Aero-engine metal sealing ring vibration test method

Abstract

The invention belongs to the technical field of sealing ring vibration test, and particularly relates to an aero-engine metal sealing ring vibration test method, which comprises the following steps of: clamping a sealing ring based on a tool, and simulating an installation environment of the sealing ring; vibration excitation is applied to the excitation preset area of the tool clamping the sealing ring based on a vibration exciter to simulate the vibration environment of the aero-engine under the actual working condition, and vibration data are collected in the measurement preset area of the tool; according to the invention, the sealing ring is subjected to vibration excitation in the X direction, the Y direction and the Z direction based on the vibration exciter, and after the influence of the excitation is measured, the vibration test under the condition of a functional vibration test spectrum and a durability vibration test spectrum in three orthogonal directions of the metal sealing ring can be completed; it is determined that the sealing ring can work normally in the vibration environment, and any damage which may cause failure of parts due to exposure in the vibration environment is confirmed.

Description

Technical Field

[0001] The invention belongs to the technical field of sealing ring vibration testing, and in particular relates to a vibration testing method for a metal sealing ring of an aero-engine. Background Art

[0002] The vibration test method is a test method that simulates the actual working environment of electrical, electronic, automotive parts and other products and goods involved in transportation to identify whether the product can withstand environmental vibration. It is applicable to research, development, quality control and manufacturing in all walks of life. Existing vibration tests include sine vibration test, random vibration test, impact vibration test, environmental vibration test, etc.

[0003] The existing vibration test method for aircraft engine accessories consists of a vibration exciter, a support, a connector, a horizontal slide and a vertical table. In order to meet the vibration requirements in different directions at the same time, it is necessary to configure another vibration exciter or manually adjust the vibration direction of the vibration exciter. As a result, the test error is increased and the test cost is also increased.

[0004] Therefore, it is necessary to develop a method that can perform vibration tests in three degrees of freedom. Summary of the invention

[0005] In view of this, the present invention provides a vibration test method for a metal sealing ring of an aircraft engine, which simulates the installation environment of the sealing ring based on a tooling, and performs vibration excitation on the sealing ring in the X direction, Y direction and Z direction based on a vibration exciter. After measuring the influence of the excitation, vibration testing under the conditions of a functional vibration test spectrum and a durability vibration test spectrum along three orthogonal directions of the metal sealing ring can be completed to determine whether the sealing ring can work normally in a vibration environment and confirm any damage that may cause component failure caused by exposure to the vibration environment.

[0006] The technical solution of the present invention:

[0007] A vibration test method for a metal sealing ring of an aircraft engine, comprising:

[0008] The sealing ring is clamped by a tool to simulate the installation environment of the sealing ring;

[0009] Applying vibration excitation to the predetermined excitation area of ​​the tooling clamping the sealing ring based on the vibration exciter to simulate the vibration environment of the actual working conditions of the aircraft engine, and collecting vibration data in the predetermined measurement area of ​​the tooling;

[0010] evaluating the performance and durability of the sealing ring based on the vibration data;

[0011] Wherein: the tooling supports the vibration exciter to perform vibration excitation on the sealing ring in the X direction, the Y direction and the Z direction.

[0012] Furthermore, the vibration direction of the excitation point of the exciter is on a straight line parallel to the horizontal plane, and is used to generate sinusoidal excitation, square wave excitation, triangle wave excitation and white noise random excitation.

[0013] Furthermore, the tooling includes an upper clamping plate and a lower clamping plate, both of which are disc-shaped and have the same diameter; a coaxial annular groove is provided on at least one of the upper clamping plate and the lower clamping plate; the annular groove is adapted to the size of the sealing ring; when clamping the sealing ring, the sealing ring is clamped between the coaxial upper clamping plate and the lower clamping plate, and a part of the sealing ring is engaged in the annular groove.

[0014] Furthermore, a gasket is provided on at least one of the upper clamping plate and the lower clamping plate, and when the tool clamps the sealing ring, the gasket separates the upper clamping plate and the lower clamping plate to simulate the installation gap of the sealing ring on the aircraft component.

[0015] Furthermore, the tooling is hoisted based on two tie rods respectively cooperating with two hoisting rings; the tie rods support the tooling to move in the X direction, the Y direction and the Z direction.

[0016] Furthermore, the aviation engine metal sealing ring vibration test method specifically includes the following steps:

[0017] S101: clamping the sealing ring based on the tooling;

[0018] S102: hoisting the tooling based on the hoisting ring, ensuring that the tooling is parallel to the excitation direction of the exciter, and one corner of the tooling contacts the exciter as a first excitation point; installing a signal collector with the diagonal point of the first excitation point on the tooling as a first collection point, activating the exciter and recording the first vibration data after being transmitted through the sealing ring based on the signal collector;

[0019] S103: adjusting the lifting ring and the pull rod, rotating the tooling 90° along the main axis of the tooling, taking the contact angle between the tooling and the exciter as the second excitation point, and taking the diagonal point of the second excitation point on the tooling as the second collection point to collect second vibration data;

[0020] S104: adjusting the lifting ring and the pull rod, turning the tooling 90 degrees along the radial direction of the tooling, and making one corner of the tooling contact the exciter as a third excitation point, and collecting third vibration data with the diagonal point of the third excitation point on the tooling as a third collection point;

[0021] S105: Calculate the working performance of the sealing ring based on the first vibration data, the second vibration data and the third vibration data.

[0022] Furthermore, the excitation methods for the first excitation point, the second excitation point and the third excitation point include sinusoidal frequency sweep test, and the excitation frequencies are 15.7-31.4 Hz, 31.4-62.8 Hz, 70.0-142.7 Hz, 235.1-417.7 Hz and 352.4-874.5 Hz.

[0023] Furthermore, the excitation method for the first excitation point, the second excitation point and the third excitation point also includes a random vibration test, and the excitation frequencies are 20-300 Hz and 300-2000 Hz.

[0024] Furthermore, the signal collector is an accelerometer; and the conversion of the excitation point on the tooling is achieved based on the movement of the pull rod controlled by a stepper motor.

[0025] Furthermore, the height of the gasket is determined based on the axial height of the sealing ring.

[0026] Beneficial effects of the present invention:

[0027] This embodiment controls the fixture to move back and forth in three degrees of freedom by means of a stepper motor, thereby solving the problem that the centers of the vibrator and the fixture cannot be aligned when they are installed and connected, and improving the accuracy of the test.

[0028] This embodiment adopts a suspension method, which can accurately simulate the vibration environment of the aircraft engine in actual flight, minimize the interference of clamping resonance, and monitor the sealing ring response in real time through sensors. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0030] Figure 1 Vibration test flow chart

[0031] Figure 2 This is the installation diagram for the X-axis vibration test;

[0032] Figure 3 This is the installation diagram for the Y-axis excitation test;

[0033] Figure 4 This is the installation diagram for the Z-axis vibration test;

[0034] Figure 5 It is the time domain waveform and FFT spectrum diagram in the 15.7-31.4 frequency band in the X direction;

[0035] Figure 6It is the time domain waveform and FFT spectrum diagram in the frequency band of 31.4-62.8 in the X direction;

[0036] Figure 7 It is the time domain waveform and FFT spectrum diagram in the frequency band of 70.0-142.7 in the X direction;

[0037] Figure 8 It is the time domain waveform and FFT spectrum diagram in the frequency band of 70.0-142.7 in the X direction;

[0038] Fig. 9 It is the time domain waveform and FFT spectrum diagram in the frequency band of 70.0-142.7 in the X direction;

[0039] Fig.10 It is the power spectrum density curve of 20-300Hz in the X direction;

[0040] Fig.11 It is the power spectrum density curve of 300-2000Hz in the X direction;

[0041] Fig.12 It is a schematic diagram of the structure of the tooling;

[0042] Fig.13 It is a schematic diagram of the structure of the upper clamping plate or the lower clamping plate;

[0043] Among them: 1. Support platform; 2. Vibrator; 3. Tooling; 4. Lifting ring; 5. Ring groove; 6. Gasket. DETAILED DESCRIPTION

[0044] The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.

[0045] The following describes the embodiments of the present disclosure through specific examples, and those skilled in the art can easily understand other advantages and effects of the present disclosure from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all of the embodiments. The present disclosure can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present disclosure.

[0046] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present disclosure, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0047] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present disclosure. The illustrations only show components related to the present disclosure rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0048] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0049] Metal sealing rings are mostly used in aircraft engines to play a sealing role, and their sealing effect is closely related to the safe operation and operating efficiency of aircraft engines. According to the AES100 engine sealing ring technical agreement, parts need to be subjected to vibration tests in the assembled state. The embodiment of the present invention studies and develops a vibration test method for metal sealing rings, using the vibration test parameters of commercial engines as the standard, that is, completing vibration tests under the conditions of functional vibration test spectra and durability vibration test spectra along three orthogonal directions of the metal sealing ring, to determine whether the sealing ring can work normally in a vibration environment and confirm any damage caused by exposure to a vibration environment that may cause component failure. Commercial engines need to obtain airworthiness certification, and all accessories are required to undergo vibration damage tests, including metal sealing rings. In the development of future aircraft engines, vibration damage tests for metal sealing rings will also become a trend. The demand for testing the working performance indicators of metal sealing rings in a vibration environment will become an inevitable trend.

[0050] In one embodiment of the present invention, a vibration test method for a metal sealing ring of an aircraft engine is provided, comprising:

[0051] The sealing ring is clamped based on the tool 3 to simulate the installation environment of the sealing ring;

[0052] Apply vibration excitation to the predetermined excitation area of ​​the tooling 3 clamping the sealing ring based on the vibration exciter 2 to simulate the vibration environment of the actual working conditions of the aircraft engine, and collect vibration data in the predetermined measurement area of ​​the tooling 3;

[0053] evaluating the performance and durability of the sealing ring based on the vibration data;

[0054] Wherein: the tooling 3 supports the vibration exciter 2 to perform vibration excitation on the sealing ring in the X direction, the Y direction and the Z direction.

[0055] In this embodiment, the vibration direction of the excitation point of the exciter 2 is on a straight line parallel to the horizontal plane, and is used to generate sinusoidal excitation, square wave excitation, triangle wave excitation and white noise random excitation.

[0056] In this embodiment, if Fig.12 As shown, the tooling 3 includes an upper clamping plate and a lower clamping plate both of which are disc-shaped and have the same diameter; Fig.13 As shown, a coaxial annular groove 5 is provided on at least one of the upper clamping plate and the lower clamping plate; the annular groove 5 is adapted to the size of the sealing ring; when the sealing ring is clamped, the sealing ring is clamped between the coaxial upper clamping plate and the lower clamping plate, and a part of the sealing ring is engaged in the annular groove 5.

[0057] In this embodiment, a gasket 6 is provided on at least one of the upper clamping plate and the lower clamping plate. When the tooling 3 clamps the sealing ring, the gasket 6 separates the upper clamping plate and the lower clamping plate to simulate the installation gap of the sealing ring on the aircraft component.

[0058] In this embodiment, the tooling 3 is hoisted based on two tie rods respectively cooperating with two hoisting rings 4; the tie rods support the tooling 3 to move in the X direction, the Y direction and the Z direction.

[0059] In this embodiment, the aviation engine metal sealing ring vibration test method specifically includes the following steps:

[0060] S101: clamping the sealing ring based on the tooling 3;

[0061] S102: The tooling 3 is hoisted based on the hoisting ring 4, ensuring that the tooling 3 is parallel to the excitation direction of the exciter 2, and one corner of the tooling 3 contacts the exciter 2 as a first excitation point; a signal collector is installed with the diagonal point of the first excitation point on the tooling 3 as a first collection point, the exciter 2 is activated, and the first vibration data after being transmitted through the sealing ring is recorded based on the signal collector;

[0062] S103: adjusting the lifting ring 4 and the pull rod, rotating the tool 3 390° along the main axis of the tool 3, taking the contact angle between the tool 3 and the exciter 2 as the second excitation point, and taking the diagonal point of the second excitation point on the tool 3 as the second collection point to collect second vibration data;

[0063] S104: adjusting the lifting ring 4 and the pull rod, turning the tooling 3 by 390° along the radial direction of the tooling 3, and making one corner of the tooling 3 contact the exciter 2 as a third excitation point, and collecting third vibration data with the diagonal point of the third excitation point on the tooling 3 as a third collection point;

[0064] S105: Calculate the working performance of the sealing ring based on the first vibration data, the second vibration data and the third vibration data.

[0065] In this embodiment, the excitation method for the first excitation point, the second excitation point and the third excitation point includes a sine frequency sweep test, and the excitation frequencies are 15.7-31.4 Hz, 31.4-62.8 Hz, 70.0-142.7 Hz, 235.1-417.7 Hz and 352.4-874.5 Hz.

[0066] In this embodiment, the excitation method for the first excitation point, the second excitation point and the third excitation point further includes a random vibration test, and the excitation frequencies are 20-300 Hz and 300-2000 Hz.

[0067] In this embodiment, the signal collector is an accelerometer; the switching of the excitation point on the tooling 3 is achieved based on the stepper motor controlling the movement of the pull rod.

[0068] In this embodiment, the height of the gasket 6 is determined based on the axial height of the sealing ring.

[0069] This embodiment simulates the vibration environment of the aircraft engine under actual working conditions by applying vibration excitation. The signal generator generates a signal, which is amplified by the power amplifier and acts on the exciter 2.

[0070] The exciter 2 excites the load, and the exciter 2 is equipped with an accelerometer at a corresponding position of the load;

[0071] In this embodiment, data is collected online through a data collector. After the collection is completed, data analysis is performed in an industrial computer. The principle of the vibration test system is as follows: Figure 1As shown. Specifically, the following steps are included: Step 1: Select a suitable pad, install the metal sealing ring and the special tooling 3 fixture; Step 2: Adjust the fixture position through the rocker arm to align it with the exciter 2 and connect it, and install a sensor at the other end of the fixture to monitor the response of the sealing ring during the vibration process in real time; Step 3: Set the vibration test input parameters (such as vibration frequency and amplitude); Step 4: Start the vibration test and calculate the vibration duration and collect the vibration signal; Step 5: Evaluate the performance and durability of the sealing ring based on the data analysis results.

[0072] Core Program:

[0073] Use metal sealing ring vibration fixture lifting solution (such as Figure 2 As shown in the figure, the vibration fixture and the metal sealing ring are directly excited by the exciter 2, which eliminates the installation platform required by the general passability vibration test bench and greatly reduces the vibration test cost.

[0074] During the vibration test, the required voltage signal input amplitude was measured through the metal sealing ring vibration input parameter index verification test. On this basis, the exciter 2 was connected to the fixture using the given voltage amplitude, and the connection was tightened using the screw and the locking nut to ensure that the accelerometer and the screw were on the same horizontal line. The accelerometer was excited in the X, Y, and Z directions respectively to test the range of amplitude that the metal sealing ring could reach under load.

[0075] This embodiment controls the fixture to move back and forth in three degrees of freedom by means of a stepper motor, thereby solving the problem that the center of the vibrator 2 cannot be aligned when being installed and connected with the fixture, and improving the accuracy of the test.

[0076] This embodiment adopts a suspension method, which can accurately simulate the vibration environment of the aircraft engine in actual flight, minimize the interference of clamping resonance, and monitor the sealing ring response in real time through sensors.

[0077] The present invention is further described below based on clamping, parameter setting and vibration testing in three directions:

[0078] Clamping

[0079] X-direction vibration test: Install the specimen and the vibration fixture 3 on the vibration test bench. Figure 2 shown.

[0080] Y-direction vibration test: adjust the test piece and the vibration fixture 3 horizontally by 90° and install them on the vibration test bench. Figure 3 shown.

[0081] Z-direction vibration test: Install the specimen and the vibration fixture 3 on the vibration test bench. Figure 4 shown.

[0082] Parameter settings

[0083] (1) Sine frequency sweep test

[0084] ①The frequency range of the sine signal is adjustable in 2Hz~2KHz and 20Hz~20KHz.

[0085] ② Use manual and automatic frequency adjustment.

[0086] ③Linear and logarithmic modes.

[0087] ④Output waveform frequency LED digital display.

[0088] ⑤It has the functions of sine wave, square wave, triangle wave and white noise output.

[0089] ⑥It has output amplitude voltage meter indication.

[0090] (2) Random vibration spectrum test

[0091] The exciter 2 is driven by a white noise signal to generate a random vibration spectrum. The white noise power spectrum density is a constant noise in the entire frequency domain, and all frequencies have the same random noise energy density.

[0092] ①Amplifier gain adjustment

[0093] Coarse adjustment: This is a potentiometer with a switch that has an approximately logarithmic characteristic. It is used to adjust the amplitude of the power amplifier output voltage and current. The switch is used to "reset" the instrument.

[0094] Fine adjustment: This is a lead potentiometer, which is used to slowly adjust the output voltage and current of the power amplifier.

[0095] ②Current limit adjustment

[0096] It is used to pre-adjust the output current effective value. The pre-adjusted current limit range can be adjusted between 3A and 12A.

[0097] ③Power switch

[0098] 220V50HZ power switch, the power indicator light will light up after the power is turned on.

[0099] X-direction vibration test

[0100] (1) Sine frequency sweep test

[0101] A. Frequency range (15.7-31.4Hz)

[0102] Adjust the voltage amplitude of the signal generator to 900mV, within the frequency range of 15.7-31.4Hz. Figure 4It can be seen that within one cycle, the amplitude changes evenly. From the spectrum diagram, we can see that at 28.3Hz, the maximum positive peak can reach about 2.02g. Figure 5 shown.

[0103] B. Frequency range (31.4-62.8Hz)

[0104] Adjust the voltage amplitude of the signal generator to 600mV, in the frequency range of 31.4-62.8, by Figure 5 It can be seen that at 32Hz, the maximum peak is 1.3g, such as Figure 6 shown.

[0105] C. Frequency range (70.0-142.7Hz)

[0106] Adjust the voltage amplitude of the signal generator to 1V, in the frequency range of 70.0-142.7, by Figure 6 It can be seen that at 70.3Hz, the maximum positive peak can reach 1.5g, such as Figure 7 shown.

[0107] D. Frequency range (235.1-417.7Hz)

[0108] Adjust the voltage amplitude of the signal generator to 3.2V, in the frequency range of 235.1-417.7, by Figure 7 It can be seen that at 236Hz, the peak value reaches about 2.2g, such as Figure 8 shown.

[0109] E. Frequency range (352.4-874.5Hz)

[0110] Adjust the voltage amplitude of the signal generator to 5V, in the frequency range of 352.4-874.5, by Figure 8 It can be seen that at 860Hz, the peak value reaches 15.3g, such as Fig. 9 shown.

[0111] (2) Random vibration test

[0112] A. Low frequency band (20-300Hz)

[0113] The test results show that in the low frequency range of 20-300 (Hz), Fig. 9 It can be obtained that the power spectrum density varies around 0.0003g2 / Hz, such as Fig.10 As shown;

[0114] B. High frequency band (300-2000Hz)

[0115] Depend on Fig.10It can be seen that in the high frequency band of 300-2000 (Hz), the power spectrum density has an obvious peak near 900Hz, which is close to the natural frequency of the fixture, such as Fig.11 shown.

[0116] Y direction vibration test

[0117] (1) Sine frequency sweep test

[0118] A. Frequency range (15.7-31.4Hz)

[0119] The voltage amplitude of the signal generator is adjusted to 900mV. In the frequency band of 15.7-31.4, at 29.8Hz, the maximum positive peak value can reach about 2.10g.

[0120] B. Frequency range (31.4-62.8Hz)

[0121] The voltage amplitude of the signal generator is adjusted to 600mV, and the maximum peak value is 1.4g at 35.2Hz in the frequency band of 31.4-62.8.

[0122] C. Frequency range (70.0-142.7Hz)

[0123] The voltage amplitude of the signal generator is adjusted to 1V. In the frequency band of 70.0-142.7, at 71.5Hz, the maximum positive peak value can reach 1.6g.

[0124] D. Frequency range (235.1-417.7Hz)

[0125] The voltage amplitude of the signal generator was adjusted to 3.2V. In the frequency band of 235.1-417.7, at 237Hz, the peak value reached about 2.29g.

[0126] E. Frequency range (352.4-874.5Hz)

[0127] The voltage amplitude of the signal generator was adjusted to 5V, and the peak value reached 17.4g at 873.2Hz in the frequency band of 352.4-874.5.

[0128] (2) Random vibration spectrum test

[0129] White noise refers to noise whose power spectral density is constant in the entire frequency domain, and random noise with the same energy density at all frequencies.

[0130] A. Low frequency band (20-300Hz)

[0131] The test results show that in the low frequency range of 20-300 (Hz), Figure 2-12It can be obtained that the power spectral density varies around 0.0002g2 / Hz.

[0132] B. High frequency band (300-2000Hz)

[0133] Depend on Figure 2-13 It can be seen that in the high frequency band of 300-2000 (Hz), the power spectrum density has an obvious peak near 900 Hz, which is close to the natural frequency of the fixture.

[0134] Z-direction vibration test

[0135] (1) Sine frequency sweep test

[0136] A. Frequency range (15.7-31.4Hz)

[0137] The voltage amplitude of the signal generator is adjusted to 900mV, and the amplitude changes evenly within the frequency range of 15.7-31.4 in one cycle. At 27.5Hz, the maximum positive peak value can reach about 1.83g.

[0138] B. Frequency range (31.4-62.8Hz)

[0139] The voltage amplitude of the signal generator was adjusted to 600 mV, and the maximum peak value was 1.2 g at 32.0 Hz in the frequency band of 31.4-62.8.

[0140] C. Frequency range (70.0-142.7Hz)

[0141] The voltage amplitude of the signal generator is adjusted to 1V. In the frequency band of 70.0-142.7, at 141.8Hz, the maximum positive peak value can reach 3.3g.

[0142] D. Frequency range (235.1-417.7Hz)

[0143] The voltage amplitude of the signal generator was adjusted to 3.2V. In the frequency band of 235.1-417.7, the test required the positive peak to reach 20.0g. At 236Hz, the peak reached about 55.5g.

[0144] (2) Random vibration spectrum test

[0145] White noise refers to noise whose power spectral density is constant in the entire frequency domain, and random noise with the same energy density at all frequencies.

[0146] A. Low frequency band (20-300Hz)

[0147] The test results show that in the low frequency range of 20-300 (Hz) and in the frequency band of 200-240 (Hz), the power spectrum density increases significantly.

[0148] B. High frequency band (300-2000Hz)

[0149] In the high frequency band of 300-2000 (Hz), several obvious peaks appear in the power spectrum density, which are related to the natural frequency of the fixture.

[0150] The above is only a specific implementation of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present disclosure should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. A vibration test method for a metal sealing ring of an aircraft engine, characterized in that: include: The sealing ring is clamped by a tool to simulate the installation environment of the sealing ring; Applying vibration excitation to the predetermined excitation area of ​​the tooling clamping the sealing ring based on the vibration exciter to simulate the vibration environment of the actual working conditions of the aircraft engine, and collecting vibration data in the predetermined measurement area of ​​the tooling; evaluating the performance and durability of the sealing ring based on the vibration data; Wherein: the tooling supports the vibration exciter to perform vibration excitation on the sealing ring in the X direction, the Y direction and the Z direction.

2. The method for vibration testing of metal sealing rings of aircraft engines according to claim 1, characterized in that: The vibration direction of the excitation point of the exciter is on a straight line parallel to the horizontal plane, and is used to generate sinusoidal excitation, square wave excitation, triangle wave excitation and white noise random excitation.

3. The method for vibration testing of metal sealing rings of aircraft engines according to claim 2, characterized in that: The tooling includes an upper clamping plate and a lower clamping plate, both of which are disc-shaped and have the same diameter; a coaxial annular groove is provided on at least one of the upper clamping plate and the lower clamping plate; the annular groove is adapted to the size of the sealing ring; when the sealing ring is clamped, the sealing ring is clamped between the coaxial upper clamping plate and the lower clamping plate, and a part of the sealing ring is engaged in the annular groove.

4. The method for vibration testing of metal sealing rings of aircraft engines according to claim 3, characterized in that: A gasket is provided on at least one of the upper clamping plate and the lower clamping plate. When the tool clamps the sealing ring, the gasket separates the upper clamping plate and the lower clamping plate to simulate the installation gap of the sealing ring on the aircraft component.

5. The method for vibration testing of metal sealing rings of aircraft engines according to claim 4, characterized in that: The tooling is hoisted based on two tie rods respectively cooperating with two hoisting rings; the tie rods support the tooling to move in the X direction, the Y direction and the Z direction.

6. The method for vibration testing of metal sealing rings of aircraft engines according to claim 5, characterized in that: The aeroengine metal sealing ring vibration test method specifically comprises the following steps: S101: clamping the sealing ring based on the tooling; S102: hoisting the tooling based on the hoisting ring, ensuring that the tooling is parallel to the excitation direction of the exciter, and one corner of the tooling contacts the exciter as a first excitation point; installing a signal collector with the diagonal point of the first excitation point on the tooling as a first collection point, activating the exciter and recording the first vibration data after being transmitted through the sealing ring based on the signal collector; S103: adjusting the lifting ring and the pull rod, rotating the tooling 90° along the main axis of the tooling, taking the contact angle between the tooling and the exciter as the second excitation point, and taking the diagonal point of the second excitation point on the tooling as the second collection point to collect second vibration data; S104: adjusting the lifting ring and the pull rod, turning the tooling 90 degrees along the radial direction of the tooling, and making one corner of the tooling contact the exciter as a third excitation point, and collecting third vibration data with the diagonal point of the third excitation point on the tooling as a third collection point; S105: Calculate the working performance of the sealing ring based on the first vibration data, the second vibration data and the third vibration data.

7. The method for vibration testing of metal sealing rings of aircraft engines according to claim 6, characterized in that: The excitation methods for the first excitation point, the second excitation point and the third excitation point include sinusoidal frequency sweep test, and the excitation frequencies are 15.7-31.4 Hz, 31.4-62.8 Hz, 70.0-142.7 Hz, 235.1-417.7 Hz and 352.4-874.5 Hz.

8. The method for vibration testing of metal sealing rings of aircraft engines according to claim 7, characterized in that: The excitation method for the first excitation point, the second excitation point and the third excitation point also includes a random vibration test, and the excitation frequencies are 20-300 Hz and 300-2000 Hz.

9. The method for vibration testing of metal sealing rings of aircraft engines according to claim 8, characterized in that: The signal collector is an accelerometer; the conversion of the excitation point on the tooling is achieved based on the stepper motor controlling the movement of the pull rod.

10. The method for vibration testing of metal sealing rings of aircraft engines according to claim 4, characterized in that: The height of the gasket is determined based on the axial height of the sealing ring.

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