Aero-engine compressor rotor stretching detection device and detection method

Abstract

According to the aero-engine compressor rotor stretching detection device and method, a dummy shaft is led out through a low-pressure pull rod, and a tool pull rod and a shifting sleeve are matched with the end face, the outer circle and a locking nut of the low-pressure pull rod, so that the deformation amount of the low-pressure pull rod can be strictly controlled in the shifting sleeve rotating process; and through alignment of calibration lines, it is ensured that the assembly position meets the design requirement. Meanwhile, monitoring of the stretching amount and alignment of the calibration line can be completed through the distance measuring instrument and the visual alignment device, data visualization in the assembly process is achieved, the assembly quality and the assembly efficiency are improved, and the problems that the rotor assembly stretching amount cannot be visualized and digitized, and the assembly position is difficult to match are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of tensile testing of compressor rotors of aircraft engines, and more specifically, relates to a tensile testing device and a testing method for compressor rotors of aircraft engines. Background Art

[0002] The first and second stage rotors of a new turboprop engine low-pressure compressor adopt a new type of large interference fit stop centering and end face torque transmission connection with low-pressure tie rod tightening. In the actual assembly process, the residual deformation of the low-pressure tie rod is currently controlled and the locking collar is installed to ensure the reliability of the rotor connection. In order to ensure the safe and stable operation of the engine, the residual deformation of the low-pressure tie rod needs to be monitored during the assembly process.

[0003] The rotor structure of a new turboprop engine Figure 1 As shown, the turboprop engine rotor includes a first-stage rotor, a second-stage rotor, a low-pressure tie rod, a tone wheel and a locking nut. The compressor first-stage disc with a 2.5# bearing is connected to the compressor second-stage disc stop by a low-pressure tie rod, and the locking nut presses the 2.5# bearing through the tone wheel. In the rotor assembly, the tightening torque of the bolts, nuts, and bearing locking nuts is a key element in the control of the assembly state. In CN201711054883.4, an aircraft engine rotor assembly method discloses an assembly method that can be adopted, which includes: step A, assembling the rotor, step B, providing a device, the device includes an outer support tube, an inner tie rod, a nut wrench, a hydraulic pump, a dial indicator and a handle. Step C, adjusting the transmission rod, installing the dial indicator, adjusting the force of the dial indicator acting on the transmission rod, so that the transmission rod is in stable contact with the step portion of the inner tie rod. Step D, applying a pressure of 0.2 MPa to the hydraulic pump, and then adjusting the dial indicator to zero. Step E: Increase the pressure of the hydraulic pump, tighten the nut, and then remove the pressure of the hydraulic pump. Step F: Apply a pressure of 0.2 MPa to the hydraulic pump and detect the reading of the dial indicator. This patent designs a device that simplifies the assembly process and improves assembly efficiency. However, the stretching amount needs to be strictly controlled during the rotor stretching process. In this device, it is impossible to monitor and measure key quality data in real time during the assembly process, and its assembly accuracy and quality stability cannot be highly guaranteed.

[0004] In order to solve the problem of data monitoring and measurement, CN202410809505.6, an aircraft engine rotor stretching and stretching detection device, discloses a monitoring device, including a basic frame, a rotor stop and positioning tool, a hydraulic stretching mechanism, a tie rod stretching measurement mechanism and a control system, wherein the basic frame includes a base and a column, the base is fixedly mounted on the ground, the column is vertically fixed to the rear side of the base, the rotor stop and positioning tool is fixedly slidably connected to the base, the hydraulic stretching mechanism and the tie rod stretching measurement device are fixedly mounted on the column, and the control system is fixedly mounted behind the column. This patent realizes the automatic execution of rotor stretching action during the compressor rotor assembly process according to the assembly requirements of aircraft engine compressor rotor components. At the same time, real-time detection and collection of tensile deformation data, analysis and decision-making of parts during the process can significantly improve the assembly quality and consistency. However, during the assembly process, not only the stretching amount must be strictly controlled, such as Figure 2 In addition, it is necessary to ensure that the circumferential position of the locking nut is properly tightened. If the stretching amount does not meet the design value or the end face / circumferential claws of the locking block claw cannot be installed at the same time, it is necessary to apply load again to tighten or unload and reload to tighten until the stretching amount meets the design requirements and the locking block circumference and end face claws can lock the parts at the same time. The stretching process of the stretching device is not visible, and the process is cumbersome and uncontrollable, resulting in reduced installation efficiency, so it is difficult to ensure that the installation position of the parts matches. Summary of the invention

[0005] The present invention provides an aircraft engine compressor rotor stretching detection device to overcome the problems that the existing aircraft engine rotor stretching amount cannot be visualized, the stretching amount cannot be monitored at one time, the locking block cannot be aligned with the locking grooves of the nut and the pull rod at one time, and the stretching tooling needs to be disassembled and assembled multiple times.

[0006] The present invention also provides a detection method including an aircraft engine compressor rotor stretching detection device based on the device.

[0007] The present invention is achieved through the following technical solutions:

[0008] An aircraft engine compressor rotor stretching detection device, comprising a stretching device, a rangefinder, a visual alignment device and a control system;

[0009] The stretching device comprises a low-pressure pull rod lead-out dummy shaft, a tooling pull rod, a hydraulic pump, a support bridge and a pull sleeve, the tooling pull rod is sleeved on the low-pressure pull rod lead-out dummy shaft, the tooling pull rod is connected to the outer wall of the low-pressure pull rod, the pull sleeve is sleeved on the outer wall of the tooling pull rod, and the pull sleeve can be sleeved with the locking nut on the low-pressure pull rod, and calibration lines are provided on the low-pressure pull rod lead-out dummy shaft and the pull sleeve; the hydraulic pump is fixedly connected to the support bridge, and the hydraulic pump and the support bridge are sleeved on the tooling pull rod, and the hydraulic pump is fixedly connected to the tooling pull rod through the tooling nut;

[0010] The stretching device is fixed on a fixture frame, and a distance meter for measuring the displacement of the low-voltage pull rod lead-out dummy shaft is provided on the fixture frame. The fixture frame is also provided with a visual alignment device for detecting the alignment of the fixture pull rod and the calibration line on the low-voltage pull rod lead-out dummy shaft;

[0011] The hydraulic pump, the visual alignment device and the rangefinder are connected to a control system.

[0012] Furthermore, the distance meter is located just above the dummy shaft led out of the low-pressure pull rod.

[0013] Furthermore, one end of the low-pressure pull rod lead-out dummy shaft is provided with an end face tooth opening matching the low-pressure pull rod end face groove of the aircraft engine compressor rotor, and the other end of the low-pressure pull rod lead-out dummy shaft is provided with a calibration line for calibrating the position of the locking block installation groove of the low-pressure pull rod.

[0014] Furthermore, the inner wall of the tooling pull rod is provided with an internal thread matching the outer wall thread of the low-pressure pull rod of the aircraft engine compressor rotor.

[0015] Furthermore, the tooling pull rod is also provided with a calibration line for coinciding the low-pressure pull rod leading-out dummy shaft with the dial sleeve calibration line.

[0016] Furthermore, the pull sleeve is provided with a calibration line for calibrating the installation position of the lock block of the locking nut.

[0017] Furthermore, the visual alignment device includes a first visual alignment device and a second visual alignment device. The first visual alignment device detects the alignment of the calibration line at the connection between the calibration rod and the low-voltage rod lead-out dummy shaft, and the second visual alignment device detects the alignment of the calibration line on the pull sleeve and the tooling rod.

[0018] Furthermore, the support bridge is provided with a visual hole or a transparent visual area for the marking line on the tooling pull rod to be detected by the visual alignment device.

[0019] Furthermore, the rangefinder is a laser rangefinder.

[0020] Furthermore, the visual alignment device includes a camera or a video camera.

[0021] A method for detecting the tensile strength of an aircraft engine compressor rotor, comprising the following steps:

[0022] S1. Connect the second-stage rotor to the low-pressure pull rod through threads, then put the first-stage rotor on the low-pressure pull rod to make the first-stage rotor and the second-stage rotor interference connected, put the tone wheel on the first-stage rotor, screw the locking nut on the low-pressure pull rod to make the locking nut contact with the tone wheel.

[0023] S2. Install the toothed part of one end of the low-pressure tie rod lead-out dummy shaft in the end face groove of the low-pressure tie rod of the compressor rotor of the aircraft engine, and set a calibration line on the other end to calibrate the position of the locking block installation groove of the low-pressure tie rod. Then, fit the tool tie rod on the outer wall of the low-pressure tie rod lead-out dummy shaft, so that the end with the internal thread is connected to the external thread of the outer circle of the low-pressure tie rod, and then fit the pull sleeve on the tool tie rod and make the pull sleeve fit on the locking nut at the same time. The surface of the pull sleeve is provided with a calibration line for calibrating the installation angle of the nut.

[0024] S3. After fixing the hydraulic pump and the supporting bridge, fit them onto the tooling tie rod, and connect the tooling tie rod and the hydraulic pump through the tooling nut. Set the pressure value of the hydraulic pump in the control system and start the hydraulic pump.

[0025] S4. The first visual alignment device aligns the calibration line of the low-voltage pull rod lead-out false shaft of the low-voltage pull rod lock block installation groove, and the second visual alignment device aligns the calibration line of the lock block installation position of the calibrated locking nut. There is an offset in the installation position of the locking nut, which causes the lock block to be unable to be aligned with the installation position of the locking nut in the lock block installation groove. When the calibration lines of the upper camera and the lower camera are not in a straight line, the locking nut is driven to rotate by turning the dial sleeve until the calibration lines of the first visual alignment device and the second visual alignment device are in the same straight line, that is, the low-voltage pull rod lock block installation groove calibrated by the low-voltage pull rod lead-out false shaft and the lock block installation position of the locking nut are aligned with the installation structure position of the lock block.

[0026] S5. Release the pressure on the hydraulic cylinder, disassemble the tensile testing device, install the locking block and the safety on the locking nut, and complete the rotor assembly.

[0027] Furthermore, when the calibration lines of the dummy shaft led out by the low-pressure pull rod and the pull sleeve coincide, the stretching value measured by the distance meter is controlled within a range of 0.66-0.813 mm.

[0028] Compared with the prior art, the beneficial effects are:

[0029] The present invention uses the low-pressure pull rod to lead out the false shaft, the tooling pull rod and the pull sleeve to match the low-pressure pull rod end face, outer circle and locking nut. In the process of rotating the pull sleeve, the deformation of the low-pressure pull rod can be strictly controlled, and the alignment of the calibration line can be used to ensure that its assembly position meets the design requirements. At the same time, the present application can monitor the stretching amount and align the calibration line through a rangefinder and a visual alignment device, realize data visualization during the assembly process, and improve assembly quality and assembly efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 is a schematic diagram of the rotor structure;

[0031] Figure 2 It is a schematic diagram of the alignment of the low-pressure tie rod and the locking nut;

[0032] Figure 3 It is a schematic diagram of a tensile testing device for an aircraft engine compressor rotor;

[0033] Figure 4 It is an exploded schematic diagram of the stretching device structure;

[0034] Figure 5 It is a schematic diagram of the structural combination of the stretching device.

[0035] Among them, 101 tone wheel, 102 locking block, 103 locking nut, 104 low-pressure pull rod, 105 first-stage rotor, 106 second-stage rotor, 2 stretching device, 201 low-pressure pull rod leading out dummy shaft, 202 tooling pull rod, 203 pull sleeve, 204 hydraulic pump, 205 support bridge, 206 tooling nut, 3 rangefinder, 401 upper camera, 402 lower camera, 5 tooling frame. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] It should be noted that if there are directional indications (such as up, down, left, right, front, and back) in the embodiments of the present invention, the directional indications are only used to explain the relative positional relationship, movement, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indications will also change accordingly. If there are descriptions of "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features.

[0038] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] Example 1

[0040] This embodiment provides an aircraft engine compressor rotor stretching detection device, including a stretching device 2, a rangefinder 3 and a visual alignment device.

[0041] The stretching device 2 includes a low-pressure tie rod lead-out dummy shaft 201, a tool tie rod 202, a hydraulic pump 204, a support bridge 205 and a pull sleeve 203. One end of the low-pressure tie rod lead-out dummy shaft 201 is connected to the end face of the low-pressure tie rod 104. The tool tie rod 202 is sleeved on the low-pressure tie rod lead-out dummy shaft 201, and the tool tie rod 202 is connected to the outer wall of the low-pressure tie rod 104. The pull sleeve 203 is sleeved on the outer wall of the tool tie rod 202, and the pull sleeve 203 can be connected to the locking nut 103 on the low-pressure tie rod 104. The hydraulic pump 204 is fixedly connected to the support bridge 205, and the hydraulic pump 204 and the support bridge 205 are sleeved on the tool tie rod 202, and the hydraulic pump 204 is fixedly connected to the tool tie rod 202 through the tool nut 206.

[0042] The stretching device 2 is fixed on the tooling frame 5, and a laser rangefinder 3 is provided above the tooling frame 5. The laser rangefinder 3 is located at the low-pressure pull rod lead-out dummy shaft 201 to measure the end surface displacement of the low-pressure pull rod lead-out dummy shaft 201. The tooling frame 5 is also provided with a visual alignment device to detect the rotational offset of the low-pressure pull rod lead-out dummy shaft 201 and the tooling pull rod 202. The hydraulic pump 204, the visual alignment device and the rangefinder 3 are connected to the control system.

[0043] Example 2

[0044] This embodiment provides an aircraft engine compressor rotor stretching detection device, including a stretching device 2, a rangefinder 3 and a visual alignment device.

[0045] like Figures 4-5 The stretching device 2 includes a low-pressure pull rod lead-out dummy shaft 201, a tooling pull rod 202, a hydraulic pump 204, a support bridge 205 and a pull sleeve 203. One end of the low-pressure pull rod lead-out dummy shaft 201 is provided with an end face tooth mouth matching the end face notch of the low-pressure pull rod 104, and the other end is provided with a calibration line for calibrating the installation groove position of the locking block 102 of the low-pressure pull rod 104. The tooling pull rod 202 is fitted on the low-pressure pull rod lead-out dummy shaft 201, and the inner wall of the tooling pull rod 202 is provided with an internal thread matching the outer wall thread of the low-pressure pull rod 104. The pull sleeve 203 is fitted on the outer wall of the tooling pull rod 202, and the pull sleeve 203 can be fitted with the locking nut 103 on the low-pressure pull rod 104, and the pull sleeve 203 is provided with a calibration line for calibrating the installation position of the locking block on the locking nut 103. The surface of the tooling tie rod 202 is provided with a straight line for the low-pressure tie rod to lead out the dummy shaft 201 and coincide with the marking line of the pull sleeve 203. The hydraulic pump 204 and the support bridge 205 are fixedly connected, and the hydraulic pump 204 and the support bridge 205 are sleeved on the tooling tie rod 202, and the hydraulic pump 204 and the tooling tie rod 202 are fixedly connected through the tooling nut 206.

[0046] like Figure 3 As shown, the stretching device 2 is fixed on the tooling frame 5, and a laser rangefinder 3 is provided above the tooling frame 5. The laser rangefinder 3 is located on the central axis of the power cylinder, the support bridge 205, the tooling tie rod 202 and the pull sleeve 203 to measure the displacement of the end face of the pressure tie rod leading out of the dummy shaft. An upper camera 401 is provided above the tooling frame 5 to detect the calibration line of the connection between the tooling tie rod 202 and the low-pressure tie rod leading out of the dummy shaft 201, and a lower camera 402 is provided below the tooling frame 5 to detect the calibration line on the pull sleeve 203 and the tooling tie rod 202. The hydraulic pump 204, the upper camera 401, the lower camera 402 and the rangefinder 3 are connected to the control system.

[0047] In this embodiment, the visual alignment device may use a video camera for monitoring in addition to a camera.

[0048] Example 3

[0049] This embodiment provides a method for detecting the tensile strength of an aircraft engine compressor rotor. Figure 1 As shown, the aircraft engine rotor includes a first-stage rotor 105, a second-stage rotor 106, a low-pressure tie rod 104, a tone wheel 101 and a locking nut 103. The deformation of the low-pressure tie rod 104 when assembled in place is 0.66-0.813 mm. The detection steps include:

[0050] S1. Connect the second-stage rotor 106 to the low-pressure tie rod 104 through threads, and then put the first-stage rotor 105 on the low-pressure tie rod 104 to make the first-stage rotor 105 and the second-stage rotor 106 interference connected, put the tone wheel 101 on the first-stage rotor 105, screw the locking nut 103 on the low-pressure tie rod 104, and make the locking nut 103 contact with the tone wheel 101.

[0051] S2. Install the toothed portion at one end of the low-pressure rod lead-out dummy shaft 201 in the end face groove of the low-pressure rod 104 of the compressor rotor of the aircraft engine, and set a calibration line at the other end to calibrate the installation groove position of the lock block 102 of the low-pressure rod 104. Then, fit the tooling rod 202 on the outer wall of the low-pressure rod lead-out dummy shaft 201, so that the end with the internal thread is connected to the external thread of the outer circle of the low-pressure rod 104, and then fit the pull sleeve 203 on the tooling rod 202 and make the pull sleeve 203 fit on the locking nut 103 at the same time. The surface of the pull sleeve 203 is provided with a calibration line for calibrating the installation angle of the nut.

[0052] S3. After the hydraulic pump 204 and the support bridge 205 are fixedly assembled, they are fitted on the tooling tie rod 202, and the tooling tie rod 202 and the hydraulic pump 204 are connected through the tooling nut 206. Then, the upper camera 401 is used to calibrate and align the calibration line at the fitting point where the low-pressure tie rod leads out the dummy shaft 201 and the upper part of the tooling tie rod 202, and the pressure value of the hydraulic pump 204 is set in the control system, and the hydraulic pump 204 is turned on.

[0053] S4. The upper camera 401 is aligned with the notch mark line of the low-voltage tie rod leading out of the false shaft 201, which leads out the installation groove of the low-voltage tie rod 104 and the lock block 102, and the lower camera 402 is aligned with the position calibration line of the lock block 102 installation position of the calibrated locking nut 103. Since the installation position of the locking nut 103 may be offset, the lock block 102 cannot be aligned with the installation position of the locking nut 103 in the installation groove of the lock block 102, so the calibration lines of the upper camera 401 and the lower camera 402 are not on a straight line. Turning the dial sleeve 203 drives the locking nut 103 to rotate, and at the same time ensures that the displacement difference measured by the rangefinder 3 is within 0.66-0.813mm, until the calibration lines of the upper camera 401 and the lower camera 402 are on the same straight line, that is, the low-pressure pull rod 104 locking block 102 installation groove calibrated by the low-pressure pull rod leading out false axis 201 and the locking block 102 installation position of the locking nut 103 are aligned with the installation structure position of the lock block 102.

[0054] S5. Release the pressure on the hydraulic cylinder, disassemble the tensile testing device, install the locking block 102 and the safety on the locking nut 103, and complete the rotor assembly.

[0055] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. 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 embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. An aircraft engine compressor rotor tensile testing device, characterized in that: It includes stretching device, distance meter, visual alignment device and control system; The stretching device comprises a low-pressure pull rod lead-out dummy shaft, a tooling pull rod, a hydraulic pump, a support bridge and a pull sleeve, the tooling pull rod is sleeved on the low-pressure pull rod lead-out dummy shaft, the tooling pull rod is connected to the outer wall of the low-pressure pull rod, the pull sleeve is sleeved on the outer wall of the tooling pull rod, and the pull sleeve can be sleeved with the locking nut on the low-pressure pull rod, and calibration lines are provided on the low-pressure pull rod lead-out dummy shaft and the pull sleeve; the hydraulic pump is fixedly connected to the support bridge, and the hydraulic pump and the support bridge are sleeved on the tooling pull rod, and the hydraulic pump is fixedly connected to the tooling pull rod through the tooling nut; The stretching device is fixed on a fixture frame, and a distance meter for measuring the displacement of the low-voltage pull rod lead-out dummy shaft is provided on the fixture frame. The fixture frame is also provided with a visual alignment device for detecting the alignment of the fixture pull rod and the calibration line on the low-voltage pull rod lead-out dummy shaft; The hydraulic pump, the visual alignment device and the rangefinder are connected to a control system.

2. The aircraft engine compressor rotor tensile testing device according to claim 1, characterized in that: The distance meter is located just above the dummy shaft where the low-pressure pull rod leads out.

3. The aero-engine compressor rotor tensile testing device according to claim 1, characterized in that: One end of the low-pressure pull rod leading-out dummy shaft is provided with an end face tooth opening matching the low-pressure pull rod end face groove of the aircraft engine compressor rotor, and the other end of the low-pressure pull rod leading-out dummy shaft is provided with a calibration line for calibrating the position of the locking block installation groove of the low-pressure pull rod.

4. The aircraft engine compressor rotor tensile testing device according to claim 1, characterized in that: The inner wall of the tooling pull rod is provided with an internal thread matching the outer wall thread of the low-pressure pull rod of the compressor rotor of the aircraft engine.

5. The aircraft engine compressor rotor tensile testing device according to claim 1, characterized in that: The tooling pull rod is also provided with a calibration line for coinciding the low-pressure pull rod leading out the false shaft and the dial sleeve calibration line.

6. The aircraft engine compressor rotor tensile testing device according to claim 1, characterized in that: The pull sleeve is provided with a calibration line for calibrating the installation position of the lock block of the locking nut.

7. The aircraft engine compressor rotor tensile testing device according to claim 1, characterized in that: The visual alignment device includes a first visual alignment device and a second visual alignment device. The first visual alignment device detects the alignment of the calibration line at the connection between the calibration rod and the low-voltage rod leading out false shaft, and the second visual alignment device detects the alignment of the calibration line on the pull sleeve and the tooling rod.

8. The aircraft engine compressor rotor tensile testing device according to claim 1, characterized in that: The support bridge is provided with a visual hole or a transparent visual area for the marking line on the tooling pull rod to be detected by the visual alignment device.

9. A method for detecting the tensile strength of an aircraft engine compressor rotor, characterized in that the steps include: S1. Connect the second-stage rotor to the low-pressure rod through threads, then sleeve the first-stage rotor on the low-pressure rod to make the first-stage rotor and the second-stage rotor interference-connected, sleeve the tone wheel on the first-stage rotor, screw the locking nut on the low-pressure rod to make the locking nut contact with the tone wheel; S2. Install the toothed portion of one end of the low-pressure tie rod lead-out dummy shaft in the end face groove of the low-pressure tie rod of the compressor rotor of the aircraft engine, and provide a calibration line at the other end to calibrate the position of the locking block installation groove of the low-pressure tie rod. Then, fit the tooling tie rod on the outer wall of the low-pressure tie rod lead-out dummy shaft so that one end with the internal thread is connected to the external thread of the outer circle of the low-pressure tie rod. Then, fit the pull sleeve on the tooling tie rod and simultaneously fit the pull sleeve on the locking nut. The surface of the pull sleeve is provided with a calibration line for calibrating the installation angle of the nut. S3. After the hydraulic pump and the support bridge are fixedly assembled, they are fitted on the tooling tie rod, and the tooling tie rod and the hydraulic pump are connected through the tooling nut, the pressure value of the hydraulic pump is set in the control system, and the hydraulic pump is turned on; S4. The first visual alignment device aligns the calibration line of the low-voltage tie rod leading out false shaft of the low-voltage tie rod locking block installation groove, and the second visual alignment device aligns the calibration line of the lock block installation position of the calibrated locking nut. There is an offset in the installation position of the locking nut, which causes the lock block to be unable to be aligned with the installation position of the locking nut in the lock block installation groove. When the calibration lines of the upper camera and the lower camera are not in a straight line, the locking nut is driven to rotate by turning the dial sleeve until the calibration lines of the first visual alignment device and the second visual alignment device are in the same straight line, that is, the low-voltage tie rod locking block installation groove calibrated by the low-voltage tie rod leading out false shaft and the lock block installation position of the locking nut are aligned with the installation structure position of the lock block; S5. Release the pressure on the hydraulic cylinder, disassemble the tensile testing device, install the locking block and the safety on the locking nut, and complete the rotor assembly.

10. The method for tensile testing of an aircraft engine compressor rotor according to claim 9, characterized in that: When the calibration lines of the low-pressure pull rod leading out the dummy shaft and the pull sleeve coincide, the stretching value measured by the distance meter is controlled at 0.66-0.813mm.

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