Aero-engine compressor tester power unit debugging method and system

Abstract

The invention relates to the technical field of gas compressor test, and discloses a method and a system for debugging a power unit of a gas compressor tester of an aero-engine, and the method comprises the steps: respectively carrying out the speed-up test and the speed-down test of different angular acceleration horizontal values on a motor under a non-load condition; obtaining the maximum rotating speed overshoot and the maximum steady speed precision in each step rotating speed process under the angular acceleration horizontal value corresponding to each test, and respectively establishing a function relation between the maximum rotating speed overshoot and the angular acceleration and a function relation between the maximum steady speed precision and the angular acceleration in the acceleration test and the deceleration test; and determining a speed-up angular acceleration limit value and a speed-down angular acceleration limit value of the compressor tester under the load condition. While ensuring the safe operation of the compressor performance test, the method solves the problem of uncertainty caused by adopting the control rotating speed as a monitoring means in the prior art, and further improves the performance evaluation precision of the compressor.

Description

Technical Field

[0001] The invention relates to the technical field of compressor testing, and discloses a power unit debugging method and system for an aero-engine compressor tester. Background Art

[0002] The performance test of aircraft engine compressors has the characteristics of high performance evaluation accuracy, high speed, high power, and multiple risk sources. The compressor tester responsible for the test must have functions such as high-precision testing equipment, high-precision control units, and high-reliability security units. The stringent requirements for the power unit are different from those in most other industrial application fields.

[0003] The existing aircraft engine compressor performance test requires speed-up and speed-down tests, and the angular acceleration control of the motor is crucial during this process. If the angular acceleration parameters are not set properly, the motor operation may become unstable, which directly affects the safety and accuracy of the compressor test. In addition, the motor control during the current compressor test generally relies on the experience of technicians to control the motor speed, which makes it difficult to ensure the accuracy and consistency of the compressor performance test. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft engine compressor tester power unit debugging method and system, which can ensure the safe operation of the compressor performance test while solving the uncertainty problem caused by the traditional use of speed control as a monitoring method, and further improve the accuracy of compressor performance evaluation.

[0005] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0006] The method for debugging the power unit of an aircraft engine compressor tester includes:

[0007] The angular acceleration of the motor is gradually increased from a preset initial angular acceleration according to the steps of the preset angular acceleration gradient. Each time the angular acceleration is increased by one level, the motor is subjected to a speed increase test and a speed reduction test under no-load conditions, respectively, until the motor becomes unstable during operation; and the maximum speed overshoot and the maximum steady-speed accuracy are recorded during each step speed process under the corresponding angular acceleration level value of each test; the speed increase test is to increase the motor speed from a stationary state to a rated speed step by step under each angular acceleration level value, and the speed reduction test is to reduce the motor speed from a rated speed step by step to a stationary state under each angular acceleration level value;

[0008] Taking each angular acceleration level value before instability in the speed-up test as the independent variable, and taking the maximum speed overshoot and the maximum steady-speed accuracy under the corresponding angular acceleration level value as the dependent variables, the first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and the second functional relationship between the maximum steady-speed accuracy and the angular acceleration level value of the speed-up test are established;

[0009] Taking each angular acceleration level value before the instability of the speed reduction test as the independent variable, and taking the maximum speed overshoot and the maximum steady speed accuracy under the corresponding angular acceleration level value as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum steady speed accuracy and the angular acceleration level value of the speed reduction test are established;

[0010] According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, a first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the first functional relationship; a second speed-up angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the second functional relationship;

[0011] According to the minimum value of the first speed-up angular acceleration limit value and the second speed-up angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor, the angular acceleration limit value of the motor during the speed-up process under load conditions is analyzed and obtained;

[0012] According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, the first deceleration angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the third functional relationship; the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the fourth functional relationship;

[0013] According to the minimum value of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor, the angular acceleration limit value of the motor during the deceleration under load conditions is analyzed and obtained.

[0014] Further, according to the minimum value α of the first acceleration increase angular acceleration limit value and the second acceleration increase angular acceleration limit value ms , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during the speed increase process under load conditions u .

[0015] Further, according to the minimum value α of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value mj , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during deceleration under load conditions d .

[0016] Furthermore, according to the angular acceleration level α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the moment of inertia J2 of the tested compressor rotor, the Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

[0017] In order to achieve the above technical effects, the present invention also provides an aircraft engine compressor tester power unit debugging system, which is used to implement the aircraft engine compressor tester power unit debugging method; comprising:

[0018] The data acquisition module is used to obtain the maximum speed overshoot and maximum steady-speed accuracy of each step speed of the motor of the power unit of the aircraft engine compressor tester at each angular acceleration level value in the speed increase test and the speed reduction test under no-load conditions; the speed increase test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to the steps of a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped up from a static state to a rated speed under no-load conditions until the motor becomes unstable during operation; the speed reduction test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to the steps of a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped down from the rated speed to a static state under no-load conditions until the motor becomes unstable during operation;

[0019] A speed-up model building module is used to establish a first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value of the speed-up test, with each angular acceleration level value before the speed-up test becomes unstable as an independent variable, and with the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables;

[0020] A speed reduction model construction module is used to establish a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value of the speed reduction test, with each angular acceleration level value before the speed reduction test becomes unstable as an independent variable, and with the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables;

[0021] The speed-up model analysis module is used to reversely calculate the first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester using the first functional relationship according to the speed overshoot limit value and the speed stabilization accuracy limit value of the compressor tester; and reversely calculate the second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value using the second functional relationship;

[0022] The first analysis module is used to analyze and obtain the angular acceleration limit value of the motor during the speed-up process under load conditions according to the minimum value of the first speed-up angular acceleration limit value and the second speed-up angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor;

[0023] The deceleration model analysis module is used to reversely calculate the first deceleration angular acceleration limit value corresponding to the compressor tester speed overshoot limit value and the steady speed accuracy limit value using the third functional relationship according to the compressor tester speed overshoot limit value; and reversely calculate the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value using the fourth functional relationship;

[0024] The second analysis module is used to analyze and obtain the angular acceleration limit value of the motor during the deceleration process under load conditions according to the minimum value of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor.

[0025] Furthermore, in the first analysis module, according to the minimum value α of the first acceleration angular acceleration limit value and the second acceleration angular acceleration limit value ms , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during the speed increase process under load conditions u .

[0026] Furthermore, in the second analysis module, according to the minimum value α of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value mj , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during deceleration under load conditions d .

[0027] Furthermore, the method further comprises a third analysis module, which is used to analyze the angular acceleration level α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the moment of inertia J2 of the tested compressor rotor, using Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

[0028] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention takes into account the influence of the maximum speed overshoot and steady speed accuracy of the compressor tester in determining the angular acceleration limit value during the motor speed-up and speed-down processes, while ensuring the safe operation of the compressor performance test, solves the uncertainty problem caused by the traditional use of speed control as a monitoring method, and further improves the accuracy of compressor performance evaluation. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a flow chart of the debugging method of the power unit of the aircraft engine compressor tester in Example 1 or 2;

[0030] Figure 2 This is a structural block diagram of the power unit debugging system of the aircraft engine compressor tester in Example 1;

[0031] Figure 3 It is the speed curve diagram of the speed increase test and the speed decrease test in Example 2;

[0032] Figure 4 The speed curve diagram of the motor in the embodiment 2 during the stable stage of a certain target speed fluctuation;

[0033] Among them, 1. Data acquisition module; 2. Speed-up model construction module; 3. Speed-down model construction module; 4. Speed-up model analysis module; 5. First analysis module; 6. Speed-down model analysis module; 7. Second analysis module; 8. Third analysis module. DETAILED DESCRIPTION

[0034] The present invention is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0035] Example 1

[0036] See also Figure 1 , Figure 2 , the power unit debugging method of the aircraft engine compressor tester includes:

[0037] The angular acceleration of the motor is gradually increased from a preset initial angular acceleration according to the steps of the preset angular acceleration gradient. Each time the angular acceleration is increased by one level, the motor is subjected to a speed increase test and a speed reduction test under no-load conditions, respectively, until the motor becomes unstable during operation; and the maximum speed overshoot and the maximum steady-speed accuracy are recorded during each step speed process under the corresponding angular acceleration level value of each test; the speed increase test is to increase the motor speed from a stationary state to a rated speed step by step under each angular acceleration level value, and the speed reduction test is to reduce the motor speed from a rated speed step by step to a stationary state under each angular acceleration level value;

[0038] Taking each angular acceleration level value before instability in the speed-up test as the independent variable, and taking the maximum speed overshoot and the maximum steady-speed accuracy under the corresponding angular acceleration level value as the dependent variables, the first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and the second functional relationship between the maximum steady-speed accuracy and the angular acceleration level value of the speed-up test are established;

[0039] Taking each angular acceleration level value before the instability of the speed reduction test as the independent variable, and taking the maximum speed overshoot and the maximum steady speed accuracy under the corresponding angular acceleration level value as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum steady speed accuracy and the angular acceleration level value of the speed reduction test are established;

[0040] According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, a first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the first functional relationship; a second speed-up angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the second functional relationship;

[0041] According to the minimum value of the first speed-up angular acceleration limit value and the second speed-up angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor, the angular acceleration limit value of the motor during the speed-up process under load conditions is analyzed and obtained;

[0042] According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, the first deceleration angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the third functional relationship; the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the fourth functional relationship;

[0043] According to the minimum value of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor, the angular acceleration limit value of the motor during the deceleration under load conditions is analyzed and obtained.

[0044] In this embodiment, by performing speed-up tests and speed-down tests on the motor at different angular acceleration levels under no-load conditions, the maximum speed overshoot and the maximum steady-speed accuracy in each step speed process under the corresponding angular acceleration level of each test are obtained, and the functional relationship between the maximum speed overshoot and the angular acceleration, and the functional relationship between the maximum steady-speed accuracy and the angular acceleration of the speed-up test and the speed-down test are established respectively, so as to determine the speed-up angular acceleration limit value and the speed-down angular acceleration limit value of the compressor tester under load conditions. The present invention takes into account the influence of the maximum speed overshoot and the steady-speed accuracy of the compressor tester in determining the angular acceleration limit value during the motor speed-up process and the speed-down process, and solves the uncertainty problem caused by the traditional use of speed control as a monitoring method while ensuring the safe operation of the compressor performance test, and further improves the accuracy of compressor performance evaluation.

[0045] Based on the same inventive concept, this embodiment also provides an aircraft engine compressor tester power unit debugging system, including:

[0046] The data acquisition module 1 is used to obtain the maximum speed overshoot and maximum steady-speed accuracy of each step speed of the motor of the power unit of the aircraft engine compressor tester under no-load conditions at each angular acceleration level value in the speed-up test and the speed-down test; the speed-up test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to the steps of a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped up from a static state to a rated speed under no-load conditions until the motor becomes unstable during operation; the speed-down test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to the steps of a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped down from the rated speed to a static state under no-load conditions until the motor becomes unstable during operation;

[0047] The speed-up model building module 2 is used to establish a first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value of the speed-up test, with each angular acceleration level value before the speed-up test instability as an independent variable, and with the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables;

[0048] The speed reduction model building module 3 is used to establish a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value of the speed reduction test, with each angular acceleration level value before the speed reduction test becomes unstable as an independent variable, and with the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables;

[0049] The speed-up model analysis module 4 is used to reversely calculate the first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester using the first functional relationship according to the speed overshoot limit value and the speed stabilization accuracy limit value of the compressor tester; and reversely calculate the second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value using the second functional relationship;

[0050] The first analysis module 5 is used to analyze and obtain the angular acceleration limit value of the motor during the speed increase process under load conditions according to the minimum value of the first speed increase angular acceleration limit value and the second speed increase angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor;

[0051] The deceleration model analysis module 6 is used to reversely calculate the first deceleration angular acceleration limit value corresponding to the compressor tester speed overshoot limit value and the steady speed accuracy limit value using the third functional relationship according to the compressor tester speed overshoot limit value; and reversely calculate the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value using the fourth functional relationship;

[0052] The second analysis module 7 is used to analyze and obtain the angular acceleration limit value of the motor during the deceleration process under load conditions according to the minimum value of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor.

[0053] Considering that emergency braking may be required during the test, it is necessary to quickly decelerate the motor to a stop and achieve safe emergency braking while ensuring that the motor will not become unstable, thereby ensuring the safety of the test. The aircraft engine compressor tester power unit debugging system in this embodiment also includes a third analysis module 8, which is used to use the angular acceleration level value α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the moment of inertia J2 of the tested compressor rotor, to analyze the angular acceleration level α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the tested compressor rotor moment of inertia J2. Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

[0054] Example 2

[0055] See also Figure 1 This embodiment takes the motor debugging of a certain type of compressor tester power unit as an example to explain in detail the debugging method flow of the aircraft engine compressor tester power unit of the present invention. The specific operation steps are as follows:

[0056] Step 1: Calculate the theoretical angular acceleration α0 of the motor according to the performance parameters of the power unit motor, and set the preset angular acceleration gradient and initial angular acceleration of the motor during the speed-up test or speed-down test according to the theoretical angular acceleration α0;

[0057] In this embodiment, the angular acceleration gradient of the motor is set in steps of α0 / 10, and the initial angular acceleration is α0 / 2, that is, during the speed-up test or speed-down test, the angular acceleration is set to start from α0 / 2 for a gradient speed-up test or a gradient speed-down test. Figure 3 As shown, for example, during the gradient speed-up test, the motor speed is stepped up from a stationary state to a rated speed at an angular acceleration level of α0 / 2, and then the angular acceleration level is increased to α0 / 2+α0 / 10, and then the motor speed is stepped up from a stationary state to a rated speed, and the operation is repeated until the motor becomes unstable during the speed-up process at a certain angular acceleration level. The speed reduction test process is similar and will not be described in detail here.

[0058] Step 2: The angular acceleration of the motor is gradually increased from a preset initial angular acceleration according to the step of a preset angular acceleration gradient. Each time the angular acceleration is increased by one level, the motor is subjected to a speed increase test and a speed reduction test under no-load conditions until the motor becomes unstable during operation; and the maximum speed overshoot and the maximum steady-speed accuracy are recorded during each step speed under the corresponding angular acceleration level value of each test; the speed increase test is to increase the motor speed from a stationary state to a rated speed at each angular acceleration level value, and the speed reduction test is to reduce the motor speed from a rated speed to a stationary state at each angular acceleration level value;

[0059] like Figure 3 and Figure 4 In this embodiment, the maximum speed overshoot n at each angular acceleration level is cs =Max|n1-n0|, where n0 is the target speed and n1 is the maximum speed exceeding the target speed; maximum steady speed accuracy where n max is the maximum speed fluctuation in the target speed stabilization phase, n min is the minimum speed of fluctuation in the target speed stabilization phase, and n is the rated speed of the motor.

[0060] Step 3: Taking each angular acceleration level value before the instability of the speed-up test as the independent variable, and taking the maximum speed overshoot and the maximum steady-speed accuracy under the corresponding angular acceleration level value as the dependent variables, a first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and a second functional relationship between the maximum steady-speed accuracy and the angular acceleration level value of the speed-up test are established;

[0061] Step 4: Taking each angular acceleration level value before the instability of the speed reduction test as the independent variable, and taking the maximum speed overshoot and the maximum steady speed accuracy under the corresponding angular acceleration level value as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum steady speed accuracy and the angular acceleration level value of the speed reduction test are established;

[0062] Step 5: According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, reverse calculation is performed using the first functional relationship to obtain the first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester; reverse calculation is performed using the second functional relationship to obtain the second speed-up angular acceleration limit value corresponding to the steady speed accuracy limit value;

[0063] Step 6: Analyze and obtain the angular acceleration limit value of the motor during the speed increase process under load conditions according to the minimum value of the first speed increase angular acceleration limit value and the second speed increase angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor;

[0064] In this embodiment, the Analyze and obtain the angular acceleration limit value α of the motor during the speed increase process under load conditions u , α ms is the minimum value of the first speed-up angular acceleration limit value and the second speed-up angular acceleration limit value, J1 is the motor moment of inertia, and J2 is the moment of inertia of the compressor rotor under test.

[0065] Step 7: According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, the first deceleration angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the third functional relationship; the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the fourth functional relationship;

[0066] Step 8: According to the minimum value α of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value mj , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during deceleration under load conditions d .

[0067] Step 9: According to the angular acceleration level value α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the moment of inertia J2 of the tested compressor rotor, adopt Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

[0068] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for debugging a power unit of an aircraft engine compressor tester, characterized in that: include: The angular acceleration of the motor is gradually increased from a preset initial angular acceleration according to the steps of the preset angular acceleration gradient. Each time the angular acceleration is increased by one level, the motor is subjected to a speed increase test and a speed reduction test under no-load conditions, respectively, until the motor becomes unstable during operation; and the maximum speed overshoot and the maximum steady-speed accuracy are recorded during each step speed process under the corresponding angular acceleration level value of each test; the speed increase test is to increase the motor speed from a stationary state to a rated speed step by step under each angular acceleration level value, and the speed reduction test is to reduce the motor speed from a rated speed step by step to a stationary state under each angular acceleration level value; Taking each angular acceleration level value before instability in the speed-up test as the independent variable, and taking the maximum speed overshoot and the maximum steady-speed accuracy under the corresponding angular acceleration level value as the dependent variables, the first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and the second functional relationship between the maximum steady-speed accuracy and the angular acceleration level value of the speed-up test are established; Taking each angular acceleration level value before the instability of the speed reduction test as the independent variable, and taking the maximum speed overshoot and the maximum steady speed accuracy under the corresponding angular acceleration level value as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum steady speed accuracy and the angular acceleration level value of the speed reduction test are established; According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, a first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the first functional relationship; a second speed-up angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the second functional relationship; According to the minimum value of the first speed-up angular acceleration limit value and the second speed-up angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor, the angular acceleration limit value of the motor during the speed-up process under load conditions is analyzed and obtained; According to the speed overshoot limit value and the steady speed accuracy limit value of the compressor tester, the first deceleration angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester is obtained by reverse calculation using the third functional relationship; the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value is obtained by reverse calculation using the fourth functional relationship; According to the minimum value of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor, the angular acceleration limit value of the motor during the deceleration under load conditions is analyzed and obtained.

2. The method for debugging a power unit of an aircraft engine compressor tester according to claim 1, characterized in that: According to the minimum value α of the first acceleration increase angular acceleration limit value and the second acceleration increase angular acceleration limit value ms , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during the speed increase process under load conditions u .

3. The method for debugging a power unit of an aircraft engine compressor tester according to claim 1, characterized in that: According to the minimum value α of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value mj , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during deceleration under load conditions d .

4. The method for debugging a power unit of an aircraft engine compressor tester according to claim 1, characterized in that: According to the angular acceleration level α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the moment of inertia J2 of the tested compressor rotor, the Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

5. An aircraft engine compressor tester power unit debugging system, used to implement the aircraft engine compressor tester power unit debugging method according to claim 1; characterized in that: include: The data acquisition module is used to obtain the maximum speed overshoot and maximum steady-speed accuracy of each step speed of the motor of the power unit of the aircraft engine compressor tester at each angular acceleration level value in the speed increase test and the speed reduction test under no-load conditions; the speed increase test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to the steps of a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped up from a static state to a rated speed under no-load conditions until the motor becomes unstable during operation; the speed reduction test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to the steps of a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped down from the rated speed to a static state under no-load conditions until the motor becomes unstable during operation; A speed-up model building module is used to establish a first functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value of the speed-up test, with each angular acceleration level value before the speed-up test becomes unstable as an independent variable, and with the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables; A speed reduction model construction module is used to establish a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value of the speed reduction test, with each angular acceleration level value before the speed reduction test becomes unstable as an independent variable, and with the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables; The speed-up model analysis module is used to reversely calculate the first speed-up angular acceleration limit value corresponding to the speed overshoot limit value of the compressor tester using the first functional relationship according to the speed overshoot limit value and the speed stabilization accuracy limit value of the compressor tester; and reversely calculate the second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value using the second functional relationship; The first analysis module is used to analyze and obtain the angular acceleration limit value of the motor during the speed-up process under load conditions according to the minimum value of the first speed-up angular acceleration limit value and the second speed-up angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor; The deceleration model analysis module is used to reversely calculate the first deceleration angular acceleration limit value corresponding to the compressor tester speed overshoot limit value and the steady speed accuracy limit value using the third functional relationship according to the compressor tester speed overshoot limit value; and reversely calculate the second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value using the fourth functional relationship; The second analysis module is used to analyze and obtain the angular acceleration limit value of the motor during the deceleration process under load conditions according to the minimum value of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, as well as the rotational inertia of the motor and the rotational inertia of the tested compressor rotor.

6. The aircraft engine compressor tester power unit debugging system according to claim 5, characterized in that: In the first analysis module, according to the minimum value α of the first acceleration increase angular acceleration limit value and the second acceleration increase angular acceleration limit value, ms , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during the speed increase process under load conditions u .

7. The aircraft engine compressor tester power unit debugging system according to claim 5, characterized in that: In the second analysis module, according to the minimum value α of the first deceleration angular acceleration limit value and the second deceleration angular acceleration limit value, mj , as well as the motor moment of inertia J1 and the tested compressor rotor moment of inertia J2, using Analyze and obtain the angular acceleration limit value α of the motor during deceleration under load conditions d .

8. The aircraft engine compressor tester power unit debugging system according to claim 5, characterized in that: The third analysis module is also included, which is used to use the angular acceleration level value α1 of the stable deceleration operation within the rated speed before instability in the deceleration test, as well as the theoretical acceleration α0 of the motor, the motor moment of inertia J1, and the moment of inertia J2 of the tested compressor rotor, Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

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