A method for testing a thin-walled drum of an aero-engine in rotation

Abstract

The application belongs to the field of aero-engine excitation test, and is a rotating excitation test method for a thin-walled drum cylinder of an aero-engine. Strain gauges are pasted on the outer wall cylinder surface, the root of the grid tooth and the tooth tip position of the three-stage drum cylinder, the test rotor is assembled, and then the simulated turbine shaft head is docked with the test platform. The excitation load of a specific engine order is applied to the three-stage disc real blades of the rotating thin-walled drum cylinder, the vibration response of the thin-walled drum cylinder in the resonance speed range is obtained in the form of vibration transmission, the damping sheet is installed on the inner wall of the three-stage drum cylinder in the circumferential direction, the rotating excitation test of the thin-walled drum cylinder in the second round of damping state is carried out, and the vibration response of the thin-walled drum cylinder in the resonance range is obtained again. The vibration suppression effect of the current type damping sheet on the thin-walled drum cylinder can be evaluated by comparing the results of the two rounds of rotating excitation tests of the thin-walled drum cylinder. The problem that the existing component rotating excitation tester cannot study the vibration characteristics of the thin-walled drum cylinder is solved.

Description

Technical Field

[0001] This application belongs to the field of aero-engine vibration testing, and specifically relates to a method for rotating vibration testing of a thin-walled drum of an aero-engine. Background Technology

[0002] Aero-engine sealing structures are designed to control airflow leakage between rotor and stator stages; effective sealing can significantly improve aero-engine efficiency. With the advent of high-performance turbines and compressors, various design methods have been used to improve the efficiency of aero-engine sealing structures, such as higher grate lengths and smaller blade tip clearances. However, this also leads to higher dynamic loads being applied to the sealing structure, which can easily cause high-cycle fatigue failure of related structures.

[0003] Aero engines typically feature serrated seals on their thin-walled drums. Due to airflow vibration, the rotating drum usually experiences several pitch diameter / pitch circle vibration modes within the engine's design speed range. This can cause crack initiation at the tips of the long serrations, which can lead to crack propagation and ultimately, drum failure. Compared to high-cycle fatigue issues in blades, high-cycle fatigue problems in rotating thin-walled drums are more difficult to detect.

[0004] Due to cost considerations, attempting to solve the entire high-cycle fatigue problem through whole-engine testing is impractical. Therefore, a dynamic rotating test bench with an excitation system offers a solution. The HCF excitation system of the dynamic rotating test bench includes a drive shaft 1, a vibration test piece 2 located at the output end of the drive shaft 1, a vibration load application device 3 that applies loads to the drive test piece, and a lubricating oil circulation system. The dynamic rotating test bench can simulate the static and dynamic environments in the engine flow path, excluding aerodynamic loads, such as… Figure 1 As shown, rotational speed, temperature field, and excitation factors can all be simulated simultaneously. Therefore, by using a component-level rotating vibration tester, the dynamic characteristics and potential HCF (High-Frequency Combustion Failure) of the thin-walled drum can be determined, and evaluation parameters can be provided for design modifications in the early stages of engine development. Furthermore, the vibration reduction effect of the damping structure can be evaluated, which can reduce engine development costs and shorten the development cycle.

[0005] However, existing HCF excitation systems have the following drawbacks:

[0006] Technical aspects

[0007] For excitating rotating blades, the liquid jet excitation method is commonly used. This involves arranging a series of nozzles around the test rotor, with the jet direction perpendicular to the rotor's rotational plane, causing the jet to be sprayed axially onto the blades. During the test, a continuous mist of liquid is ejected from the nozzles, impacting designated locations on the rotating blades. Upon contact with the blades, the liquid's kinetic energy generates an impact force. The circumferentially distributed and fixed nozzles create a specific frequency excitation force relative to the rotating blades. By controlling the number of nozzles and the rotor's rotational speed, a specific modal resonance response of the blades can be generated. By controlling the flow rate and pressure of the liquid at the nozzles, the amplitude of the excitation force can be adjusted, thereby controlling the magnitude of the resonance response.

[0008] Currently, for rotating thin-walled drums, since the drum's rotation center is coaxial with the engine and the test equipment's drive shaft, it is impossible to use axial injection excitation methods to excite the coaxially rotating thin-walled drum based on existing test equipment. Figure 2 As shown, the injector 5 on the injector boom 4 cannot axially spray the high-speed lubricating oil jet 6 onto the target vibration location. If a vibration excitation method involving radial injection along the drum is used, it will be impossible to generate the specific engine-order vibration load, such as... Figure 3 As shown, the nozzle 5 on the injection rod 4 sprays a high-speed lubricating oil jet 6 radially onto the target vibration location. However, this also prevents the study of the vibration characteristics of a thin-walled drum under rotating test conditions.

[0009] Cost

[0010] If the method of injecting excitation lubricating oil radially along the thin-walled drum is adopted, an additional set of auxiliary drums that rotate synchronously with the thin-walled drum needs to be designed. The auxiliary drums are machined with the same number of holes in the circumferential direction as the excitation engine. Figure 4 As shown. The liner drum is assembled between the nozzle and the thin-walled drum. When the test piece and the liner drum rotate together, the lubricating oil jet ejected from the nozzle will periodically spray onto the thin-walled drum through the circumferential through-hole on the liner drum, forming a certain engine-order excitation load.

[0011] However, the outer diameter of the surrogate drum is larger than that of the test drum. The strength design of the thin-walled drum of the aero-engine has approached the strength boundary of the material. In order to ensure that the surrogate drum does not fail before the test drum during high-speed rotation, the design is difficult, the material selection cost is high, the processing cost is high, and the strength reserve of the surrogate drum is low, and the risk of rotor explosion is high during the test.

[0012] In terms of efficiency

[0013] To collect dynamic stress data for the thin-walled drum and sealing grates, strain gauges need to be attached to the surface of the drum and grates. When using a liner drum for testing, lubricating oil is periodically sprayed onto the drum surface. The high-speed oil jets damage the strain gauges attached to the thin-walled drum and sealing grates, resulting in short strain gauge lifespans and the inability to collect or only collecting a small amount of test data. The test piece then needs to be removed from the test bench, disassembled, reattached, balanced, and tested again, resulting in repeated testing cycles that are lengthy and inefficient.

[0014] Therefore, how to study the vibration characteristics of thin-walled drums under rotating test conditions is a problem that needs to be solved. Summary of the Invention

[0015] The purpose of this application is to provide a rotational excitation test method for thin-walled drums of aero-engines, in order to solve the problem that existing rotational excitation tests cannot achieve the study of vibration characteristics of thin-walled drums under rotational test conditions.

[0016] The technical solution of this application is: a method for rotary excitation testing of thin-walled drums of aero-engines, comprising:

[0017] Strain gauges were attached to the three-stage drum at three locations: the outer wall of the drum, the root of the grate teeth, and the tip of the grate teeth.

[0018] The booster stage rotor assembly is assembled, which includes a second-stage disc, a second-stage disc assembly block, a third-stage disc, and actual third-stage disc blades.

[0019] Connect the booster stage rotor assembly with the three-stage drum to the simulated turbine shaft head, and then connect the plug, lock nut and locking plate respectively; after assembly, install the dynamic stress test lead along the reliable position of the rotor assembly with strain gauges and apply oil protection measures.

[0020] The simulated turbine shaft head is connected to the test platform via the leading and trailing edge variable excitation system. When the trailing edge excitation scheme is adopted, the simulated turbine shaft head is connected to the upper stop positioning surface and the lower stop positioning surface of the leading and trailing edge variable excitation system by bolts.

[0021] Without installing damping plates on the inner wall of the three-stage drum, a first round of undamped rotational excitation tests of the thin-walled drum was conducted to obtain the vibration response of the thin-walled drum within its resonant speed range. Then, with damping plates installed circumferentially on the inner wall of the three-stage drum, a second round of damped rotational excitation tests of the thin-walled drum was conducted to obtain the vibration response of the thin-walled drum within its resonant speed range.

[0022] By comparing and analyzing the vibration response data of the thin-walled drum in the two rounds of tests, the amplitude of vibration response change under each section diameter / section circle vibration mode of the thin-walled drum was obtained, and the vibration reduction effect of the current type of damping plate on the thin-walled drum was evaluated.

[0023] Preferably, at least two sets of strain gauges are attached to the outer surface of the three-stage drum, the root of the comb teeth, and the tip of the comb teeth, respectively.

[0024] Preferably, the variable excitation system for the leading and trailing edges includes a hollow drive shaft, a multi-functional vertical adapter flange, a clamp, and a pin; the hollow drive shaft is connected to the drive turbine of the component rotation excitation tester, and the multi-functional vertical adapter flange is fitted with the hollow drive shaft by an interference fit, with the multi-functional vertical adapter flange having a pin connection at the interference fit surface and being protected by a clamp.

[0025] Preferably, the secondary disc and the simulated turbine shaft head are coaxially sleeved and connected by bolts. The clamping structure of the secondary disc and the simulated turbine shaft head also includes a plug, a locking nut, and locking plates. A locking cavity is provided at the bottom of the simulated turbine shaft head. The top of the plug is inserted into the locking cavity, and the bottom abuts against the bottom surface of the simulated turbine shaft head. The locking nut is threaded onto the outer wall of the simulated turbine shaft head, and the top of the locking nut abuts against the secondary disc. There are multiple sets of locking plates, and the multiple sets of locking plates are evenly distributed along the circumference of the plug. Each set of locking plates is fixedly connected between the plug and the locking nut.

[0026] This application discloses a method for rotating vibration testing of a thin-walled drum of an aero-engine. First, strain gauges are circumferentially attached to the surface of the outer wall of the drum under test, as well as the tips and roots of the toothed ferrules. A rotating vibration test rotor for the thin-walled drum is then assembled by assembling the drum under test, the actual blades of the corresponding stage of the thin-walled drum, the counterweights of adjacent thin-walled drums and the corresponding stage of the thin-walled drum, and the test rotor transition section. Dynamic stress test leads are then installed on the strain gauges, and oil-proof protection measures are applied. The rotating vibration test rotor is then connected to a component rotating vibration tester, completing the test assembly. The test rotor is then tested and operated. When the vibration level of the test rotor is within the equipment vibration limit range, the test rotor can conduct the first round of rotating vibration testing of the thin-walled drum without dampers under lubricating oil excitation. The axially injected lubricating oil transmits the excitation load of a specific engine order to the thin-walled drum under test through the actual blades, thereby obtaining the vibration response of the thin-walled drum within its resonant speed range. Next, damping plates were installed on the inner wall of the thin-walled drum. A second round of rotational excitation tests on the thin-walled drum with damping plates was conducted under lubricating oil excitation to obtain the vibration response of the thin-walled drum within its resonant speed range. By comparing the test data from the two rounds, the vibration reduction effect of the current type of damping plate on the thin-walled drum can be effectively evaluated, solving the problem that existing component rotational excitation testers cannot study the vibration characteristics of thin-walled drums. Attached Figure Description

[0027] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0028] Figure 1 This is a schematic diagram of the excitation system structure of the component rotation excitation tester in the background art;

[0029] Figure 2 This is a schematic diagram of the axial injection of vibrating lubricating oil in the experimental device in the background art;

[0030] Figure 3 This is a schematic diagram of radial injection of vibrating lubricating oil in the experimental device in the background art;

[0031] Figure 4 This is a schematic diagram of a liner drum with a circumferential through-hole structure in the background art.

[0032] Figure 5 This is a schematic diagram of the mechanical scheme for the rotor in the thin-walled drum rotation excitation test of this application;

[0033] Figure 6 This is a schematic diagram of the variable excitation system for the leading and trailing edges in this application;

[0034] Figure 7 This is a schematic diagram showing the bonding position of the strain gauges in the rotational vibration test of the thin-walled drum in this application;

[0035] Figure 8 This is a schematic diagram of the rotational vibration test process for the thin-walled drum of an aero-engine in this application.

[0036] 1. Drive shaft; 2. Vibration test specimen; 3. Vibration load application device; 4. Injector rod; 5. Injector nozzle; 6. High-speed lubricating oil jet; 7. Simulated turbine shaft head; 8. Plug; 9. Locking nut; 10. Locking plate; 11. Third-stage disc; 12. Real blades of the third-stage disc; 13. Counterweight of the second-stage disc; 14. Second-stage drum; 15. Third-stage drum; 16. Hollow drive shaft; 17. Hoop; 18. Multifunctional vertical adapter flange; 19. Upper stop positioning surface; 20. Lower stop positioning surface; 21. Pin; 22. Grate tooth tip; 23. Grate tooth root; 24. Cylinder surface; 25. Inner wall of the third-stage drum; 26. Outer wall of the third-stage drum. Detailed Implementation

[0037] 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 some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] A Rotary Vibration Test Method for Thin-Walled Drums of Aero-Engine

[0039] like Figure 8 As shown, it includes the following steps:

[0040] Step S100: Design of load application scheme for thin-walled drum rotational vibration test

[0041] Thin-walled drum components in aero-engines are typically assembled between rotating disk stages, forming a grate-like gas path seal together with the stator. When designing the load application scheme for rotating vibration tests of thin-walled drums, to address the limitation of existing test setups for studying the vibration characteristics of rotating thin-walled drums, the rotating disk blades adjacent to the drum can be used. A specific engine-order excitation load can be first applied to the rotating disk blades. The rigid connection formed between the high-speed rotating blades and the drum under centrifugal force transmits the excitation load borne by the blades to the thin-walled drum through the disk. When the frequency of the excitation load coincides with a specific pitch diameter / pitch circle vibration mode frequency of the thin-walled drum, the drum will exhibit pitch diameter / pitch circle vibration under that specific mode.

[0042] A rotational vibration test was conducted on a thin-walled drum of a certain type of engine's third-stage drum, combined with... Figure 5 The booster stage rotor assembly includes: a secondary drum 14, a secondary disc counterweight 13, a tertiary drum 15 (the thin-walled drum to be tested), and actual blades 12 of the tertiary disc. The secondary disc assembly block 13 is installed between the secondary disc 14 and the tertiary disc 11.

[0043] A real blade 12 of the third-stage disk 11 is installed at the rim position. An excitation load of a specific engine order is applied to the real blade 12 of the third-stage disk along the rotational axis of the test rotor. Under the condition of high-speed rotation of the test rotor, the third-stage disk 11 and the real blade 12 of the third-stage disk are in a rigid connection state. Therefore, the excitation load of the specific engine order will be transmitted to the third-stage drum 15 (the thin-walled drum to be tested) through the blade.

[0044] Step S200: Design of the mechanical scheme for the rotor in the thin-walled drum rotational vibration test.

[0045] A rotational vibration test was conducted on a thin-walled drum of a certain type of engine's third-stage drum, combined with... Figure 5 When the excitation load is first applied to the blades of the rotating disk, and then the excitation load borne by the blades is transferred to the thin-walled drum through the disk, the secondary drum 14 adjacent to the third-stage drum 15 (the thin-walled drum under test) does not need to be equipped with actual blades. Instead, the secondary disk counterweight 13 is installed in place of the actual blades at the corresponding position on the disk. The first-stage drum and the corresponding disk do not participate in the assembly when conducting the rotational excitation test of the third-stage thin-walled drum.

[0046] The excitation load (axially injected lubricating oil jet) can be injected from either the leading edge or the trailing edge of the actual blade 12 of the third-stage disk. When the injection is selected from the leading edge of the actual blade 12 of the third-stage disk, the counterweight 13 of the second-stage disk, due to its small radial dimension, will not interfere with the excitation load. When the injection is selected from the trailing edge of the actual blade 12 of the third-stage disk, the axially injected lubricating oil jet will be directly recovered by the lubricating oil circulation system after impacting the actual blade 12 of the third-stage disk, and will not transmit the excitation load to the third-stage drum 15 (the thin-walled drum under test) through the counterweight 13 of the second-stage disk. Therefore, there will be no interference from multiple excitation loads.

[0047] The secondary disk 14 is connected to and tightened with the simulated turbine shaft head 7. The simulated turbine shaft head 7 is then connected to the test platform via the leading and trailing edge variable excitation system. Based on the axial length of the test rotor, the flange end of the simulated turbine shaft head 7 is connected to the upper stop positioning surface 19 and the lower stop positioning surface 20 of the leading and trailing edge variable excitation system. After the connection is tightened, the test platform can drive the drum excitation test rotor assembly to rotate via the hollow drive shaft 16 of the leading and trailing edge variable excitation system.

[0048] Preferably, the secondary disc 14 is coaxially sleeved with the simulated turbine shaft head 7 and connected by bolts to ensure convenience and stability. The clamping structure between the secondary disc 14 and the simulated turbine shaft head 7 also includes a plug 8, a locking nut 9, and locking plates 10. A locking cavity is provided at the bottom of the simulated turbine shaft head 7. The top of the plug 8 is inserted into the locking cavity, and the bottom abuts against the bottom surface of the simulated turbine shaft head 7. The locking nut 9 is threaded onto the outer wall of the simulated turbine shaft head 7, and the top of the locking nut 9 abuts against the secondary disc 14. There are multiple sets of locking plates 10, and these sets are evenly distributed along the circumference of the plug 8. Each set of locking plates 10 is fixedly connected between the plug and the locking nut 9. In this way, the plug 8 supports the locking nut 9 through the locking plates 10. Tightening the locking nut 9 can stably clamp the secondary disc 14, and the locking plates 10 prevent the components from loosening and rotating.

[0049] Step S300: Assembly and balancing of rotor assembly for thin-walled drum rotational vibration test

[0050] First, apply 15 patches to the three-stage drum tube (the thin-walled drum tube to be tested), combined with... Figure 7 Strain gauges were attached to points b and c on the outer wall 26 of the third-stage drum to measure the vibration response level of the surface of the thin-walled drum body; strain gauges were attached to points a and d on the outer wall 26 of the third-stage drum to measure the vibration response level of the root of the thin-walled drum tooth; strain gauges were attached to points f and g on the outer wall 26 of the third-stage drum to measure the vibration response level of the tip of the thin-walled drum tooth; the vibration response levels at the above three typical locations can be used to evaluate the strength reserve of the thin-walled drum.

[0051] Next, the booster stage rotor assembly is assembled.

[0052] Since the target excitation location is at the third-stage drum position, the booster stage rotor assembly can be tested without assembling the first-stage drum and matching blades.

[0053] Then, the rotor assembly for the thin-walled drum rotational vibration test was assembled and balanced.

[0054] The booster stage rotor assembly with the three-stage drum 15 (the thin-walled drum to be tested) is connected to the simulated turbine shaft head 7. Axial clamping between the assemblies is ensured by the plug 8 and locking nut 9, and loosening rotation is prevented by the locking plate 10. After assembly, strain gauges are installed along reliable positions on the rotor assembly with dynamic stress test leads, and oil-proof protection measures are applied. Next, a rotational excitation test of the thin-walled drum is performed to balance the rotor assembly.

[0055] Without damping plates installed along the circumferential direction on the inner wall of the third-stage drum 11, and with strain gauges installed along the circumferential direction on the outer wall of the third-stage drum 11, the first round of undamped rotational excitation test was conducted to obtain the vibration response of the thin-walled drum within the resonant speed range, and the vibration response results were recorded. After the first round of test, the test assembly was wiped, cleaned, and dried on the test platform to remove any residual lubricating oil from the inner and outer walls of the test assembly. Finally, the condition of the strain gauges was checked.

[0056] Then, damping plates were installed circumferentially on the inner wall of the third-stage drum 11, and a second round of damped rotational excitation test was carried out to obtain the vibration response of the thin-walled drum within the resonance range for the second time, and the vibration response results were recorded.

[0057] Step S400: Dating the rotor assembly of the thin-walled drum rotary vibration test to the test platform.

[0058] The assembled thin-walled drum rotary vibration test rotor assembly is docked with the test platform via a leading-edge and trailing-edge variable excitation system. Figure 5 and Figure 6 When using a trailing edge excitation scheme, the simulated turbine shaft head 7 needs to be bolted to the lower stop positioning surface 20 of the leading and trailing edge variable excitation system. Combined with... Figure 2 A specific number of fuel injector rods 4 are evenly arranged circumferentially to form a specific engine-level excitation load. A fuel injector nozzle 5 is installed on each fuel injector rod 4. The axial position of the fuel injector rod 4 is adjusted so that the nozzle orifice is positioned above the trailing edge of the actual blade 12 of the third-stage disk, with an axial distance of 10 mm. Then, the radial position of the nozzle orifice on the fuel injector rod 4 is adjusted so that the nozzle orifice is within the blade body of the actual blade 12 of the third-stage disk, maintaining a radial distance of 10 mm from the blade tip. The maximum excitation load is generated when the high-speed lubricating oil jet impacts the blade tip region of the actual blade 12 of the third-stage disk.

[0059] The leading and trailing edge variable excitation system includes a hollow drive shaft 16, a multi-functional vertical adapter flange 18, a clamp 17, and a pin 21. The hollow drive shaft 16 is connected to the drive turbine of the component rotation excitation tester. The multi-functional vertical adapter flange 18 is interference-fitted with the hollow drive shaft 16. The multi-functional vertical adapter flange 18 has a pin 21 connected at the interference fit surface and is protected by a clamp 17 to prevent the pin 21 from flying out and failing during high-speed operation. The upper end face of the multi-functional vertical adapter flange 18 is provided with an upper stop positioning surface 19, and the lower end face is provided with a lower stop positioning surface 20. After the test assembly is connected and tightened, the test platform can drive the thin-walled drum rotation excitation test rotor assembly to rotate through the hollow drive shaft 16 of the leading and trailing edge variable excitation system.

[0060] Within the full speed range specified in the test, under conditions of no lubricating oil excitation, the test rotor was debugged and operated to verify its balancing effect. When the vibration level of the test rotor is within the equipment vibration limit range, the balancing measures of the test rotor are considered qualified.

[0061] Next, the dynamic stress test lead inside the test rotor assembly needs to be led out from the inner hole of the hollow drive shaft 16 to the slip ring actuator to complete the transmission and conversion of the rotational signal and the stationary signal. After debugging the signal amplifier and data acquisition system, the thin-walled drum rotational vibration test can be carried out.

[0062] Step S500: Conduct a rotational excitation test on the thin-walled drum.

[0063] Combination Figure 7 Without installing damping plates on the inner wall 25 of the three-stage drum, the first round of undamped rotational excitation tests on the thin-walled drum was conducted to obtain the vibration response of the thin-walled drum within its resonant speed range. After completing the first round of tests, the test components were wiped, cleaned, and dried on the test platform to remove lubricating oil residue from the inner and outer walls of the test components, and finally the condition of the strain gauges was checked.

[0064] Next, damping plates were installed circumferentially on the inner wall 25 of the third-stage drum, and a second round of rotational excitation tests on the thin-walled drum with damping was conducted. The vibration response of the thin-walled drum within its resonant speed range was obtained.

[0065] Step S600: Compare and analyze the vibration response data of the thin-walled drum in the two rounds of tests. After statistical analysis, obtain the vibration response variation amplitude under each section diameter / section circle vibration mode of the thin-walled drum. This can effectively evaluate the vibration reduction effect of the current type of damping plate on the thin-walled drum.

[0066] This application involves attaching strain gauges to three locations on the outer wall 26 of the third-stage drum: the surface 24 of the drum body, the root 23 of the comb teeth, and the tip 22 of the comb teeth. Then, the third-stage drum 15 is connected to the adjacent second-stage drum 14. The corresponding disks of each drum stage are equipped with the actual blades 12 of the third-stage disk and the assembly blocks 13 of the second-stage disk, respectively. Then, they are connected to the simulated turbine shaft head 7 to complete the test rotor assembly. Finally, the simulated turbine shaft head 7 is docked with the test platform. Then, without installing damping plates on the inner wall 25 of the third-stage drum, a first round of undamped rotational excitation tests on the thin-walled drum was conducted. By applying a specific engine-order excitation load (i.e., a certain number of circumferentially distributed high-speed lubricating oil jets) to the actual blades 12 of the third-stage disk of the rotating thin-walled drum, vibration response at the target excitation position of the third-stage drum 15 was induced through vibration transmission, thereby obtaining the vibration response of the thin-walled drum within the resonant speed range. Then, with damping plates installed circumferentially on the inner wall 25 of the third-stage drum, a second round of damped rotational excitation tests on the thin-walled drum was conducted. Using the same vibration transmission path, the vibration response of the thin-walled drum within the resonant range was obtained again. By comparing the results of the two rounds of rotational excitation tests on the thin-walled drum, the vibration suppression effect of the current type of damping plate on the thin-walled drum can be evaluated. High-speed lubricating oil jets do not need to be directly sprayed onto the surface of thin-walled drums, solving the problems of short strain gauge survival time and insufficient test data collection in existing testing methods, which require repeated removal of the test piece and re-attaching of strain gauges. Part of the lubricating oil jet is atomized after impacting the rotating blades, while the remaining jet is directly collected by the lubricating oil collector of the component rotation vibration tester through the gaps between the blades, avoiding erosion of the strain gauges on the thin-walled drum surface and achieving a 100% strain gauge survival rate during the test. It also solves the problem that existing component rotation vibration testers cannot study the vibration characteristics of thin-walled drums, expanding the application boundaries of component rotation vibration testers; and addresses the problems of existing testing methods where the design, material selection, and processing of the test drum requires significant manpower and material resources, and the test drum has low strength reserves and a high risk of bursting during the test. The method of transferring excitation load based on the structure of the test rotor itself avoids complex structural design and ensures the structural reliability of the test rotor.

[0067] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change.

[0068] Secondly: The accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0069] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method of rotating impulse testing of a thin-walled drum of an aeroengine, characterized in that, The method comprises the following steps: Strain gauges are attached to the three-stage drum (15), and are attached to the cylinder surface (24), the comb tooth root (23) and the comb tooth tip (22) of the outer wall (26) of the three-stage drum; the three-stage drum (15) is a thin-walled drum to be measured; The pressurization stage rotor assembly is assembled, and the pressurization stage rotor assembly comprises a second-stage disc drum (14), a second-stage disc assembly block (13), a third-stage disc drum (11) and a third-stage disc real blade (12); The pressurization stage rotor assembly with the three-stage drum (15) is connected to the simulated turbine shaft head (7), and then the plug cover (8), the locking nut (9) and the locking plate (10) are connected respectively; after the assembly is completed, the strain gauges are installed along the reliable positions of the rotor assembly, and oil-proof protection measures are taken; The simulated turbine shaft head (7) is connected to the front edge and the rear edge variable excitation system through the upper stop opening positioning surface (19) and the lower stop opening positioning surface (20) of the front edge and the rear edge variable excitation system; when the rear edge excitation scheme is adopted, the simulated turbine shaft head (7) is connected to the front edge and the rear edge variable excitation system through the upper stop opening positioning surface (19) and the lower stop opening positioning surface (20) of the front edge and the rear edge variable excitation system; The damping sheet is not installed on the inner wall (25) of the three-stage drum, and the first round of thin-walled drum rotating excitation test in the undamped state is carried out; the vibration response of the target excitation position of the three-stage drum (15) is caused in a vibration transmission manner by applying the excitation load of a specific engine order to the three-stage disc real blade (12) of the rotating thin-walled drum; then the damping sheet is installed on the inner wall (25) of the three-stage drum in the circumferential direction, and the second round of thin-walled drum rotating excitation test in the damped state is carried out; the vibration response of the thin-walled drum in the resonance speed range thereof is obtained through the same vibration transmission path; The vibration response data of the thin-walled drum in the front and rear two rounds of tests are compared and analyzed, the vibration response change amplitude of the thin-walled drum in each pitch diameter or pitch circle vibration mode is obtained, and the damping effect of the current type damping sheet on the thin-walled drum is evaluated; The front edge and the rear edge variable excitation system comprises a hollow transmission shaft (16), a multifunctional vertical adapter flange (18), a hoop (17) and a pin (21); the hollow transmission shaft (16) is connected to the driving turbine of the component rotating excitation tester; the multifunctional vertical adapter flange (18) is connected to the hollow transmission shaft (16) through interference tightness cooperation, the multifunctional vertical adapter flange (18) is connected to the pin (21) at the interference tightness cooperation surface and is protected by the hoop (17).

2. The aeroengine thin-walled drum rotor spin excitation test method of claim 1, wherein: At least two groups of strain gauges are attached to the cylinder surface (24), the comb tooth root (23) and the comb tooth tip (22) of the outer wall (26) of the three-stage drum respectively.

3. The aeroengine thin-walled drum rotor spin excitation test method of claim 1, wherein: The secondary disc cylinder (14) is coaxially sleeved with the simulation turbine shaft head (7) and is connected through bolts, and the compression structure of the secondary disc cylinder (14) and the simulation turbine shaft head (7) further comprises a plug cover (8), a locking nut (9) and a locking plate (10); the bottom of the simulation turbine shaft head (7) is provided with a locking cavity, the top of the plug cover (8) is inserted into the locking cavity, the bottom of the plug cover (8) is abutted with the bottom surface of the simulation turbine shaft head (7), the locking nut (9) is threadedly connected to the outer wall of the simulation turbine shaft head (7), and the top of the locking nut (9) is abutted with the secondary disc cylinder (14), and the locking plates (10) are provided in multiple groups, and the multiple groups of locking plates (10) are uniformly arranged along the circumference of the plug cover (8), and each group of the locking plates (10) is fixedly connected between the plug cover and the locking nut (9).

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