Aero-engine vibration assessment test method and system

Abstract

The invention belongs to the technical field of aero-engine vibration tests, and particularly relates to an aero-engine vibration assessment test method and system. Comprising the following steps: determining the worst vibration environment of accessories; determining the staying rotating speed of an engine rotor and the staying time of the staying rotating speed; according to the staying rotating speed of the engine rotor and the staying time of the staying rotating speed, a vibration assessment test run spectrum is formulated; based on the worst accessory vibration environment, carrying out an engine complete machine test by referring to the vibration assessment test run spectrum; generating an engine rotating speed and vibration curve graph according to the whole engine test measurement data, and making an accessory vibration limit value; an accessory vibration assessment test is carried out on a complete engine, and the complete engine used in the accessory vibration assessment test simulates the possible maximum vibration environment and test temperature of accessories in a full operation cycle and a full rotation speed range; and the installation and vibration environment is more in line with the engineering practical situation.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engine vibration test, and particularly relates to a vibration assessment test method and system for aero-engines. Background Art

[0002] Components and accessories are generally installed on the aero-engine casing and will be affected by various vibration loads caused by engine rotor excitation and self-rotating component excitation during actual operation. To ensure that components and accessories will not experience structural damage due to vibration during long-term use and can stably perform their functions in different vibration environments, vibration assessment tests need to be carried out for each type of component and accessory.

[0003] The existing vibration assessment test method for components and accessories is as follows: First, an environmental vibration spectrum is formulated with reference to GJB150.16 or DO-160. This vibration spectrum specifies the vibration spectrum type, frequency range, and vibration amplitude. Then, the component and accessory are installed on a vibration table and the formulated environmental vibration spectrum is applied through the vibration table. Finally, according to the life requirements of the component and accessory (currently, the life of an engine is generally less than 1000 hours, and the requirements for components and accessories are higher), vibration assessment tests are carried out in at least 30 minutes in each of the three directions of horizontal, vertical, and axial directions, and the cumulative duration is not less than 3 hours.

[0004] The existing vibration assessment tests for engine components and accessories have the following disadvantages:

[0005] 1) The environmental vibration spectra for each type of component and accessory are the same, resulting in over-loose or over-strict assessment for some components and accessories. In fact, due to factors such as different installation positions on the engine casing and different self-weights of each type of component and accessory, the environmental vibration spectra are necessarily different.

[0006] 2) The test process is generally carried out at room temperature, and the influence of temperature factors cannot be considered. During actual operation, the temperature at the installation position of some components and accessories is above 300°C. High temperature has a relatively obvious impact on the stiffness, fatigue, and other characteristics of components and accessories. The existing tests cannot fully demonstrate that there will be no damage during actual operation.

[0007] 3) The test time is too long. There are generally about 40 types of engine components and accessories, so the cumulative test time will be not less than 120 hours. Summary of the Invention

[0008] In view of the above problems, the present invention proposes a vibration assessment test method for aero-engines, including:

[0009] Assembling the engine unit for component and accessory vibration assessment according to the most severe vibration environment of the component and accessory;

[0010] Determining the residence speed of the engine rotor and the residence time at the residence speed;

[0011] Formulate a vibration assessment test running spectrum according to the engine rotor's staying speed and the staying time of the staying speed;

[0012] Carry out the engine's overall machine test with reference to the vibration assessment test running spectrum.

[0013] Furthermore, the worst vibration environment of the accessories includes:

[0014] Set the worst unbalance of the engine rotor;

[0015] Set the worst unbalance of the rotating parts of the accessories themselves according to the level of the balance accuracy standard.

[0016] Furthermore, the determination of the engine rotor's staying speed specifically includes:

[0017] Obtain the minimum steady-state speed of the rotor as n 最小稳态 , the maximum steady-state speed as n 最大稳态 , the maximum transient speed as n 最大瞬态 , the system error of the rotor speed control as η 控制精度 and the overshoot of the rotor as η 超调 ;

[0018] According to n 最小稳态 , n 最大稳态 , n 最大瞬态 , η 控制精度 and η 超调 , obtain the minimum speed of the rotor as n min and the maximum speed as n max ;

[0019] According to n min and n max , obtain the engine rotor's staying speed.

[0020] Furthermore, the determination of the staying time of the staying speed specifically includes; according to the known engine rotor's staying speed being greater than 10 and the vibration residence times of the accessories being not less than 10 7 times; it is concluded that the vibration residence times of the accessories at each engine rotor's staying speed are not less than 10 6 times;

[0021] According to the engine rotor's staying speed and the vibration residence times of the staying speed, obtain the staying time of the staying speed.

[0022] Furthermore, at the end of the engine's overall machine test;

[0023] Generate a curve graph of the engine speed and vibration according to the measurement data of the engine's overall machine test, and formulate the vibration limit value of the accessories;

[0024] And decompose and inspect the finished accessories according to the quality inspection standards of the finished accessories.

[0025] Further, the vibration limit value of the finished accessories is formulated as follows: according to the engine overall test measurement data including the engine body vibration values at each dwell speed Sort them from largest to smallest, and the first K engine body vibration values are sequentially recorded as where K represents the number of engine body vibration values selected from largest to smallest; then calculate the vibration margin λ according to formula (1);

[0026]

[0027] Calculate the vibration limit value V of the finished accessories according to formula (2) 限制值 ;

[0028]

[0029] Further, according to n 最小稳态 , n 最大稳态 , n 最大瞬态 , η 控制精度 and η 超调 , obtain the minimum rotor speed n min and the maximum rotor speed n max , specifically,

[0030] Calculate the minimum rotor speed n min according to formula (3);

[0031] n min = n 最小稳态 (3)

[0032] Calculate the maximum rotor speed n max according to formula (4);

[0033] n max = MAX(n 最大稳态 + η 控制精度 , n 最大瞬态 + η 超调 ) (4).

[0034] Further, according to n min and n max , obtain the engine rotor dwell speed, specifically,

[0035] If then obtain the corresponding i-th engine rotor dwell speed according to formula (5) The speed step is 120 rpm;

[0036]

[0037] where ω 额定 is the rated speed;

[0038] If then the corresponding residence speed of the i-th engine rotor is obtained according to formula (6) The speed step is in accordance with (n max - n min ) / 9 * ω 额定 ;

[0039]

[0040] Furthermore, based on the residence speed of the engine rotor and the number of vibration residence times at the residence speed, the residence time of each residence speed is obtained Specifically, it includes:

[0041] The residence time corresponding to the residence speed is obtained according to formula (7)

[0042] The total cumulative residence time T is obtained according to formula (8);

[0043]

[0044] The present invention provides an aero-engine vibration assessment test system, and the system includes:

[0045] The engine assembly for vibration assessment of the integrated accessories that conforms to the most severe vibration environment of the integrated accessories;

[0046] A control device connected to the engine assembly, and the control device is used to control the speed of the engine rotor and calculate the residence speed of the engine rotor and the residence time at the residence speed;

[0047] A vibration assessment test running spectrum generated based on the control device;

[0048] A test device for inputting the vibration assessment test running spectrum, and the test device is used to operate and carry out the engine assembly test.

[0049] Advantageous effects

[0050] The advantageous effects of the present invention compared with the prior art are as follows:

[0051] 1. In this application, the vibration assessment test of the integrated accessories is carried out on the engine assembly, and the engine assembly used in the vibration assessment test of the integrated accessories simulates the possible maximum vibration environment and test temperature of the integrated accessories during the full operation cycle and the full speed range; making the installation and vibration environment more in line with the actual engineering situation.

[0052] 2. In this application, the accessories are placed in the whole machine for testing, which shortens the test time. The test time can be shortened by 40 - 50%, further accelerating the progress of the test.

[0053] 3. In this application, by measuring the vibration data of the engine body during the test, the vibration margin and vibration limit value are obtained, the relationship between the engine body vibration and the accessory vibration is established, and the vibration limit value for on-site monitoring of the accessories is formulated, further ensuring the safe use of the engine.

[0054] Other features and advantages of the present invention will be described in the following specification, and, in part, will be obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained through the structures pointed out in the specification and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0055] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0056] Figure 1 It shows the flowchart of the method in the embodiments of the present invention.

[0057] Figure 2 It shows the test flowchart in the embodiments of the present invention.

[0058] Figure 3 It shows the accessory resonance response diagram in the embodiments of the present invention.

[0059] Figure 4 It shows the schematic diagram of the engine rotor stop speed test spectrum without dwell time limit in the embodiments of the present invention.

[0060] Figure 5 It shows the schematic diagram of the engine rotor stop speed test spectrum with dwell time limit in the embodiments of the present invention.

[0061] Figure 6 It shows the flowchart for formulating the on-site vibration limit value in the embodiments of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0062] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the protection scope of the present invention.

[0063] This application provides a method for aero-engine vibration assessment test, referring to Figure 1 and Figure 2 , including:

[0064] Assembling the engine complete machine for accessory vibration assessment according to the worst vibration environment of the accessories;

[0065] Determining the engine rotor's hold speed and the hold time at the hold speed;

[0066] Formulating a vibration assessment test running spectrum according to the engine rotor's hold speed and the hold time at the hold speed;

[0067] Carrying out the engine complete machine test with reference to the vibration assessment test running spectrum.

[0068] In an embodiment of the present invention, the worst vibration environment of the accessories includes:

[0069] Setting the worst unbalance of the engine rotor;

[0070] Setting the worst unbalance of the rotating parts of the accessories themselves according to the grade of the balance accuracy standard.

[0071] In an embodiment of the present invention, at the end of the engine complete machine test;

[0072] According to the measurement data of the engine complete machine test, generating a curve graph of engine speed and vibration, and formulating the vibration limit value of the accessories; accelerating the fatigue damage of the accessories through the cumulative effect of vibration energy to realize the laboratory verification of the equivalent field service conditions;

[0073] And disassembling and inspecting the accessories according to the accessory quality inspection standard.

[0074] After the test is completed, disassembling the accessories according to the accessory quality inspection standard, checking the various functions of the accessories, and determining whether the functions of the accessories are normal; if all the disassembled and inspected functions of the accessories are normal, it is considered that within the above vibration limit value of the accessories, the vibration fatigue characteristics of the accessories meet the use requirements. On the contrary, if there are abnormal functions in the disassembled and inspected accessories, within the above vibration limit value of the accessories, the vibration fatigue characteristics of the accessories do not meet the use requirements.

[0075] During the implementation process, the accessory in actual work is mainly subject to vibration loads caused by the excitation of the engine rotor and the excitation of its own rotating parts. These vibration loads are mainly caused by the rotor unbalance. Therefore, in order to simulate the most severe vibration environment of the accessory, it is necessary to adjust the engine rotor unbalance and the unbalance of the accessory's own rotating parts to the most severe state. For the most severe unbalance of the engine rotor, it can be prefabricated with reference to the patent "Method and System for Determining the Maximum Unbalance of an Engine Rotor, Electronic Equipment, Storage Medium". For the most severe unbalance of the accessory's own rotating parts, generally, the unbalance of the accessory's own rotating parts at the factory is controlled according to the G0.4 accuracy class in the international balance accuracy standard ISO1940. However, in actual work, the rotating parts are worn, which will cause an increase in unbalance. Considering that the structure of the accessory's own rotating parts is relatively simple and the operating conditions are relatively stable, therefore, the most severe unbalance of the accessory's own rotating parts can be reduced by one accuracy class on the basis of the factory balance accuracy class, that is, the unbalance of the accessory's own rotating parts is prefabricated according to the G1.0 accuracy class;

[0076] According to the requirements, prefabricate the unbalances of the engine rotor and the accessory's own rotating parts, and complete the assembly of the engine whole machine for the vibration assessment of the accessory according to the assembly process.

[0077] The vibration environment of the accessory is not only related to the unbalance, but also related to the running speed of the rotor. Therefore, by determining the dwell speed of the engine rotor and the dwell time of the engine rotor, a vibration assessment test spectrum for the accessory under the whole machine state is formulated. Based on the assembled engine whole machine completed according to the assembly process, a vibration assessment test for the accessory is carried out. During the vibration assessment test, the vibration of the engine body is measured at each engine rotor dwell speed, and a curve graph of the engine speed and vibration is obtained to establish the relationship between the vibration of the engine body and the vibration of the accessory;

[0078] In this application, the vibration assessment test for the accessory is carried out on the engine whole machine, and the engine whole machine used in the vibration assessment test for the accessory simulates the possible maximum vibration environment and test temperature of the accessory during the full operating cycle and the full speed range. This makes the installation and vibration environment more in line with the actual engineering situation.

[0079] In an embodiment of the present invention, the determination of the engine rotor dwell speed specifically includes:

[0080] Obtain the minimum steady-state speed of the rotor as n 最小稳态 、the maximum steady-state speed as n 最大稳态 、the maximum transient speed as n 最大瞬态 from the engine limit value file, and the system error of the rotor speed control is η2] 控制精度 and the rotor overshoot is η 超调 ;

[0081] According to n最小稳态 , n 最大稳态 , n 最大瞬态 , η 控制精度 and η 超调 , obtain the minimum rotor speed as n min and the maximum speed as n max ;

[0082] According to n min and n max , obtain the engine rotor holding speed.

[0083] In an embodiment of the present invention, the residence time for determining the holding speed specifically includes: according to the known engine rotor holding speed being greater than 10 and the vibration residence times of the accessories being not less than 10 7 times; it is obtained that the vibration residence times of the accessories at each engine rotor holding speed are not less than 10 6 times;

[0084] According to the engine rotor holding speed and the vibration residence times of the holding speed, obtain the residence time of the holding speed.

[0085] Calculate the equivalent relationship according to the Miner fatigue cumulative damage theory, and obtain that the vibration residence times of the accessories are not less than 10 7 times;

[0086] In an embodiment of the present invention, the according to n 最小稳态 , n 最大稳态 , n 最大瞬态 , η 控制精度 and η 超调 , obtain the minimum rotor speed n min and the maximum speed n max , specifically,

[0087] Calculate the minimum rotor speed n min according to formula (3);

[0088] n min = n 最小稳态 (3)

[0089] Calculate the maximum rotor speed n max according to formula (4);

[0090] n max = MAX(n 最大稳态 + η 控制精度 , n 最大瞬态 + η 超调 ) (4).

[0091] In an embodiment of the present invention, refer to Figure 2 , Figure 3 , Figure 4 andFigure 5 , according to n min and n max , obtain the engine rotor's dwell speed. Specifically,

[0092] If then obtain the corresponding dwell speed of the i-th engine rotor according to formula (5) The speed step is 120 rpm;

[0093]

[0094] where ω 额定 is the rated speed;

[0095] If then obtain the corresponding dwell speed of the i-th engine rotor according to formula (6) The speed step is (n max - n min ) / 9 * ω 额定 ;

[0096]

[0097] When the accessory is just in the resonance state at a certain speed, if the speed control accuracy is not high, it will not be possible to ensure that the accessory stays in the resonance state for a long time, resulting in a loose assessment. Therefore, during the test, it is necessary to control the rotor speed by using high-precision speed control equipment. According to the resonance curve of the components and engineering experience, the speed control accuracy requirement is within 60 rpm. Based on this, if the dwell speed of the rotor in the accessory vibration assessment test can be stepped up from the minimum speed n min to the maximum speed n max at a speed step of 120 rpm;

[0098] If n min = 80%, ω 额定 = 45000, n max = 102%;

[0099] then, the total number of speeds to stop is (1.02 - 0.8) × 45000 / 120 = 82.5, rounded up to 83, which is greater than 9, that is plus 1 at the rear boundary, a total of 84 dwell speeds.

[0100]

[0101] If the dwell speed of the rotor in the accessory vibration assessment test can be (n max - n min ) / 9 * ω额定 The rotational speed step, from the minimum rotational speed n min climbs to the maximum rotational speed n max ;

[0102] If n min = 100%, ω 额定 = 45000, n max = 102%

[0103] Then, the total number of rotational speeds to stay is (1.02 - 1.0) × 45000 / 120 = 7.5, rounded up to 8, less than 9. At this time, the rotational speed step (n max - n min ) / 9 * ω 额定 = 100.

[0104]

[0105] In an embodiment of the present invention, obtaining the residence time of each residence rotational speed according to the residence rotational speed of the engine rotor and the number of vibration residence times of the residence rotational speed Specifically includes:

[0106] Obtaining the residence time corresponding to the residence rotational speed according to formula (7)

[0107] Obtaining the cumulative total residence time T according to formula (8);

[0108]

[0109] During the implementation process, taking a certain type of engine as an example, the minimum rotational speed of its combustion engine rotor is 28350 rpm, and the maximum rotational speed is 46350 rpm. Based on formulas (7) and (8), the calculated cumulative total time T is 68.75 hours. And this type of engine has a total of 43 types of accessories. According to the existing test method, the cumulative total time is not less than 129 hours, so that the test time can be shortened by 40% - 50%.

[0110] In addition, since the residence rotational speed of the rotor has reached the limit value and the residence time is more than 20 minutes in the accessory vibration assessment test, but in actual use, there will be strict restrictions on the time for the engine to stay at the limit rotational speed for a single time to ensure safety. Therefore, when the residence rotational speed is above the rotational speed with a limited service time of the engine, the residence time at this residence rotational speed needs to be split, but the cumulative total time after splitting must meet the original residence time requirement.

[0111] Taking a certain type of engine as an example, the single - stay time of the engine rotor should not exceed 2 minutes when the speed is above 45450 rpm. For a stay speed greater than 45450 rpm, such as 45510 rpm, the stay time should be no less than 22 minutes. Then, 22 minutes need to be split into 11 parts. After running 1 part, the engine is pulled down to a state with a lower speed and no limit on the single - run duration. This process is repeated until all 11 parts are tested.

[0112] In one embodiment of the present invention, referring to Figure 6 , the vibration limit value of the accessory is formulated, specifically including: according to the engine body vibration values at each stay speed included in the engine overall test measurement data Sort the from large to small. The first K engine body vibration values are sequentially denoted as where K represents the number of engine body vibration values selected from large to small; then calculate the vibration margin λ according to formula (1);

[0113]

[0114] Calculate the vibration limit value V of the accessory according to formula (2) 限制值 ;

[0115]

[0116] The existing vibration assessment test of the engine accessory cannot provide a reference for the on - site use monitoring of the accessory. Generally, the on - site use of the engine will conduct real - time vibration monitoring of the engine body vibration. At present, the vibration assessment test of the accessory is carried out on the component bench and is a pass - through test, and the relationship between the engine body vibration and the accessory vibration cannot be established;

[0117] By determining the engine rotor stay speed and the stay time at each stay speed, formulating a test driving spectrum for the vibration assessment test of the accessory under the overall engine state, and carrying out the vibration assessment test of the accessory. During the test, measure the engine body vibration at each stay speed to obtain the engine body vibration values at each stay speed, denoted as Arrange the measured engine body vibration values at each stay speed in order of magnitude, and select the 10 largest engine body vibration values, denoted as In the way of linear equivalence, convert the vibration cycle times of the accessory with a smaller engine body vibration value to the vibration cycle times of the maximum engine body vibration amount, obtain the vibration margin λ with reference to formula (1), and finally obtain the vibration limit value of the accessory according to formula (2); by establishing the relationship between the engine body vibration and the accessory vibration, and formulating the vibration limit value for on - site monitoring of the accessory, further ensure the safe use of the engine;

[0118] In Ten values of 30, 31, 32, …, 38, 39 respectively, the vibration margin λ = 0.885 is obtained according to formula (1), and then V is obtained according to formula (2). 限制值 = 34.5

[0119] An aero-engine vibration assessment test system, the system includes:

[0120] The accessory vibration assessment engine of the whole machine that conforms to the most severe vibration environment of the assembled accessory;

[0121] A control device connected to the engine of the whole machine, the control device is used to control the rotational speed of the engine rotor and calculate the dwell speed of the engine rotor and the dwell time of the dwell speed;

[0122] Based on the vibration assessment test running spectrum generated by the control device;

[0123] The test device that inputs the vibration assessment test running spectrum, and the test device is used to operate and carry out the engine whole machine test.

[0124] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A vibration assessment test method for an aero-engine, characterized in that, Including: Complete the assembly of the engine for the vibration assessment of the accessory according to the most severe vibration environment of the accessory; Determine the dwell speed of the engine rotor and the dwell time of the dwell speed; Formulate a vibration assessment test running spectrum according to the dwell speed of the engine rotor and the dwell time of the dwell speed; Carry out the engine whole machine test with reference to the vibration assessment test running spectrum.

2. The aero-engine vibration assessment test method according to claim 1, characterized in that Complete the assembly of the engine for the vibration assessment of the accessory according to the most severe vibration environment of the accessory, including: Set the most severe unbalance of the engine rotor; Set the most severe unbalance of the rotating parts of the accessory itself according to the grade of the balance accuracy standard.

3. A method for a vibration assessment test of an aeroengine according to claim 1, characterized in that The determination of the dwell speed of the engine rotor specifically includes: Obtain the minimum steady-state speed of the rotor as n according to the engine limit value file 最小稳态 and the maximum steady-state speed as n 最大稳态 and the maximum transient speed as n 最大瞬态 . The system error of rotor speed control is η 控制精度 and the rotor overshoot is η 超调 ; According to n 最小稳态 , n 最大稳态 , n 最大瞬态 , η 控制精度 and η 超调 , the minimum rotational speed of the rotor is obtained as n min and the maximum rotational speed is n max ; According to n min and n max , obtain the engine rotor hold speed.

4. A method for a vibration assessment test of an aeroengine according to claim 1, wherein The residence time for determining the residence speed specifically includes: based on the known fact that the residence speed of the engine rotor is greater than 10 and the number of vibration residence times of the accessories is not less than 10 7 times; it is obtained that the number of vibration residence times of the accessories at each residence speed of the engine rotor is not less than 10 6 times; Obtain the dwell time of the dwell speed according to the dwell speed of the engine rotor and the vibration dwell times of the dwell speed.

5. A method for a vibration assessment test of an aero-engine according to claim 1, characterized in that, At the end of the engine whole machine test, generate a curve graph of engine speed and vibration according to the measurement data of the engine whole machine test, and formulate the vibration limit value of the accessory; And disassemble and inspect the accessory according to the quality inspection standard of the accessory.

6. A method for a vibration assessment test of an aero-engine according to claim 5, characterized in that, The formulated vibration limit value of the attachment specifically includes: according to the engine body vibration values at each dwell speed included in the engine overall test measurement data Sort the from largest to smallest, and record the first K engine body vibration values in sequence as where K represents the number of engine body vibration values selected from largest to smallest; then calculate the vibration margin λ according to formula (1); Calculate the vibration limit value V of the attachment according to formula (2) 限制值 ; 7. A method for a vibration assessment test of an aeroengine according to claim 3, characterized in that Said according to n 最小稳态 、n 最大稳态 、n 最大瞬态 、η 控制精度 and η 超调 to obtain the minimum rotor speed n min and the maximum speed n max Specifically, Calculate the minimum rotational speed n of the rotor according to formula (3). min ; n min = n 最小稳态 (3) Calculate the maximum rotor speed n according to formula (4) max ; n max = MAX(n 最大稳态 + η 控制精度 ,n 最大瞬态 + η 超调 ) (4).

8. A method for an aero-engine vibration assessment test according to claim 7, characterized in that Said according to n min and n max , obtain the engine rotor holding speed, specifically, If then obtain the corresponding stay speed of the i-th engine rotor according to formula (5) The speed step is 120 rpm; where ω 额定 is the rated speed; If then obtain the corresponding dwell speed of the i-th engine rotor according to formula (6) The speed step is in accordance with (n max - n min ) / 9 * ω 额定 ; 9. A method for a vibration assessment test of an aero-engine according to claim 4, wherein, Obtaining the residence time of each residence speed according to the residence speed of the engine rotor and the number of vibration residencies at the residence speed Specifically including: Obtain the residence time corresponding to the residence speed according to formula (7) Obtain the total cumulative dwell time T according to formula (8); 10. An aero-engine vibration assessment test system, characterized in that, The system includes: The engine for the vibration assessment of the accessory that conforms to the most severe vibration environment of the accessory; A control device connected to the engine whole machine, which is used to control the speed of the engine rotor and calculate the dwell speed of the engine rotor and the dwell time of the dwell speed; A vibration assessment test running spectrum generated based on the control device; A test device that inputs the vibration assessment test running spectrum, and the test device is used to operate and carry out the engine whole machine test.

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