A tensile testing device and method for an aircraft engine compressor rotor

Abstract

The present invention discloses a tensile testing device and method for an aero-engine compressor rotor. The present invention utilizes a low-pressure pull rod to lead out a dummy shaft, a tooling pull rod, and a pull sleeve to match the low-pressure pull rod end face, outer circle, and locking nut. During the rotation of the pull sleeve, the deformation of the low-pressure pull rod can be strictly controlled, and alignment of the calibration lines can be used to ensure that its assembly position meets the design requirements. At the same time, the present application can monitor the tensile amount and align the calibration lines through a rangefinder and a visual alignment device, thereby realizing data visualization during the assembly process, improving assembly quality and efficiency, and resolving issues such as the inability to visualize and digitize the rotor assembly tensile amount and the difficulty in matching assembly positions.

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's low-pressure compressor utilize a new, large-interference stop for centering and a face-to-face torque-transfer connection with a tightened low-pressure tie rod. During assembly, the rotor connection is reliably secured by controlling the residual deformation of the low-pressure tie rod and installing a locking collar. To ensure safe and stable engine operation, this residual deformation must be monitored during assembly.

[0003] A new turboprop engine rotor structure 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 lock nut. The first-stage compressor disc with a 2.5# bearing is connected to the second-stage compressor disc through an interference fit joint via the low-pressure tie rod. The lock nut compresses the 2.5# bearing via the tone wheel. During rotor assembly, the tightening torque of the bolts, nuts, and bearing lock nuts is a key factor in controlling the assembly state. CN201711054883.4 discloses an assembly method for an aircraft engine rotor. The method includes: Step A, assembling the rotor; Step B, providing a device comprising an outer support tube, an inner tie rod, a nut runner, a hydraulic pump, a dial indicator, and a handle; Step C, adjusting the transmission rod, installing the dial indicator, and adjusting the force applied by the dial indicator to the transmission rod to ensure stable contact between the transmission rod and the stepped 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. In step E, the hydraulic pump pressure is increased, the nut is tightened, and then the hydraulic pump pressure is removed. In step F, a pressure of 0.2 MPa is applied to the hydraulic pump and the dial indicator reading is checked. This patent design utilizes a device that simplifies the assembly process and improves assembly efficiency. However, the rotor stretching process requires strict control of the stretching amount. This device cannot monitor and measure key quality data in real time during the assembly process, and its assembly accuracy and quality stability cannot be 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 pull rod stretching measurement mechanism and a control system. The basic frame includes a base and a column, the base is fixedly installed 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 pull rod stretching measurement device are fixedly installed on the column, and the control system is fixedly installed behind the column. This patent realizes the automatic execution of rotor stretching action during the assembly process of the compressor rotor according to the assembly requirements of the aircraft engine compressor rotor components. At the same time, the real-time detection and collection of the tensile deformation data, analysis and decision-making of the 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 claws cannot be installed at the same time, it is necessary to re-apply load and tighten or unload and reload and 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, the process is cumbersome and uncontrollable, resulting in reduced installation efficiency, and 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 of existing aircraft engine rotor stretching that cannot be visualized, cannot be monitored at one time, and the locking block cannot be aligned with the locking groove 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 of 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 includes a low-pressure pull rod leading-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 leading-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. The low-pressure pull rod leading-out dummy shaft and the pull sleeve are provided with a calibration line; the hydraulic pump and the support bridge are fixedly connected, and the hydraulic pump and the support bridge are sleeved on the tooling pull rod, and the hydraulic pump and the tooling pull rod are fixedly connected by the tooling nut;

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

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

[0012] Furthermore, the distance meter is located just above the dummy shaft where the low-voltage pull rod leads out.

[0013] Furthermore, one end of the low-pressure pull rod leading-out dummy shaft is provided with an end face tooth opening that matches 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.

[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 aligning 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 locking 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 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.

[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 tensile testing 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 portion of one end of the low-pressure rod lead-out dummy shaft into the end face groove of the low-pressure rod of the aircraft engine compressor rotor. A calibration line is provided on the other end to calibrate the position of the low-pressure rod's locking block installation groove. Next, fit the tooling rod onto the outer wall of the low-pressure rod lead-out dummy shaft, connecting its internally threaded end with the external threads on the outer circumference of the low-pressure rod. Finally, fit the pull sleeve onto the tooling rod and simultaneously fit it onto the lock nut. The pull sleeve has a calibration line on its surface to calibrate the nut's installation angle.

[0024] S3. After fixing the hydraulic pump and the support bridge together, 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-pressure pull rod lead-out false shaft of the low-pressure pull rod lock block installation groove, and the second visual alignment device aligns the calibration line of the lock block installation position of the calibration 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 dial sleeve is turned to drive the locking nut to rotate 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-pressure pull rod lock block installation groove of the low-pressure pull rod lead-out false shaft calibration and the lock block installation position of the locking nut are aligned with the installation structure position of the lock block.

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

[0027] Furthermore, when the calibration lines of the dummy shaft led out of the low-pressure pull rod and the dial sleeve coincide with each other, 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 utilizes a low-pressure pull rod to lead out a false shaft, a tooling pull rod, and a pull sleeve to coordinate the low-pressure pull rod end face, outer diameter, and lock nut. During the rotation of the pull sleeve, the deformation of the low-pressure pull rod can be strictly controlled, and alignment of the calibration lines can be used to ensure that its assembly position meets the design requirements. Furthermore, the present invention can monitor the stretching amount and align the calibration lines using a rangefinder and a visual alignment device, achieving data visualization during the assembly process and improving assembly quality and efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0032] Figure 3 This 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 tensile 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 devices, 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 rack. DETAILED DESCRIPTION

[0036] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall 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 the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of such features.

[0038] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "provided with," "connected," etc., should be understood in a broad sense. For example, "connected" may refer to a fixed connection, a detachable connection, or an integral connection; it may refer to a mechanical connection or an electrical connection; it may refer to a direct connection or an indirect connection through an intermediate medium; it may refer to internal communication between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in the present invention based on the 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 pull rod lead-out dummy shaft 201, a tooling pull rod 202, a hydraulic pump 204, a support bridge 205, and a shifting sleeve 203. One end of the low-pressure pull rod lead-out dummy shaft 201 is connected to the end face of the low-pressure pull rod 104. The tooling pull rod 202 fits over the low-pressure pull rod lead-out dummy shaft 201 and is connected to the outer wall of the low-pressure pull rod 104. The shifting sleeve 203 fits over the outer wall of the tooling pull rod 202 and can be connected to the locking nut 103 on the low-pressure pull rod 104. The hydraulic pump 204 is fixedly connected to the support bridge 205, and the hydraulic pump 204 and the support bridge 205 fit over the tooling pull rod 202. The hydraulic pump 204 and the tooling pull rod 202 are fixedly connected via a tooling nut 206.

[0042] The stretching device 2 is fixed to a fixture frame 5. A laser rangefinder 3 is installed above the fixture frame 5. The laser rangefinder 3 is located at the low-pressure tie rod lead-out dummy shaft 201 and measures the end surface displacement of the low-pressure tie rod lead-out dummy shaft 201. The fixture frame 5 is also equipped with a visual alignment device to detect the rotational offset of the low-pressure tie rod lead-out dummy shaft 201 and the fixture tie 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 end face teeth that match the end face notch of the low-pressure pull rod 104, and the other end is provided with a calibration line that calibrates the installation groove position of the locking block 102 of the low-pressure pull rod 104. The tooling pull rod 202 fits onto 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 that matches the outer wall thread of the low-pressure pull rod 104. The pull sleeve 203 fits onto the outer wall of the tooling pull rod 202 and is capable of fitting with the locking nut 103 on the low-pressure pull rod 104. The pull sleeve 203 is provided with a calibration line that calibrates 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 aligning the calibration line of the low-pressure tie rod leading out the dummy shaft 201 and 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 fitted onto the tooling tie rod 202. The hydraulic pump 204 and the tooling tie rod 202 are fixedly connected by a tooling nut 206.

[0046] like Figure 3 As shown, the stretching device 2 is fixed to the fixture frame 5. A laser rangefinder 3 is installed above the fixture frame 5. The laser rangefinder 3 is located on the central axis of the power cylinder, support bridge 205, fixture rod 202, and pull sleeve 203. It measures the displacement of the end face of the pressure rod lead-out dummy shaft. An upper camera 401 is installed above the fixture frame 5 to detect the calibration line at the connection between the fixture rod 202 and the low-pressure rod lead-out dummy shaft 201. A lower camera 402 is also installed below the fixture frame 5 to detect the calibration line on the pull sleeve 203 and fixture rod 202. The hydraulic pump 204, upper camera 401, lower camera 402, and 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 is 0.66-0.813 mm. The detection steps include:

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

[0051] S2. Install the toothed portion of one end of the low-pressure rod lead-out dummy shaft 201 into the end face groove of the low-pressure rod 104 of the aircraft engine compressor rotor. A calibration line is provided on the other end to mark the installation groove position of the locking block 102 of the low-pressure rod 104. Then, fit the tooling rod 202 onto the outer wall of the low-pressure rod lead-out dummy shaft 201, so that its internally threaded end connects with the external thread of the outer circumference of the low-pressure rod 104. Then, fit the pull sleeve 203 onto the tooling rod 202 and simultaneously fit the pull sleeve 203 onto the lock nut 103. The surface of the pull sleeve 203 has a calibration line to mark the nut installation angle.

[0052] S3. The hydraulic pump 204 and support bridge 205 are securely assembled and fitted onto the tooling tie rod 202. The tooling tie rod 202 and the hydraulic pump 204 are connected via the tooling nut 206. The upper camera 401 is then used to calibrate the alignment of the low-pressure tie rod lead-out dummy shaft 201 and the upper portion of the tooling tie rod 202. The hydraulic pump 204 pressure value 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 marking line on the low-voltage rod leading out of the dummy shaft 201, which leads to the low-voltage rod 104 and the locking block 102 mounting groove. The lower camera 402 is aligned with the position marking line on the locking block 102 mounting position, which marks the locking nut 103. Because the locking nut 103 may be offset from its mounting position, the locking block 102 may not be aligned with the locking nut 103 mounting position in the locking block 102 mounting groove. Therefore, the marking lines of the upper and lower cameras 401 and 402 are not aligned. 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 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. Depressurize 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 the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. An aircraft engine compressor rotor tensile testing device, characterized in that: Including stretching device, distance meter, visual alignment device and control system; The stretching device includes a low-pressure pull rod leading-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 leading-out dummy shaft. One end of the low-pressure pull rod leading-out dummy shaft is provided with an end face tooth mouth that matches the low-pressure pull rod end face groove of the aircraft engine compressor rotor. 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. 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. The low-pressure pull rod leading-out dummy shaft and the pull sleeve are provided with a calibration line; the hydraulic pump and the support bridge are fixedly connected, and the hydraulic pump and the support bridge are sleeved on the tooling pull rod, and the hydraulic pump and the tooling pull rod are fixedly connected by the tooling nut; The stretching device is fixed on the tooling frame, and the tooling frame is provided with a rangefinder for measuring the displacement of the low-voltage pull rod leading out dummy shaft. The tooling frame is also provided with a visual alignment device for detecting the alignment of the tooling pull rod and the calibration line on the low-voltage pull rod leading out dummy shaft. 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 pull rod and the low-voltage pull rod leading out dummy shaft, and the second visual alignment device detects the alignment of the dial sleeve and the calibration line on the tooling pull rod. An upper camera for detecting the alignment line between the fixture pull rod and the low-voltage pull rod leading out of the dummy shaft is provided above the fixture frame, and a lower camera for detecting the alignment line between the dial sleeve and the fixture pull rod is provided below the fixture frame. The hydraulic pump, visual alignment device and rangefinder are connected to a control system.

2. The aero-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 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 that matches the outer wall thread of the low-pressure pull rod of the compressor rotor of the aircraft engine.

4. 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 the low-pressure pull rod to lead out the false shaft and the sleeve calibration line to coincide.

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

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

7. A method for tensile testing of an aircraft engine compressor rotor, characterized in that: The detection method is implemented based on the aircraft engine compressor rotor tensile detection device according to any one of claims 1 to 6, and the steps include: S1. Thread the second-stage rotor to the low-pressure rod. Then, place the first-stage rotor over the low-pressure rod to achieve an interference fit between the first-stage and second-stage rotors. Slip the tone wheel onto the first-stage rotor and tighten the lock nut onto the low-pressure rod until the lock nut contacts the tone wheel. S2. Install the toothed portion of one end of the low-pressure tie rod leading out of the dummy shaft in the end face groove of the low-pressure tie rod of the aircraft engine compressor rotor. The other end is provided with a calibration line to calibrate the position of the locking block installation groove of the low-pressure tie rod. Then, the tooling tie rod is sleeved on the outer wall of the low-pressure tie rod leading out of the 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. Then, the pull sleeve is sleeved on the tooling tie rod and the pull sleeve is simultaneously sleeved on the lock nut. The pull sleeve surface is provided with a calibration line to calibrate the nut installation angle. S3. After fixing the hydraulic pump and the support bridge, fit the combination on 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 turn on the hydraulic pump. S4. The first visual alignment device aligns the calibration line of the low-pressure pull rod leading out false shaft of the low-pressure pull rod lock block installation groove, and the second visual alignment device aligns the calibration line of the lock block installation position of the calibration lock nut. There is an offset in the installation position of the lock nut, which causes the lock block to be unable to be aligned with the installation position of the lock 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 dial sleeve is turned to drive the lock nut to rotate 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-pressure pull rod lock block installation groove calibrated by the low-pressure pull rod leading out false shaft and the lock block installation position of the lock nut are aligned with the installation structure position of the lock block; S5. Depressurize the hydraulic cylinder, disassemble the tensile testing device, install the locking block and safety on the locking nut, and complete the rotor assembly.

8. The method for tensile testing of an aircraft engine compressor rotor according to claim 7, characterized in that: When the calibration lines of the dummy shaft and the dial sleeve led out by the low-pressure pull rod coincide, the stretching value measured by the distance meter is controlled within 0.66-0.813mm.

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