Method of assembling an engine rotor for dynamic stress testing and assembly structure

Abstract

The application discloses an engine rotor assembling method and structure for dynamic stress test. The engine rotor is assembled safely and reliably without changing the dynamic balance performance of the engine rotor by adopting a connecting anti-loosening device including a spring, a connecting sleeve tooth, an adjusting ring and a connecting screw, and using a connecting screw wrench to connect and install the connecting anti-loosening device installed in a cavity.

Description

Technical Field

[0001] This invention relates to the field of turbine engine rotor assembly, and more specifically, to an assembly method and assembly structure for an engine rotor used for dynamic stress testing. Background Technology

[0002] Compressor blades are critical components of aero engines, but also prone to failure. To ensure engine safety, dynamic stress testing and analysis are typically performed on the blades during the engine design phase to assess and determine the permissible stress levels and durability under all operating conditions. Since the combustion chamber is located between the compressor and turbine, and the turbine shaft is generally designed as a hollow, long shaft, performing dynamic stress testing and analysis on compressor blades using a rear-lead wire method presents challenges such as long signal transmission distances and structural complexity. The lead wires and related components must be blind-mounted within deep holes in the turbine shaft, which may affect the dynamic balance of the engine rotor.

[0003] Typically, the compressor rotor and turbine rotor of a single-rotor engine are combined via a spline connection to achieve torque transmission. For example, CN201210196589.8 discloses a power transmission mechanism for a compressor and turbine, which uses a turbine with straight trapezoidal back teeth and a compressor impeller with straight trapezoidal end teeth meshing together in a compressor impeller-to-turbine back tooth transmission mechanism, and a turbine shaft end conical nut locking device that uses a conical locking nut that engages with the housing to axially lock and mesh with a gear ring for transmission. Assembly is the final step in ensuring the engine's dynamic balance characteristics. Currently, engine assembly largely relies on worker experience, and the assembly process can easily affect the dynamic balance performance of the engine rotor. Therefore, how to safely and reliably assemble the engine rotor without altering its dynamic balance performance is a significant challenge currently faced by rear-lead systems. Summary of the Invention

[0004] The technical problem to be solved by the present invention is that the connection between the elastic shaft of the existing engine and the front journal of the compressor rotor is difficult to ensure precise stability due to the large length-to-diameter ratio. The present invention provides a turbine engine rotor assembly method for dynamic stress testing.

[0005] Another technical problem solved by the present invention is to provide a turbine engine rotor assembly structure for dynamic stress testing.

[0006] The objective of this invention is achieved through the following technical solution:

[0007] An assembly method for an engine rotor used in dynamic stress testing, comprising the following steps:

[0008] S1. Assemble the compressor rotor assembly and perform dynamic balancing;

[0009] Install the front lead tube assembly and test lead in the test lead assembly onto the compressor rotor, and then perform dynamic balancing;

[0010] S2. Assemble the turbine rotor assembly and perform dynamic balancing;

[0011] Install the rear lead tube assembly from the test lead assembly onto the turbine rotor, and then perform dynamic balancing;

[0012] S3. Assemble the engine rotor;

[0013] S31. Install the compressor rotor onto the engine casing, install the turbine shaft onto the rear journal of the compressor rotor, lead the test lead out from the inner cavity of the turbine shaft, and sequentially put the spring, connecting sleeve teeth, adjusting ring and connecting screw of the anti-loosening device onto the test lead, and push them into the inner cavity of the turbine shaft and the rear journal from the rear end of the turbine shaft;

[0014] S32. Place the push rod of the connecting screw wrench onto the test lead and push it into the inner cavity of the turbine shaft until the push rod contacts the end face of the connecting sleeve teeth. The external thread of the screw sleeve end is screwed into the internal thread of the connecting screw. The toothed sleeve meshes with the end teeth on the connecting screw. Press the socket wrench onto the connecting screw and put the pressure sleeve on the push rod so that the push rod presses against the connecting sleeve teeth and compresses the spring, forcing the connecting sleeve teeth to remain a certain distance away from the connecting screw. Tighten the connecting screw by turning the connecting screw wrench to connect the turbine shaft to the rear journal of the compressor rotor.

[0015] S33. After removing the pressure sleeve, under the reaction force of the spring, the connecting sleeve teeth retract and enter the connecting screw. The small external spline of the connecting sleeve teeth engages with the internal spline of the connecting screw, and the large external spline engages with the internal spline of the rear journal. The connecting screw is locked on the rear journal.

[0016] S34. After removing the connecting screw wrench, put the rear lead tube assembly on the test lead and install it into the inner cavity of the turbine shaft. Then install the turbine disk and turbine blades onto the turbine shaft, thus completing the assembly of the engine rotor.

[0017] Furthermore, the specific steps for assembling the compressor rotor and performing dynamic balancing in S1 include:

[0018] S11. Assemble the compressor discs of each stage in sequence, and at the same time pass the test leads through the compressor discs of each stage and fix them on the inner wall of the compressor discs of each stage;

[0019] S12. Install the front lead tube assembly in the rear journal, and then assemble them together on the rear end face of the compressor wheel assembly. Test the lead wires by passing through the center of the front lead tube assembly.

[0020] S13. Install the compressor blades onto the compressor wheel assembly and connect the test leads to the strain gauges on the compressor blades;

[0021] S14. After bending the flexible test lead extending from the rear journal into multiple strands, insert it into the lead sleeve. The lead sleeve is then tightened and fixed to the rear end of the rear journal by external thread.

[0022] S15. Place the above components on the dynamic balancing machine to complete the dynamic balancing of the compressor rotor, and then remove the wire sleeve.

[0023] Furthermore, the connecting screw wrench includes a push rod, a pressure sleeve, a screw, a nut, a socket wrench, and a toothed sleeve. The push rod is a hollow round tube, and the screw is fitted onto the outer wall of the push rod. One end of the screw is provided with a detachable pressure sleeve, and the other end is provided with an external thread that can be screwed into the internal thread of the connecting screw. The outer wall of the screw is provided with a toothed sleeve, and the end face of the toothed sleeve is provided with a toothed surface that meshes with the end teeth of the connecting screw. The toothed sleeve is provided with a socket wrench and a ring for centering the connecting screw wrench in the inner cavity of the turbine shaft.

[0024] An assembly structure for an engine rotor used for dynamic stress testing includes a compressor rotor assembly, a turbine rotor assembly, a connection anti-loosening device, and a test lead assembly. The connection anti-loosening device connects the rear journal of the compressor rotor assembly and the turbine shaft of the turbine rotor assembly. The test lead assembly is provided in the inner cavity of the compressor rotor assembly and the turbine rotor assembly.

[0025] Furthermore, the rear journal of the compressor rotor is provided with an internal spline and an internal thread in its cavity, and an external spline on its outer wall.

[0026] Furthermore, one end of the turbine shaft is provided with an internal spline that matches the external spline on the outer wall of the rear journal of the compressor rotor.

[0027] Furthermore, the connection anti-loosening device includes a spring, a connecting sleeve tooth, an adjusting ring, and a connecting screw. The connecting sleeve tooth is connected to the rear journal of the compressor rotor. A compression spring is provided on one side of the connecting sleeve tooth, and the other side of the connecting sleeve tooth is connected to one side of the connecting screw. The other side of the connecting screw is pressed against the turbine shaft on the end face of the rear journal, and an adjusting ring is provided at the point where the connecting screw and the rear journal are pressed together.

[0028] Furthermore, the two ends of the connecting sleeve have different pipe diameters. The end with the larger pipe diameter is provided with a large external spline that meshes with the internal spline of the rear journal, while the end with the smaller pipe diameter is provided with a small external spline that meshes with the internal spline of the connecting screw.

[0029] Furthermore, the outer wall of the connecting screw is provided with an external thread that engages with the internal thread of the rear axle journal, one end of the connecting screw cavity is provided with an internal spline, the cavity is provided with an internal thread, and the other end of the connecting screw is provided with an external flange, the end face of the external flange is provided with end teeth.

[0030] Furthermore, the test lead assembly includes a front lead tube assembly, a rear lead tube assembly, and a test lead, with the ends of the front lead tube assembly and the rear lead tube assembly connected, and the test lead placed inside the cavities of the front lead tube assembly and the rear lead tube assembly.

[0031] Compared with existing technologies, the beneficial effects are:

[0032] In the engine rotor assembly process, this invention uses a connecting screw wrench inserted into the turbine shaft cavity. A push rod contacts the end face of the connecting sleeve teeth, and the external thread of the screw sleeve end screws into the internal thread of the connecting screw. The sleeve meshes with the end teeth on the connecting screw. The socket wrench is pressed against the connecting screw. The push rod presses against the connecting sleeve teeth and compresses the spring, forcing the connecting sleeve teeth to remain a certain distance away from the connecting screw. By turning the connecting screw wrench, the connecting screw is tightened, connecting the turbine shaft to the rear journal of the compressor rotor. After removing the pressure sleeve, the spring force causes the connecting sleeve teeth to retract into the connecting screw. The small external spline of the connecting sleeve teeth meshes with the internal spline of the connecting screw, and the large external spline meshes with the internal spline of the rear journal. The connecting screw is locked onto the rear journal. This invention ensures safe and reliable assembly of the engine rotor without altering its dynamic balance. Attached Figure Description

[0033] Figure 1 A schematic diagram of the engine rotor assembly structure used for dynamic stress testing;

[0034] Figure 2 This is a structural diagram of the turbine shaft;

[0035] Figure 3 This is a structural diagram of the rear axle journal.

[0036] Figure 4 Structural diagram of the anti-loosening device;

[0037] Figure 5 This is a diagram of the connecting sleeve structure;

[0038] Figure 6 This is a structural diagram of the connecting screw;

[0039] Figure 7 Diagram of the test lead assembly;

[0040] Figure 8 Diagram of a connecting screw wrench;

[0041] Figure 9 Diagram of a connecting screw wrench;

[0042] Figure 10 Diagram of the compressor rotor dynamic balancing assembly;

[0043] Figure 11 This is a diagram of the turbine rotor dynamic balancing assembly.

[0044] The components include: 1. Rear journal; 101. Rear journal external spline; 102. Rear journal internal spline; 103. Rear journal internal thread; 2. Turbine shaft; 201. Turbine shaft internal spline; 3. Spring; 4. Connecting sleeve tooth; 401. Large external spline; 402. Small external spline; 5. Adjusting ring; 6. Connecting screw; 601. Connecting screw internal spline; 602. Connecting screw external thread; 603. Connecting screw internal thread; 604. End tooth; 7. Test lead assembly; 701. Front lead tube assembly; 702. Rear lead tube assembly; 703. Test lead; 8. Push rod; 9. Screw; 901. Screw external thread; 10. Tooth sleeve; 11. Socket wrench; 12. Pressure sleeve; 13. Ring; 14. Nut. Detailed Implementation

[0045] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0046] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, and back), these directional indications are only used to explain the relative positional relationships and movement of the components in a specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indications will also change accordingly. If the embodiments of the present invention involve descriptions such as "first" and "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, features defined with "first" and "second" may explicitly or implicitly include at least one of those features.

[0047] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "connected," etc., should be interpreted broadly. For example, "connection" 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 an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0048] Example 1

[0049] like Figure 1This embodiment provides a structure for an engine rotor, including a compressor rotor assembly, a turbine rotor assembly, a connection anti-loosening device, and a test lead 703 assembly 7. The connection anti-loosening device connects the rear journal 1 of the compressor rotor assembly and the turbine shaft 2 of the turbine rotor assembly. The test lead 703 assembly 7 is provided in the cavity of the rear journal 1 and the turbine shaft 2.

[0050] like Figure 2 The compressor rotor has an internal spline 102 and an internal thread 103 inside the rear journal 1, and an external spline 101 on the outer wall.

[0051] like Figure 3 One end of the turbine shaft 2 is provided with an internal spline 201 that matches the external spline 101 of the rear journal of the compressor rotor.

[0052] like Figure 4 The connection anti-loosening device includes a spring 3, a connecting sleeve tooth 4, an adjusting ring 5, and a connecting screw 6. The connecting sleeve tooth 4 is connected to the rear journal 1 of the compressor rotor. A compression spring 3 is provided on one side of the connecting sleeve tooth 4, and the other side of the connecting sleeve tooth 4 is connected to one side of the connecting screw 6. The other side of the connecting screw 6 is pressed against the turbine shaft 2 on the end face of the rear journal 1, and an adjusting ring 5 is provided at the pressing point between the connecting screw 6 and the rear journal 1.

[0053] like Figure 5 The two ends of the connecting sleeve 4 have different pipe diameters. The end with the larger pipe diameter is provided with a large external spline 401 that meshes with the internal spline 102 of the rear axle journal, and the end with the smaller pipe diameter is provided with a small external spline 402 that meshes with the internal spline 601 of the connecting screw.

[0054] like Figure 6 The outer wall of the connecting screw 6 is provided with a connecting screw external thread 602 that engages with the internal thread 103 of the rear axle journal. One end of the connecting screw 6 cavity is provided with a connecting screw internal spline 601 and a connecting screw internal thread 603. The other end of the connecting screw 6 is provided with an outward flange, and the end face of the outward flange is provided with an end tooth 604.

[0055] like Figure 7 The test lead 703 assembly 7 includes a front lead tube assembly 701, a rear lead tube assembly 702 and a test lead 703. The front lead tube assembly 701 and the rear lead tube assembly 702 are connected at their ends, and the test lead 703 is placed in the cavity of the front lead tube assembly 701 and the rear lead tube assembly 702.

[0056] Example 2

[0057] This embodiment provides an installation tool for connecting screw wrenches based on Embodiment 1, such as... Figure 8-9 The connecting screw wrench includes a push rod 8, a pressure sleeve 12, a screw 9, a nut 14, a socket wrench 11, and a toothed sleeve 10.

[0058] The top rod 8 is a hollow round tube, and the middle can be used to test the passage of the lead wire 703 assembly 7.

[0059] The pressure sleeve 12 includes a sleeve and a cylindrical pin. The sleeve is a hollow, multi-segmented cylinder. The inner cavity of the sleeve consists of four progressively larger cylindrical surfaces. The first cylindrical surface has the same diameter as the inner hole of the push rod 8 and is used to thread the test lead. The second cylindrical surface has a clearance fit with the outer cylindrical surface of the push rod 8. The third and fourth cylindrical surfaces have a clearance fit with the screw 9. The outer surface of the sleeve consists of two cylindrical surfaces, on which a cylindrical pin is provided. The cylindrical pin is flush with the outer cylindrical surface of the sleeve and is used to hook the screw 9.

[0060] The screw 9 is fitted onto the outer wall of the top rod 8, with a gap between them for easy disassembly and assembly. One end of the screw 9 has L-shaped holes evenly distributed around its circumference for mounting the cylindrical pins on the pressure sleeve 12, and the other end has an external screw thread 901 that can be screwed into the internal thread 603 of the connecting screw.

[0061] The toothed sleeve 10 is disposed on the outer wall of the screw 9, and one end face of the toothed sleeve 10 is provided with a toothed surface that meshes with the end tooth 604 of the connecting screw 6.

[0062] The socket wrench 11 is mounted on the toothed sleeve 10 and is fixed by the nut 14 to restrict its axial displacement.

[0063] The inner surface of the ring 13 is in contact with the outer cylindrical surface of the gear sleeve 10, and the outer surface is in contact with the inner cavity of the rear end of the turbine shaft 2. The ring 13 is installed as a support block at the rear end opening of the turbine shaft 2, and the connecting screw wrench is placed in the inner cavity of the turbine shaft 2 to play a centering role.

[0064] Example 3

[0065] This embodiment provides an assembly method for an engine rotor used in dynamic stress testing, based on the engine rotor assembly structure of Embodiment 1 and the manual assembly of the connecting screw wrench in Embodiment 2. Figure 10-11 The steps include:

[0066] S1. Assemble the compressor rotor and perform dynamic balancing;

[0067] S11. Assemble the compressor discs of each stage in sequence, and at the same time pass the test lead 703 through the compressor discs of each stage and fix it on the inner wall of the compressor discs of each stage;

[0068] S12. Install the front lead tube assembly 701 in the rear journal 1, and then assemble them together on the rear end face of the compressor wheel assembly. Test lead 703 passes through the center of the front lead tube assembly 701.

[0069] S13. Install the compressor blades onto the compressor wheel assembly and connect the test lead 703 to the strain gauge on the compressor blades;

[0070] S14. The flexible test lead 703 extending from the rear axle journal 1 is bent into multiple strands and then inserted into the wire sleeve. The wire sleeve is tightened and fixed to the rear end of the rear axle journal 1 by external thread.

[0071] S15. Place the above components on the dynamic balancing machine to complete the dynamic balancing of the compressor rotor, and then remove the wire sleeve.

[0072] S2. Assemble the turbine rotor and perform dynamic balancing;

[0073] S21. Install the rear lead tube assembly 702 in the turbine shaft 2, and then assemble it together with the turbine disk and turbine blades.

[0074] S22. Place the above components on a dynamic balancing machine to complete the dynamic balancing of the turbine rotor, and then remove the turbine shaft 2 and the rear lead-in pipe assembly 702 respectively.

[0075] S3. Assemble the engine rotor;

[0076] S31. Install the compressor rotor onto the engine casing, install the turbine shaft 2 onto the rear journal 1 of the compressor rotor, and lead the test lead 703 out from the inner cavity of the turbine shaft 2. Sequentially put the spring 3, connecting sleeve tooth 4, adjusting ring 5, and connecting screw 6 of the anti-loosening device onto the test lead 703, and push them into the inner cavity of the turbine shaft 2 and the rear journal 1 from the rear end of the turbine shaft 2.

[0077] S32. Place the push rod 8 of the connecting screw wrench onto the test lead 703 and push it into the inner cavity of the turbine shaft 2 until the push rod 8 contacts the end face of the connecting sleeve tooth 4. The external thread 901 of the screw at the end of the screw 9 is screwed into the internal thread 603 of the connecting screw. The tooth sleeve 10 meshes with the end tooth 604 on the connecting screw 6. The socket wrench 11 is pressed on the connecting screw 6. The pressure sleeve 12 is placed on the push rod 8 so that the push rod 8 presses against the connecting sleeve tooth 4 and compresses the spring 3, forcing the connecting sleeve tooth 4 to remain a certain distance away from the connecting screw 6. Tighten the connecting screw 6 by turning the connecting screw wrench to connect the turbine shaft 2 and the rear journal 1 of the compressor rotor together.

[0078] S33. After removing the pressure sleeve 12, under the reaction force of the spring 3, the connecting sleeve tooth 4 retracts into the connecting screw 6. The small external spline 402 of the connecting sleeve tooth 4 engages with the internal spline 601 of the connecting screw, and the large external spline 401 engages with the internal spline 102 of the rear axle journal. The connecting screw 6 is locked on the rear axle journal 1.

[0079] S34. After removing the connecting screw wrench, put the rear lead tube assembly 702 onto the test lead 703 and install it into the inner cavity of the turbine shaft 2. Then install the turbine disk and turbine blades onto the turbine shaft 2, thus completing the assembly of the engine rotor.

[0080] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A method for assembling an engine rotor for dynamic stress testing, characterized in that, The assembly method uses a connecting screw wrench. The connecting screw wrench includes a push rod, a pressure sleeve, a screw, a nut, a socket wrench, and a toothed sleeve. The push rod is a hollow round tube. The screw is fitted onto the outer wall of the push rod. One end of the screw is provided with a detachable pressure sleeve, and the other end is provided with an external thread that can be screwed into the internal thread of the connecting screw. The outer wall of the screw is provided with a toothed sleeve. The end face of the toothed sleeve is provided with a toothed surface that meshes with the end teeth of the connecting screw. The toothed sleeve is provided with a socket wrench and a ring for centering the connecting screw wrench in the inner cavity of the turbine shaft. Assembly steps include: S1. Assemble the compressor rotor assembly and perform dynamic balancing; Install the front lead tube assembly and test lead in the test lead assembly onto the compressor rotor, and then perform dynamic balancing; S2. Assemble the turbine rotor assembly and perform dynamic balancing; Install the rear lead tube assembly from the test lead assembly onto the turbine rotor, and then perform dynamic balancing; S3. Assemble the engine rotor; S31. Install the compressor rotor onto the engine casing, install the turbine shaft onto the rear journal of the compressor rotor, lead the test lead out from the inner cavity of the turbine shaft, and sequentially put the spring, connecting sleeve teeth, adjusting ring and connecting screw of the anti-loosening device onto the test lead, and push them into the inner cavity of the turbine shaft and the rear journal from the rear end of the turbine shaft; S32. Place the push rod of the connecting screw wrench onto the test lead and push it into the inner cavity of the turbine shaft until the push rod contacts the end face of the connecting sleeve teeth. The external thread of the screw is screwed into the internal thread of the connecting screw, and the toothed sleeve meshes with the end teeth on the connecting screw. Press the socket wrench onto the connecting screw, put the pressure sleeve on the push rod, so that the push rod presses against the connecting sleeve teeth and compresses the spring, forcing the connecting sleeve teeth to remain a certain distance away from the connecting screw. Tighten the connecting screw by turning the connecting screw wrench to connect the turbine shaft to the rear journal of the compressor rotor. S33. After removing the pressure sleeve, under the reaction force of the spring, the connecting sleeve teeth retract and enter the connecting screw. The small external spline of the connecting sleeve teeth engages with the internal spline of the connecting screw, and the large external spline engages with the internal spline of the rear journal. The connecting screw is locked on the rear journal. S34. After removing the connecting screw wrench, put the rear lead tube assembly on the test lead and install it into the inner cavity of the turbine shaft. Then install the turbine disk and turbine blades onto the turbine shaft, thus completing the assembly of the engine rotor.

2. The assembly method of the engine rotor for dynamic stress testing according to claim 1, characterized in that, The specific steps for assembling the compressor rotor and performing dynamic balancing in S1 include: S11. Assemble the compressor discs of each stage in sequence, and at the same time pass the test leads through the compressor discs of each stage and fix them on the inner wall of the compressor discs of each stage; S12. Install the front lead tube assembly in the rear journal, and then assemble them together on the rear end face of the compressor wheel assembly. Test the lead wires by passing through the center of the front lead tube assembly. S13. Install the compressor blades onto the compressor wheel assembly and connect the test leads to the strain gauges on the compressor blades; S14. After bending the flexible test lead extending from the rear journal into multiple strands, insert it into the lead sleeve. The lead sleeve is then tightened and fixed to the rear end of the rear journal by external thread. S15. Place the above components on the dynamic balancing machine to complete the dynamic balancing of the compressor rotor, and then remove the wire sleeve.

3. The assembly method of the engine rotor for dynamic stress testing according to claim 1, characterized in that, The assembly structure includes a compressor rotor assembly, a turbine rotor assembly, a connection anti-loosening device, and a test lead assembly. The connection anti-loosening device connects the rear journal of the compressor rotor assembly and the turbine shaft of the turbine rotor assembly. The test lead assembly is provided in the inner cavity of the compressor rotor assembly and the turbine rotor assembly.

4. The assembly method of the engine rotor for dynamic stress testing according to claim 3, characterized in that, The compressor rotor has an internal spline and internal thread inside the rear journal cavity, and an external spline on the outer wall.

5. The assembly method of the engine rotor for dynamic stress testing according to claim 3, characterized in that, One end of the turbine shaft is provided with an internal spline that matches the external spline on the outer wall of the rear journal of the compressor rotor assembly.

6. The assembly method of the engine rotor for dynamic stress testing according to claim 3, characterized in that, The connection anti-loosening device includes a spring, a connecting sleeve tooth, an adjusting ring, and a connecting screw. The connecting sleeve tooth is connected to the rear journal of the compressor rotor. A compression spring is provided on one side of the connecting sleeve tooth, and the other side of the connecting sleeve tooth is connected to one side of the connecting screw. The other side of the connecting screw is pressed against the turbine shaft on the end face of the rear journal, and an adjusting ring is provided at the pressing point between the connecting screw and the rear journal.

7. The assembly method of the engine rotor for dynamic stress testing according to claim 6, characterized in that, The two ends of the connecting sleeve have different diameters. The end with the larger diameter is provided with a large external spline that meshes with the internal spline of the rear axle journal, while the end with the smaller diameter is provided with a small external spline that meshes with the internal spline of the connecting screw.

8. The assembly method of the engine rotor for dynamic stress testing according to claim 6, characterized in that, The outer wall of the connecting screw is provided with an external thread that meshes with the internal thread of the rear axle journal. One end of the connecting screw cavity is provided with an internal spline and an internal thread. The other end of the connecting screw is provided with an external flange, and the end face of the external flange is provided with end teeth.

9. The assembly method of the engine rotor for dynamic stress testing according to claim 3, characterized in that, The test lead assembly includes a front lead tube assembly, a rear lead tube assembly, and a test lead. The front lead tube assembly and the rear lead tube assembly are connected at their ends, and the test lead is placed inside the cavity of the front lead tube assembly and the rear lead tube assembly.

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