010743171.9 discloses a shaft part runout detection mechanism and a detection method for automatically eliminating the main shaft error, including two support mechanisms. The two support mechanisms are fixed to the machine base by screws, and a workpiece is placed on the two support mechanisms. The main and driven side clamping and driving components are respectively located on the left and right sides of the workpiece and fixed to the machine base. The main and driven side clamping and driving components are pushed out, and the workpiece is clamped at both ends by a rotating center tip, so that the workpiece is clamped and driven to rotate along its own axis; by pushing out the clamping cylinder, the rotating center tip is in contact with the clamped workpiece, and the servo motor drives the center tip to make the workpiece rotate around its axis. The runout detection mechanism is installed beside the workpiece, and the runout detection mechanism detects the surface runout of the workpiece when it rotates.

[0005] The above-mentioned existing detection mechanisms are suitable for detecting the circular runout of shaft parts, and cannot detect the outer surface dimensions of shaft parts and the outer surface defects at each cross-section, reducing the use effect. Moreover, the sizes of the main shafts of different models of aero turbojet engines are also different, and the existing measurement methods are very inconvenient for the measurement process of the main shaft, which will greatly reduce the measurement efficiency of the main shaft of the aero turbojet engine. And the existing measurement devices all require the main shaft to rotate at a high speed, resulting in a complex overall structure of the measurement device, high manufacturing cost, and single detection function, reducing the use effect. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a measuring device for the main shaft of an aero-turbojet engine and its usage method, which is used to solve the problems raised in the above-mentioned background technology, improve the measuring accuracy and efficiency of the main shaft of the aero-turbojet engine, and is applicable to the detection and measurement operations of the main shafts of various models and different detection items, thereby improving the usage effect.

[0007] To solve the above technical problems, the present invention provides the following technical solutions: A measuring device for the main shaft of an aero-turbojet engine includes a mounting frame. Two annular plates are symmetrically and fixedly connected to the mounting frame. A circular ring plate is movably connected between the two annular plates. A plurality of measuring components are evenly distributed on the circular ring plate. A detection rotation component is arranged on the mounting frame, and the power output end of the detection rotation component is in transmission connection with the circular ring plate to drive the circular ring plate to rotate. A movable plate is movably connected to the inner bottom surface of the mounting frame. Two main shaft locking components are movably arranged on the top surface of the movable plate. A horizontal displacement component for driving the movable plate to move horizontally is arranged on the inner bottom surface of the mounting frame.

[0008] The following is a further optimization of the above technical solutions by the present invention: The measuring component includes a fixed shell, which is fixedly connected to the circular ring plate. A distance sensor is installed on the side wall of the fixed shell away from the circular ring plate, and the detection end of the distance sensor extends into the fixed shell. A flat plate is movably arranged in the inner cavity of the fixed shell. A movable rod is fixedly connected to the side of the flat plate away from the distance sensor. The other end of the movable rod penetrates through the circular ring plate and is adjustably installed with an adjusting rod. The other end of the adjusting rod is fixedly connected to a circular shell, and a spherical ball is movably connected in the circular shell.

[0009] Further optimization: A spring is sleeved on the outer side wall of the movable rod. One end of the spring is fixedly connected to the circular ring plate, and the other end of the spring is fixedly connected to a side plate, which is fixedly connected to the outer wall of the movable rod.

[0010] Further optimization: The detection rotation component includes a first motor, which is fixedly installed on the mounting frame. The power output end of the first motor is in transmission connection with the outer side wall of the circular ring plate through a first transmission component.

[0011] Further optimization: The main shaft locking component includes a mounting plate, which is slidably installed on the movable plate. A vertical plate is fixedly connected to the top surface of the mounting plate, and a locking mechanism for locking and clamping the end of the main shaft of the aero-turbojet engine is fixedly installed on the top surface of the vertical plate.

[0012] Further optimization: A displacement adjustment mechanism is arranged between the mounting plate and the movable plate. When the displacement adjustment mechanism is activated, it is used to drive the mounting plate to slide on the movable plate, so as to drive the vertical plate and the locking mechanism to move and adjust the horizontal position.

[0013] Further optimization: the lateral displacement assembly includes a support plate, which is fixedly mounted on the inner bottom surface of the mounting frame, and a third motor is fixedly mounted on the top surface of the support plate. The power output end of the third motor is connected to the movable plate through the second transmission assembly. When the third motor is started, it drives the movable plate to move laterally through the second transmission assembly, thereby driving the locked and clamped main shaft of the aviation turbojet engine to move laterally.

[0014] Further optimization: annular grooves are provided on the two annular plates, and fixing rings are fixedly connected to both side surfaces of the annular plates, and the fixing rings are movably installed in the corresponding annular grooves.

[0015] Further optimization: an adjustment blind hole is opened in the end of the movable rod away from the flat plate, one end of the adjusting rod is movably assembled in the adjustment blind hole, a threaded hole is vertically opened on the outer wall of the movable rod, a clamping bolt is threadedly connected in the threaded hole, and one end of the clamping bolt is tightened against the outer wall of the adjusting rod.

[0016] The present invention also provides a method for using an aviation turbojet engine main shaft measuring device, based on the above-mentioned aviation turbojet engine main shaft measuring device, comprising the following steps: S1: The main shaft of the aviation turbojet engine is passed through the annular plate and the circular ring plate. At this time, the spherical ball at the detection end of the measuring component is pressed tightly against the outer wall of the main shaft of the aviation turbojet engine, and the placement operation of the main shaft of the aviation turbojet engine is completed; S2: according to the overall length of the spindle, the two spindle locking assemblies are started to move on the movable plate toward the side close to the mounting frame until the locking mechanisms on the two spindle locking assemblies contact the two ends of the spindle, and the two ends of the spindle are clamped by the locking mechanisms; S3: Start the lateral displacement component to drive the movable plate to move horizontally. The movement of the movable plate drives the fixed spindle to move horizontally, so as to switch the measuring position on the spindle. S4: Complete the communication connection between the distance sensor in the measuring component and the peripheral detection control device, record the data on the distance sensor as the initial position, start the detection rotation component to drive the annular plate to rotate, the annular plate drives the ball to move on the outer wall of the spindle, and ensures the real-time contact between the ball and the spindle under the action of the spring. When the outer wall of the spindle has a processing defect, the ball drives the adjustment rod, the movable rod and the plate to move synchronously, and the moving distance of the plate is detected and data collected in real time through the distance sensor. After the annular plate rotates one circle, the detection process and data collection process of the spindle on a cross section are completed; S5: Turn off the detection rotation component and reversely start the lateral displacement component to drive the movable plate to drive the spindle to move laterally, so as to switch the measurement position on the spindle, and repeat the S4 step to perform the detection process and data collection process on another cross section of the spindle, and record it as the second position; S6: Repeat the above steps S4 - S5 to perform multiple data acquisition operations on the spindle data until the sphere moves to the tangency position on the other side of the spindle, and record it as the Nth position; S7: Collect the data from the initial position to the Nth position collected, and based on the data collected by one of the distance sensors as a reference, process the data collected by the distance sensors in a clockwise direction according to the number of distance sensors, so that the data of the distance sensors at all positions are converted and matched with the data at the reference position, calculate the data under the same reference and output the average value, process the average value data through the control device and arrange it from the initial position to the Nth position, so as to obtain the measurement data of the spindle of the aero - turbojet engine.

[0017] The present invention adopts the above - mentioned technical solution, and has at least the following beneficial effects: 1. In the present invention, the measurement component and the detection rotation component cooperate to work. Under the action of the spring, it can ensure that the sphere is in real - time contact with the outer wall of the spindle. Driven by the first motor, the ring plate can rotate, and the ring plate drives the measurement component to move annularly. At this time, the movement of the sphere on the outer wall of the spindle can drive the movement of the movable rod, and the movable rod drives the movement of the flat plate. The distance sensor detects the moving distance of the flat plate in real - time, so as to efficiently and accurately complete the measurement operation of the spindle.

[0018] 2. In the present invention, the spindle locking component and the lateral displacement component cooperate to work. Adjust the position of the locking mechanism according to the model of the spindle, and then drive the mounting plate to move through the second motor in the two groups of spindle locking components, so that the locking mechanisms on both sides are butted against the two ends of the spindle and lock and clamp the spindle, thus realizing the positioning and placement of the spindle, facilitating stable measurement operations, improving measurement accuracy and versatility. And by driving the movable plate to move through the third motor in the lateral displacement component, the spindle can be moved laterally to adjust the lateral position of the spindle and realize the switching of the measurement positions on the spindle; furthermore, the detection process and data acquisition process can be carried out on multiple cross - sections of the spindle, improving measurement accuracy and detection efficiency.

[0019] The following further illustrates the present invention with reference to the drawings and embodiments. Description of the Drawings

[0020] Figure 1 It is a three - dimensional view of the overall structure of Embodiment 1 of the present invention; Figure 2 It is a three - dimensional view of the lateral cross - section of the overall structure in Embodiment 1 of the present invention; Figure 3 It is a three - dimensional structure schematic diagram at the position of the movable plate in Embodiment 1 of the present invention; Figure 4 It is Figure 3Partial enlarged view at position A in the [Chinese context]; Figure 5 Schematic three-dimensional structure diagram at the position of the circular ring plate in Embodiment 1 of the present invention; Figure 6 Schematic structure diagram of the main shaft locking assembly in Embodiment 1 of the present invention; Figure 7 Schematic structure diagram of the measuring assembly in Embodiment 1 of the present invention; Figure 8 Schematic structure diagram of the mounting bracket in Embodiment 1 of the present invention; Figure 9 Schematic structure diagram of the main shaft locking assembly in Embodiment 2 of the present invention; Figure 10 Schematic structure diagram of the lateral displacement assembly in Embodiment 3 of the present invention.

[0021] In the figure: 1 - mounting bracket; 2 - annular plate; 3 - circular ring plate; 4 - measuring assembly; 5 - detection rotation assembly; 6 - movable plate; 7 - main shaft locking assembly; 8 - lateral displacement assembly; 9 - fixed shell; 10 - distance sensor; 11 - flat plate; 12 - movable rod; 13 - adjusting rod; 14 - circular shell; 15 - spherical ball; 16 - spring; 17 - side plate; 18 - first motor; 19 - first rotating shaft; 20 - first gear; 21 - annular gear; 22 - mounting plate; 23 - vertical plate; 24 - circular plate; 25 - positioning hole; 26 - positioning screw; 27 - fixing plate; 28 - second gear; 29 - second rotating shaft; 30 - second motor; 31 - first rack; 32 - pressing bolt; 33 - third motor; 34 - third rotating shaft; 35 - third gear; 36 - second rack; 37 - annular groove; 38 - fixed ring; 39 - slider; 40 - chute; 41 - support plate; 42 - guide block; 43 - guide groove; 44 - sliding groove; 45 - driving lead screw; 46 - moving block; 47 - lead screw motor; 48 - connecting plate; 49 - moving lead screw; 50 - nut block; 51 - driving motor. Detailed implementation manners

[0022] Embodiment 1: As Figure 1-8 shown: An aviation turbojet engine main shaft measuring device includes a mounting bracket 1. Two annular plates 2 are symmetrically and fixedly connected to the mounting bracket 1. A circular ring plate 3 is movably connected between the two annular plates 2. A plurality of measuring assemblies 4 are evenly distributed on the circular ring plate 3. A detection rotation assembly 5 is arranged on the mounting bracket 1. The power output end of the detection rotation assembly 5 is in transmission connection with the circular ring plate 3 to drive the circular ring plate 3 to rotate. A movable plate 6 is movably connected to the inner bottom surface of the mounting bracket 1. Two main shaft locking assemblies 7 are movably arranged on the top surface of the movable plate 6. The two main shaft locking assemblies 7 are respectively arranged on both sides of the mounting bracket 1. A lateral displacement assembly 8 for driving the movable plate 6 to move horizontally and laterally is arranged on the inner bottom surface of the mounting bracket 1.

[0023] With such a design, the main shaft of the aviation turbojet engine to be detected can be passed through the middle of the circular ring plate 3. At this time, the detection end of the measurement component 4 contacts the outer wall of the main shaft. Then, the two main shaft locking components 7 are moved on the movable plate 6 to adjust the distance between the two main shaft locking components 7, and the clamping ends of the two main shaft locking components 7 are used to clamp both ends of the main shaft. The measurement component 4 is used to perform detection operations and data measurement operations on the main shaft. The lateral displacement component 8 is activated to drive the movable plate 6 to move laterally. The movement of the movable plate 6 drives the fixed main shaft to move laterally, realizing the switching of the measurement positions on the main shaft; thus, detection operations and data measurement operations can be carried out on multiple cross-sections of the main shaft.

[0024] In Embodiment 1, a guiding block 42 is fixedly installed on the inner bottom surface of the mounting frame 1. The cross-section of the guiding block 42 is T-shaped, and the guiding block 42 is arranged along the moving direction of the movable plate 6.

[0025] A guiding groove 43 is formed on the lower bottom surface of the movable plate 6. The inner surface shape of the guiding groove 43 matches the outer surface shape of the guiding block 42. The guiding groove 43 is formed along the moving direction of the movable plate 6, and the guiding block 42 is slidably installed in the guiding groove 43.

[0026] With such a design, through the cooperation of the guiding block 42 and the guiding groove 43, the movable plate 6 is slidably installed on the mounting frame 1, which is convenient for assembly and installation. Moreover, through the cooperation of the guiding block 42 and the guiding groove 43, the movement of the movable plate 6 can also be guided, improving the stability of the movable plate 6 during movement.

[0027] As Figure 1 、 Figure 5 and Figure 7 shown, the measurement component 4 includes a fixed shell 9. The fixed shell 9 is fixedly connected to the circular ring plate 3. A distance sensor 10 is installed on a side wall of the fixed shell 9 away from the circular ring plate 3. The detection end of the distance sensor 10 extends into the fixed shell 9. A flat plate 11 is movably arranged in the inner cavity of the fixed shell 9. A movable rod 12 is fixedly connected to a side of the flat plate 11 away from the distance sensor 10. The other end of the movable rod 12 penetrates through the circular ring plate 3 and is adjustably installed with an adjusting rod 13. The other end of the adjusting rod 13 is fixedly connected to a circular shell 14. A spherical ball 15 is movably connected in the circular shell 14.

[0028] In Embodiment 1, an adjusting blind hole is formed at the end of the movable rod 12 away from the flat plate 11. One end of the adjusting rod 13 is movably assembled in the adjusting blind hole. Internal threads are formed in the adjusting blind hole, and external threads are formed on the outer surface of the adjusting rod 13. The adjusting rod 13 is threadedly connected to the adjusting blind hole.

[0029] With such a design, a threaded connection is adopted between the adjusting rod 13 and the adjusting blind hole, which can conveniently and detachably install the adjusting rod 13 in the adjusting blind hole of the movable rod 12, facilitating the assembly of the adjusting rod 13 and the movable rod 12. When the adjusting rod 13 is rotated, the overall length of the adjusting rod 13 and the movable rod 12 can be adjusted through the cooperation of the threads, which is convenient to use and applicable to the detection operation of spindles of different specifications and models.

[0030] In the first embodiment, a threaded hole is vertically formed on the outer side wall of the movable rod 12, and a pressing bolt 32 is threadedly connected in the threaded hole. One end of the pressing bolt 32 is tightly abutted against the outer wall of the adjusting rod 13. The axial position and circumferential position of the adjusting rod 13 can be limited through the pressing bolt 32, thereby realizing the locking of the adjusting rod 13 and the movable rod 12, which is convenient to use.

[0031] Outside the first embodiment, the adjusting blind hole can also be a square hole. The overall structure of the adjusting rod 13 is a square rod, and one end of the adjusting rod 13 is inserted into the adjusting blind hole. The circumferential rotation of the adjusting rod 13 can be limited through the cooperation of the square surfaces, and the axial position and circumferential position of the adjusting rod 13 can be limited through the cooperation of the pressing bolt 32, which is convenient to use.

[0032] In the first embodiment, a spherical cavity is formed in the circular shell 14, and the spherical ball 15 is embedded and installed in the spherical cavity. One side of the spherical ball 15 is located outside the circular shell 14, and the spherical ball 15 can rotate freely relative to the circular shell 14.

[0033] A spring 16 is sleeved on the outer side wall of the movable rod 12. One end of the spring 16 is fixedly connected to the ring plate 3, and the other end of the spring 16 is fixedly connected to a side plate 17, and the side plate 17 is fixedly connected to the outer wall of the movable rod 12.

[0034] With such a design, the working principle of the measuring assembly 4 is as follows: The spring 16 outputs elastic force and acts on the side plate 17 and the movable rod 12, so that the movable rod 12 is fully extended in the initial state, and the extended length of the movable rod 12 is equal to the overall length of the spring 16 in the initial state.

[0035] When the main shaft of the aviation turbojet engine to be tested is inserted into the middle of the annular plate 3, the ball 15 is in contact with the outer surface of the main shaft. At this time, the movable rod 12 is retracted into the fixed shell 9 for a distance and the spring 16 is compressed. At this time, the elastic force output by the spring 16 acts on the movable rod 12, so that the movable rod 12 has the force to move toward the main shaft, thereby ensuring that the ball 15 is in real-time contact with the outer surface of the main shaft, and the distance sensor 10 is used to collect real-time data on the distance between the flat plate 11 and the distance sensor 10, and the data on the main shaft of the aviation turbojet engine is converted into distance data, so as to improve the convenience of measuring the main shaft of the aviation turbojet engine, and through the collection of multi-point data, the measurement accuracy of the main shaft of the aviation turbojet engine can be effectively improved, which is convenient to use.

[0036] In this embodiment 1, the two annular plates 2 are fixedly installed on the mounting frame 1, and the two annular plates 2 are arranged at intervals; an annular groove 37 is opened on the side surface of the two annular plates 2 that are close to each other, and a fixing ring 38 is fixedly connected to the two side surfaces of the circular ring plate 3, and the fixing ring 38 is inserted into the corresponding annular groove 37 and the fixing ring 38 and the annular groove 37 are movably connected.

[0037] With this design, the annular plate 3 can be conveniently assembled between the two annular plates 2 through the cooperation between the fixing ring 38 and the annular groove 37, and the annular plate 3 can also be supported to rotate through the cooperation between the fixing ring 38 and the annular groove 37, thereby improving the stability of the annular plate 3 when rotating on the annular plate 2 and improving the measurement accuracy of the main shaft.

[0038] In addition to the present embodiment 1, the two side surfaces of the circular ring plate 3 can also be rotatably connected to the two annular plates 2 by means of a bearing seat and a hollow shaft sleeve.

[0039] like Figure 2 and Figure 5 As shown, the detection rotating assembly 5 includes a first motor 18, which is fixedly mounted on the mounting frame 1 and close to the annular plate 3, and a power output end of the first motor 18 is transmission-connected to the outer wall of the annular plate 3 through a first transmission assembly.

[0040] The first transmission assembly includes a first rotating shaft 19, which is fixedly mounted on the power output end of the first motor 18. The other end of the first rotating shaft 19 is rotatably mounted on the mounting frame 1, and the axis of the first rotating shaft 19 is arranged parallel to the axis of the circular ring plate 3. A first gear 20 is fixedly mounted on the outer surface of the first rotating shaft 19, and a ring gear 21 is fixedly connected to the outer wall of the circular ring plate 3. The first gear 20 is meshed with the ring gear 21.

[0041] With such a design, the working principle of the detection rotation assembly 5 is as follows: The first motor 18 is started to drive the first rotating shaft 19 and the first gear 20 to rotate. The first gear 20 meshes with the annular gear 21 to drive the annular gear 21 to rotate. The annular gear 21 drives the ring plate 3 to rotate between the two annular plates 2. The ring plate 3 drives the spherical ball 15 of the measuring assembly 4 to move annularly on the outer surface of the main shaft, which is convenient for use.

[0042] When there are defects such as dents, cracks, and protrusions on the outer surface of the main shaft, the spherical ball 15 drives the adjusting rod 13 to move. The adjusting rod 13 drives the movable rod 12 to move. The movable rod 12 drives the flat plate 11 to move. At this time, the distance sensor 10 measures the moving distance of the flat plate 11, so as to realize the detection operation of the outer surface of the main shaft, and can also collect the data on the outer surface of the main shaft, and can accurately measure whether there are defects such as dents, cracks, and protrusions on the outer surface of the main shaft.

[0043] As Figure 3 and Figure 6 As shown, the main shaft locking assembly 7 includes a mounting plate 22. The mounting plate 22 is slidably mounted on the movable plate 6. A vertical plate 23 is fixedly connected to the top surface of the mounting plate 22. A locking mechanism for locking and clamping the end of the main shaft of the aero-turbine engine is fixedly installed on the top surface of the vertical plate 23.

[0044] In the first embodiment, the locking mechanism includes a circular plate 24. The circular plate 24 is fixedly installed on the top surface of the vertical plate 23. A plurality of positioning holes 25 are formed in the circular plate 24. A positioning screw 26 is threadedly connected in the positioning hole 25.

[0045] With such a design, when it is necessary to position and install the main shaft of the aero-turbine engine, the positioning screw 26 can be threadedly connected into the corresponding positioning hole 25 on the circular plate 24, and the positioning screw 26 is threadedly connected with the connection hole on the main shaft, so as to realize the fixed connection between one end of the main shaft and the circular plate 24, and further realize the positioning and placement of the main shaft, which is convenient for use.

[0046] In addition to the first embodiment, the locking mechanism can also adopt one of a three-jaw chuck and a four-jaw chuck. When a four-jaw chuck is adopted, the four-jaw chuck is fixedly installed on the top surface of the vertical plate 23. At this time, the four-jaw chuck is used to clamp the end of the main shaft, which is convenient for use. And the three-jaw chuck and the four-jaw chuck are both existing technologies and can be directly purchased on the market, so the specific structure thereof will not be described in detail here.

[0047] A displacement adjustment mechanism is provided between the mounting plate 22 and the movable plate 6. The displacement adjustment mechanism is started to drive the mounting plate 22 to slide on the movable plate 6, so as to drive the vertical plate 23 and the locking mechanism to move and adjust the horizontal position.

[0048] In the first embodiment, the displacement adjusting mechanism includes two fixing plates 27. The two fixing plates 27 are fixedly installed on the mounting plate 22. A second rotating shaft 29 is rotatably installed between the two fixing plates 27. One end of the second rotating shaft 29 penetrates through the corresponding fixing plate 27 and is drivingly connected to a second motor 30. The second motor 30 is fixedly installed on the mounting plate 22. A second gear 28 is fixedly installed on the second rotating shaft 29.

[0049] A first rack 31 is fixedly installed on the top surface of the movable plate 6. The first rack 31 is arranged along the length direction of the movable plate 6. The second gear 28 is meshed with the first rack 31.

[0050] With such a design, the working principle of the main shaft locking assembly 7 is as follows. First, the positioning screw 26 is screwed into the specified positioning hole 25 according to the model of the main shaft of the aero-turbine engine. Then, the second motors 30 on the two groups of main shaft locking assemblies 7 are started. The second motors 30 drive the second rotating shaft 29 and the second gear 28 to rotate. The second gear 28 meshes and rotates with the first rack 31, so as to drive the mounting plate 22 to move on the movable plate 6 towards the side close to the mounting frame 1. Driven by the second motors 30, the circular plates 24 on both sides are abutted against the two ends of the main shaft. Then, the two ends of the main shaft of the aero-turbine engine are locked by the positioning screw 26, completing the clamping and locking of the main shaft, which is convenient for efficient measurement operations.

[0051] In the first embodiment, the mounting plate 22 is arranged in an inverted concave shape, and a slider 39 is fixedly connected to its inner side wall. Sliding grooves 40 are respectively opened on the front and rear side surfaces of the movable plate 6. The sliding grooves 40 are opened along the moving direction of the mounting plate 22. The slider 39 is slidably installed in the corresponding sliding groove 40, which is convenient for assembly and installation.

[0052] With such a design, the mounting plate 22 can be conveniently slidably installed on the movable plate 6 through the cooperation of the slider 39 and the sliding groove 40, which is convenient for assembly and installation. And through the cooperation of the slider 39 and the sliding groove 40, the stability of the mounting plate 22 when moving on the movable plate 6 can be improved, ensuring the measurement accuracy.

[0053] As Figure 1-3 shown, the lateral displacement assembly 8 includes a support plate 41. The support plate 41 is fixedly installed on the inner bottom surface of the mounting frame 1. A third motor 33 is fixedly installed on the top surface of the support plate 41. The power output end of the third motor 33 is drivingly connected to the movable plate 6 through a second transmission assembly.

[0054] When the third motor 33 is started, it drives the movable plate 6 to move laterally through the second transmission assembly, realizing driving the clamped and locked main shaft of the aero-turbine engine to move laterally.

[0055] The second transmission component includes a third rotating shaft 34, which is fixedly connected to the power output end of a third motor 33. The other end of the third rotating shaft 34 is rotatably connected to the inner bottom surface of the mounting frame 1. A third gear 35 is fixedly installed on the third rotating shaft 34.

[0056] On one side wall of the movable plate 6 close to the third rotating shaft 34, a second rack 36 is fixedly installed. The second rack 36 is arranged along the moving direction of the movable plate 6. The third gear 35 is meshed and connected with the second rack 36.

[0057] With such a design, the working principle of the lateral displacement component 8 is as follows: Start the third motor 33 to output rotational power to drive the third rotating shaft 34 and the third gear 35 to rotate. The third gear 35 meshes with the second rack 36 to move, and the second rack 36 drives the movable plate 6 to move. The movement of the movable plate 6 can cause the aviation turbojet engine main shaft fixed thereon to move laterally, realizing the adjustment of the lateral position of the main shaft, and thus facilitating the measurement operation at different cross-sections of the main shaft and being convenient to use.

[0058] As Figure 1-8 shown, the present invention also provides a usage method of an aviation turbojet engine main shaft measuring device. Based on the above-mentioned aviation turbojet engine main shaft measuring device, it includes the following steps: S1: Pass the aviation turbojet engine main shaft through the annular plate 2 and the circular ring plate 3. At this time, the spherical ball 15 at the detection end of the measuring component 4 abuts tightly against the outer side wall of the aviation turbojet engine main shaft, completing the placement operation of the aviation turbojet engine main shaft.

[0059] In the S1 step, the working principle of the measuring component 4 in the initial state is as follows: When the aviation turbojet engine main shaft to be detected is inserted through the middle of the circular ring plate 3, the spherical ball 15 abuts against the outer surface of the main shaft. At this time, the movable rod 12 retracts into the fixed shell 9 by a certain distance and compresses the spring 16. At this time, the elastic force output by the spring 16 acts on the movable rod 12, making the movable rod 12 have a force to move towards the direction close to the main shaft. At this time, the movable rod 12 drives the spherical ball 15 to press tightly against the outer surface of the main shaft through the adjusting rod 13, ensuring real-time contact between the spherical ball 15 and the outer surface of the main shaft.

[0060] In the S1 step, the overall length of the movable rod 12 and the adjusting rod 13 can also be adjusted. When adjustment is needed, first loosen the compression bolt 32, and then rotate the adjusting rod 13. The adjusting rod 13 and the movable rod 12 are threadedly connected, and the overall length of the adjusting rod 13 and the movable rod 12 can be adjusted through the cooperation of the threads. After the adjustment is completed, tighten the compression bolt 32 to lock the adjusting rod 13 and the movable rod 12, which is convenient to use.

[0061] S2: Start two spindle locking components 7 according to the overall length of the spindle, and make them move on the movable plate 6 towards the side close to the mounting frame 1 until the locking mechanisms on the two spindle locking components 7 contact the two ends of the spindle, and clamp the two ends of the spindle through the locking mechanisms.

[0062] In the step S2, the working principle of the spindle locking component 7 is as follows: Start the second motors 30 on the two groups of spindle locking components 7 according to the overall length of the spindle. The second motors 30 drive the second gears 28 on the second rotating shafts 29 to rotate. The second gears 28 are meshed and connected with the first racks 31, so that the mounting plates 22 move on the movable plate 6 towards the side close to the mounting frame 1. Driven by the second motors 30, the circular plates 24 on both sides are abutted against the two ends of the spindle. Then, according to the model of the spindle, positioning screws 26 are screwed into the specified positioning holes 25, and the two ends of the spindle are locked through the positioning screws 26, thereby realizing the positioning and installation of the two ends of the spindle on the circular plates 24 of the two groups of spindle locking components 7, and realizing the positioning and placement of the spindle.

[0063] S3: Start the lateral displacement component 8 to drive the movable plate 6 to move laterally. The movement of the movable plate 6 drives the fixed spindle to move laterally, so as to realize the switching of the measurement positions on the spindle.

[0064] In the step S3, the working principle of the lateral displacement component 8 is as follows: Start the third motor 33 to drive the third rotating shaft 34 and the third gear 35 to rotate. The third gear 35 meshes with the second rack 36 to move, and the second rack 36 drives the movable plate 6 to move. The movement of the movable plate 6 can drive the fixed spindle to move laterally, so as to realize the adjustment of the lateral position of the spindle. When the spherical ball 15 is tangent to the position to be detected on the spindle, stop the operation of the third motor 33.

[0065] S4: Complete the communication connection between the distance sensor 10 in the measurement component 4 and the peripheral detection and control device, record the data on the distance sensor 10 as the initial position, start the detection and rotation component 5 to drive the circular ring plate 3 to rotate between the two annular plates 2. The circular ring plate 3 drives the spherical ball 15 to move on the outer wall of the spindle, and under the action of the spring 16, ensure that the spherical ball 15 is in real-time contact with the spindle. When there are processing defects on the outer wall of the spindle, the spherical ball 15 drives the adjusting rod 13, the movable rod 12 and the flat plate 11 to move synchronously. The distance sensor 10 is used to detect and collect the movement distance of the flat plate 11 in real time. After the circular ring plate 3 rotates one circle, the detection process and data collection process of the spindle on one cross section are completed.

[0066] In the step S4, the working principle of the detection rotating assembly 5 is as follows: Start the first motor 18 to drive the first rotating shaft 19 and the first gear 20 to rotate. The first gear 20 meshes with the annular gear 21 to rotate, and the annular gear 21 drives the circular ring plate 3 to rotate between the two annular plates 2. The circular ring plate 3 drives the spherical ball 15 to move annularly on the outer wall of the main shaft.

[0067] In the step S4, the spring 16 in the measurement assembly 4 outputs elastic force to keep the spherical ball 15 in contact with the outer surface of the main shaft in real time. And the distance sensor 10 is used to collect real-time data on the distance between the flat plate 11 and the distance sensor 10, converting the data on the main shaft of the aero-turbine engine into distance data. This can improve the convenience of measuring the main shaft of the aero-turbine engine, and through the collection of multi-point data, the measurement accuracy of the main shaft of the aero-turbine engine can be effectively improved, which is convenient for use.

[0068] S5: Turn off the detection rotating assembly 5 and reverse-start the lateral displacement assembly 8 to drive the movable plate 6 to drive the main shaft to move laterally, so as to switch the measurement position on the main shaft, and repeat the step S4 for the detection process and data collection process of another cross-section of the main shaft, and record it as the second position.

[0069] S6: Repeat the above steps S4 - S5 to perform multiple data collection operations on the data of the main shaft until the spherical ball 15 moves to the tangent position on the other side of the main shaft, and record it as the Nth position.

[0070] S7: Collect the data from the initial position to the Nth position, and based on the data collected by one of the distance sensors 10 as a reference, process the data collected by the distance sensors 10 in a clockwise direction according to the number of distance sensors 10, so that the data of the distance sensors 10 at all positions are converted and matched with the reference position data, calculate the data under the same reference and output the average value, and process the average value data through the control device and arrange it from the initial position to the Nth position, so as to obtain the measurement data of the main shaft of the aero-turbine engine.

[0071] Embodiment 2: As Figure 9 shown, based on the above Embodiment 1, in this Embodiment 2, the main shaft locking assembly 7 can also adopt Figure 9 the structure shown. The main shaft locking assembly 7 includes a mounting plate 22. The overall structure of the mounting plate 22 is the same as the overall structure in the above Embodiment 1. The mounting plate 22 is slidably mounted on the movable plate 6. The upper top surface of the movable plate 6 is a plane, and the inner top surface of the mounting plate 22 is slidably connected to the upper top surface of the movable plate 6. The movable plate 6 is slidably mounted on the movable plate 6 through the cooperation of a slider 39 and a chute 40.

[0072] A sliding groove 44 is provided on the upper top surface of the movable plate 6, and the sliding groove 44 is provided along the moving direction of the mounting plate 22. A driving screw 45 is provided in the sliding groove 44, and both ends of the driving screw 45 are rotatably connected to the inner wall of the sliding groove 44 respectively. A moving block 46 is threadedly connected to the driving screw 45, and the moving block 46 is slidably connected to the sliding groove 44, and the upper end of the moving block 46 is fixedly connected to the corresponding mounting plate 22.

[0073] A lead screw motor 47 is fixedly mounted on one end of the movable plate 6 , and a power output end of the lead screw motor 47 extends into the sliding groove 44 and is drivingly connected to one end of the driving lead screw 45 .

[0074] Designed in this way, the screw motor 47 is started to drive the driving screw 45 to rotate. The driving screw 45 rotates and drives the moving block 46 to move in the sliding groove 44 through threaded cooperation. At this time, the moving block 46 can drive the mounting plate 22 to move on the movable plate 6 to adjust the lateral position of the mounting plate 22.

[0075] A vertical plate 23 is mounted on the mounting plate 22 , and a locking mechanism for locking and clamping the main shaft end of an aviation turbojet engine is fixedly mounted on the top surface of the vertical plate 23 .

[0076] In this embodiment 2, the vertical plate 23 and the locking mechanism are the same as those in the above-mentioned embodiment 1.

[0077] In this embodiment 2, the spindle locking assembly 7 is divided into two groups, and both groups of spindle locking assemblies 7 need to move toward or away from the mounting frame 1. The sliding groove 44, the driving screw 45 and the screw motor 47 can all be designed into two groups, and the two groups of driving screws 45 drive the two groups of spindle locking assemblies 7 to move toward or away from the mounting frame 1 through the cooperation of the moving block 46.

[0078] In addition to the present embodiment 2, the sliding groove 44, the driving screw 45 and the screw motor 47 can also be designed as a group, and the driving screw 45 is provided with two threaded sections, the two threaded sections are symmetrically arranged, and the thread rotation directions of the two threaded sections are opposite, and the two threaded sections are respectively threadedly connected with moving blocks 46, and the two moving blocks 46 are respectively fixedly connected to the corresponding mounting plates 22.

[0079] With this design, the screw motor 47 is started to drive the driving screw 45 to rotate. The driving screw 45 rotates and drives the two moving blocks 46 to move toward or away from each other through the cooperation of the threads on the two threaded sections, thereby driving the two sets of spindle locking assemblies 7 to move synchronously toward or away from the mounting frame 1, which is convenient and practical.

[0080] Embodiment 3, as Figure 10As shown, based on the above-mentioned Embodiment 1, in this Embodiment 3, the lateral displacement assembly 8 may also adopt Figure 10 the structure shown. The movable plate 6 is slidably mounted on the mounting frame 1 through the cooperation of the guide block 42 and the guide groove 43. Two connecting plates 48 arranged at intervals are fixedly mounted on the mounting frame 1. The two connecting plates 48 are parallel and arranged at intervals. A moving lead screw 49 is rotatably mounted between the two connecting plates 48. A nut block 50 is threadedly connected to the moving lead screw 49. One side of the nut block 50 close to the movable plate 6 is fixedly connected to the movable plate 6.

[0081] The heights of the connecting plate 48 and the nut block 50 are less than the distance between the lower end surface of the mounting plate 22 and the upper end surface of the mounting frame 1. With such a design, after the connecting plate 48 and the nut block 50 are provided, it will not affect the sliding of the mounting plate 22 on the movable plate 6.

[0082] A driving motor 51 is fixedly mounted on the inner bottom surface of the mounting frame 1. The power output end of the driving motor 51 is in transmission connection with the moving lead screw 49. The driving motor 51 outputs rotational power to drive the moving lead screw 49 to rotate. The rotation of the moving lead screw 49 drives the nut block 50 to move through threaded cooperation. The movement of the nut block 50 drives the movable plate 6 to move on the mounting frame 1, realizing the adjustment of the lateral position of the movable plate 6.

[0083] The present invention covers any substitutions, modifications, equivalent methods, and solutions made to the essence and scope of the present invention; in order to enable the public to have a thorough understanding of the present invention, specific details are described in detail in the following preferred embodiments of the present invention, and those skilled in the art can fully understand the present invention without the description of these details; in addition, in order to avoid unnecessary confusion to the essence of the present invention, well-known methods, processes, procedures, components, and circuits are not described in detail.

[0084] Those of ordinary skill in the art can understand that all or part of the steps of implementing the above-mentioned embodiment methods can be completed by instructing relevant hardware through a program, and the program can be stored in a computer-readable storage medium, such as: ROM / RAM, magnetic disk, optical disc, etc.

[0085] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. An aviation turbojet engine main shaft measuring device, comprising a mounting bracket (1), characterized in that: Two annular plates (2) are symmetrically and fixedly connected to the mounting frame (1). A circular ring plate (3) is movably connected between the two annular plates (2). A plurality of measuring components (4) are evenly distributed on the circular ring plate (3). A detection and rotation component (5) is arranged on the mounting frame (1). The power output end of the detection and rotation component (5) is in transmission connection with the circular ring plate (3) to drive the circular ring plate (3) to rotate. A movable plate (6) is movably connected to the inner bottom surface of the mounting frame (1). Two main shaft locking components (7) are movably arranged on the top surface of the movable plate (6). A transverse displacement component (8) for driving the movable plate (6) to move horizontally is arranged on the inner bottom surface of the mounting frame (1).

2. The aero-turbojet engine main shaft measuring device according to claim 1, characterized in that: The measuring component (4) includes a fixed shell (9). The fixed shell (9) is fixedly connected to the circular ring plate (3). A distance sensor (10) is installed on one side wall of the fixed shell (9) away from the circular ring plate (3). The detection end of the distance sensor (10) extends into the fixed shell (9). A flat plate (11) is movably arranged in the inner cavity of the fixed shell (9). A movable rod (12) is fixedly connected to the side of the flat plate (11) away from the distance sensor (10). The other end of the movable rod (12) penetrates through the circular ring plate (3) and is adjustably installed with an adjusting rod (13). The other end of the adjusting rod (13) is fixedly connected to a circular shell (14). A spherical ball (15) is movably connected in the circular shell (14).

3. The main shaft measuring device of an aviation turbojet engine according to claim 2, characterized in that: A spring (16) is sleeved on the outer side wall of the movable rod (12). One end of the spring (16) is fixedly connected to the circular ring plate (3). The other end of the spring (16) is fixedly connected to a side plate (17). The side plate (17) is fixedly connected to the outer wall of the movable rod (12).

4. The spindle measuring device for an aviation turbojet engine according to claim 3, characterized in that: The detection and rotation component (5) includes a first motor (18). The first motor (18) is fixedly installed on the mounting frame (1). The power output end of the first motor (18) is in transmission connection with the outer side wall of the circular ring plate (3) through a first transmission component.

5. The measuring device for the main shaft of an aviation turbojet engine according to claim 4, characterized in that: The main shaft locking component (7) includes a mounting plate (22). The mounting plate (22) is slidably installed on the movable plate (6). A vertical plate (23) is fixedly connected to the top surface of the mounting plate (22). A locking mechanism for locking and clamping the end of the main shaft of the aero-turboprop engine is fixedly installed on the top surface of the vertical plate (23).

6. The spindle measuring device for an aviation turbojet engine according to claim 5, characterized in that: A displacement adjustment mechanism is arranged between the mounting plate (22) and the movable plate (6). The displacement adjustment mechanism is started to drive the mounting plate (22) to slide on the movable plate (6), so as to drive the vertical plate (23) and the locking mechanism to move and adjust the horizontal position.

7. The main shaft measuring device of an aviation turbojet engine according to claim 6, characterized in that: The transverse displacement component (8) includes a support plate (41). The support plate (41) is fixedly installed on the inner bottom surface of the mounting frame (1). A third motor (33) is fixedly installed on the top surface of the support plate (41). The power output end of the third motor (33) is in transmission connection with the movable plate (6) through a second transmission component. When the third motor (33) is started, the movable plate (6) is driven to move horizontally through the second transmission component, so as to drive the main shaft of the aero-turboprop engine clamped by the locking mechanism to move horizontally.

8. The spindle measuring device for an aviation turbojet engine according to claim 7, characterized in that: Both of the two annular plates (2) are provided with annular grooves (37). Fixed rings (38) are fixedly connected to both side surfaces of the ring plate (3), and the fixed rings (38) are movably installed in the corresponding annular grooves (37).

9. The spindle measuring device for an aviation turbojet engine according to claim 8, wherein: One end of the movable rod (12) far away from the flat plate (11) is provided with an adjusting blind hole. One end of the adjusting rod (13) is movably assembled in the adjusting blind hole. A threaded hole is vertically formed in the outer side wall of the movable rod (12), and a pressing bolt (32) is threadedly connected in the threaded hole. One end of the pressing bolt (32) is tightly abutted against the outer wall of the adjusting rod (13).

10. A method for using a measuring device for the main shaft of an aviation turbojet engine, based on the measuring device for the main shaft of an aviation turbojet engine described in claim 9, characterized in that: It includes the following steps: S1: Pass the main shaft of the aero-turbine engine through the annular plate (2) and the ring plate (3). At this time, the ball (15) at the detection end of the measuring assembly (4) is tightly abutted against the outer side wall of the main shaft of the aero-turbine engine, and the placement operation of the main shaft of the aero-turbine engine is completed; S2: Start the two main shaft locking assemblies (7) according to the overall length of the main shaft, so that they move on the movable plate (6) towards the side close to the mounting frame (1) until the locking mechanisms on the two main shaft locking assemblies (7) contact the two ends of the main shaft, and clamp the two ends of the main shaft through the locking mechanisms; S3: Start the lateral displacement assembly (8) to drive the movable plate (6) to move laterally. The movement of the movable plate (6) drives the fixed main shaft to move laterally, so as to realize the switching of the measuring positions on the main shaft; S4: Complete the communication connection between the distance sensor (10) in the measuring assembly (4) and the external detection and control device, record the data on the distance sensor (10) as the initial position, start the detection and rotation assembly (5) to drive the ring plate (3) to rotate. The ring plate (3) drives the ball (15) to move on the outer wall of the main shaft, and under the action of the spring (16), ensure that the ball (15) is in real-time contact with the main shaft. When there are processing defects on the outer wall of the main shaft, the ball (15) drives the adjusting rod (13), the movable rod (12) and the flat plate (11) to move synchronously. The moving distance of the flat plate (11) is detected and data is collected in real time through the distance sensor (10). After the ring plate (3) rotates one circle, the detection process and data collection process of the main shaft in one cross-section are completed; S5: Turn off the detection and rotation assembly (5) and reverse-start the lateral displacement assembly (8) to drive the movable plate (6) to drive the main shaft to move laterally, so as to realize the switching of the measuring positions on the main shaft, and repeat step S4 to perform the detection process and data collection process on another cross-section of the main shaft, and record it as the second position; S6: Repeat the above steps S4 - S5 to realize multiple data collection operations on the main shaft until the ball (15) moves to the tangent position on the other side of the main shaft, and record it as the Nth position; S7: Collect the data from the initial position to the Nth position, and based on the data collected by one of the distance sensors (10) as a reference, process the data collected by the distance sensors (10) in a clockwise direction according to the number of distance sensors (10), so that the data of the distance sensors (10) at all positions are converted and matched with the reference position data, calculate the data under the same reference and output the average value, process the average value data through the control device and arrange it according to the initial position to the Nth position, so as to obtain the measurement data of the main shaft of the aero-turbine engine.

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