Method and system for debugging power unit of aircraft engine compressor tester

Abstract

The present invention relates to the field of compressor testing technology and discloses a method and system for debugging a power unit of an aero-engine compressor tester. Under no-load conditions, a motor is subjected to speed-up and speed-down tests at different angular acceleration levels, obtaining the maximum speed overshoot and maximum steady-speed accuracy for each step speed process at the corresponding angular acceleration level for each test. By establishing functional relationships between the maximum speed overshoot and angular acceleration for the speed-up and speed-down tests, and between the maximum steady-speed accuracy and angular acceleration, respectively, the speed-up and speed-down angular acceleration limit values ​​of the compressor tester under load conditions are determined. While ensuring the safe operation of the compressor performance test, the method solves the uncertainty problem caused by the traditional use of speed control as a monitoring method, further improving the accuracy of compressor performance evaluation.

Description

Technical Field

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

[0002] Aircraft engine compressor performance tests are characterized by high performance evaluation accuracy, high speed, high power, and multiple risk sources. The compressor tester responsible for the test must be equipped with high-precision testing equipment, high-precision control units, high-reliability security units, and other functions. The stringent requirements for the power unit are different from those in most other industrial application fields.

[0003] Existing aircraft engine compressor performance tests require both ramp-up and ramp-down tests, during which the motor's angular acceleration control is crucial. Improper angular acceleration parameters can lead to unstable motor operation, directly impacting the safety and accuracy of compressor testing. Furthermore, current motor control during compressor testing generally relies on the technician's experience to control motor speed, making it difficult to ensure the accuracy and consistency of compressor performance testing. Summary of the Invention

[0004] The purpose of the present invention is to provide a method and system for debugging the power unit of an aircraft engine compressor tester, which can solve 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 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 debugging method of the power unit of the aircraft engine compressor tester includes:

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

[0008] Taking each angular acceleration level before instability in the speed-up test as the independent variable, and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as the dependent variables, a first functional relationship between the maximum speed overshoot and the angular acceleration level in the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed-up test were established.

[0009] Taking each angular acceleration level before instability in the speed reduction test as the independent variable, and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level in the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed reduction test were established.

[0010] Based on the speed overshoot limit value and the speed stabilization 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 a first functional relationship; and a second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value is obtained by reverse calculation using a second functional relationship;

[0011] The angular acceleration limit value of the motor during the speed-up process under load conditions is obtained by analyzing 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.

[0012] Based on the speed overshoot limit value and the speed stabilization accuracy limit value of the compressor tester, a first speed reduction 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; and a second speed reduction angular acceleration limit value corresponding to the speed stabilization accuracy limit value is obtained by reverse calculation using the fourth functional relationship;

[0013] The angular acceleration limit value of the motor during deceleration under load conditions is obtained by analysis based on 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.

[0014] Furthermore, 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] Furthermore, 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 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, the Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

[0017] To achieve the above technical effects, the present invention further provides an aircraft engine compressor tester power unit debugging system for implementing the above aircraft engine compressor tester power unit debugging method; comprising:

[0018] A 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 a speed-up test and a speed-down test under no-load conditions; the speed-up test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped 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 a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped from the rated speed to a static state under no-load conditions until the motor becomes unstable during operation;

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

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

[0021] The speed-up model analysis module is used to reversely calculate, based on the speed overshoot limit value and the speed stabilization 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 using a first functional relationship; and reversely calculate, based on the second functional relationship, a second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value;

[0022] The first analysis module is configured to analyze and obtain the angular acceleration limit value of the motor during the speed-up process under load conditions based on 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] a deceleration model analysis module for reversely calculating, based on the compressor tester speed overshoot limit value and the steady speed accuracy limit value, a first deceleration angular acceleration limit value corresponding to the compressor tester speed overshoot limit value using a third functional relationship; and reversely calculating, based on the fourth functional relationship, a second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value;

[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 based on 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 test 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 includes a third analysis module for analyzing 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. Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

[0028] Compared with the existing technology, the beneficial effects of the present invention are: 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, it solves the uncertainty problem brought about 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 This is a flow chart of the debugging method for 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 The speed curve diagram of the speed increase test and the speed decrease test in Example 2;

[0032] Figure 4 This is a speed curve diagram of the fluctuation of a certain target speed of the motor in the stable stage in Example 2;

[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 will be described in further detail below with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the present invention to the following embodiments, as all technologies implemented based on the present invention fall within the scope of the present invention.

[0035] Example 1

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

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

[0038] Taking each angular acceleration level before instability in the speed-up test as the independent variable, and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as the dependent variables, a first functional relationship between the maximum speed overshoot and the angular acceleration level in the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed-up test were established.

[0039] Taking each angular acceleration level before instability in the speed reduction test as the independent variable, and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level in the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed reduction test were established.

[0040] Based on the speed overshoot limit value and the speed stabilization 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 a first functional relationship; and a second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value is obtained by reverse calculation using a second functional relationship;

[0041] The angular acceleration limit value of the motor during the speed-up process under load conditions is obtained by analyzing 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.

[0042] Based on the speed overshoot limit value and the speed stabilization accuracy limit value of the compressor tester, a first speed reduction 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; and a second speed reduction angular acceleration limit value corresponding to the speed stabilization accuracy limit value is obtained by reverse calculation using the fourth functional relationship;

[0043] The angular acceleration limit value of the motor during deceleration under load conditions is obtained by analysis based on 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.

[0044] In this embodiment, by performing speed-up and speed-down tests on the motor under no-load conditions at different angular acceleration levels, the maximum speed overshoot and maximum steady-speed accuracy are obtained for each step speed process at the corresponding angular acceleration level for each test. Functional relationships between the maximum speed overshoot and angular acceleration, and between the maximum steady-speed accuracy and angular acceleration, are established for the speed-up and speed-down tests, respectively, to determine the speed-up and speed-down angular acceleration limits of the compressor tester under load conditions. The present invention considers the influence of the maximum speed overshoot and steady-speed accuracy of the compressor tester in determining the angular acceleration limit values ​​during the motor speed-up and speed-down processes. While ensuring the safe operation of the compressor performance test, it solves the uncertainty problem caused by the traditional use of speed control as a monitoring method, further improving 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 at each angular acceleration level value in the speed-up test and the speed-down test under no-load conditions; the speed-up test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped 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 a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped from the rated speed to a static state under no-load conditions until the motor becomes unstable during operation;

[0047] The speed-up model construction 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, using each angular acceleration level value before instability of the speed-up test as an independent variable and the maximum speed overshoot and the maximum speed stabilization accuracy at the corresponding angular acceleration level value as dependent variables;

[0048] The deceleration model construction module 3 is used to establish a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the deceleration test, and a fourth functional relationship between the maximum speed overshoot and the angular acceleration level value of the deceleration test, using each angular acceleration level value before instability of the deceleration test as an independent variable and the maximum speed overshoot and the maximum speed stabilization accuracy at the corresponding angular acceleration level value as dependent variables;

[0049] The speed-up model analysis module 4 is configured to reversely calculate, based on the compressor tester speed overshoot limit value and the steady-speed accuracy limit value, a first speed-up angular acceleration limit value corresponding to the compressor tester speed overshoot limit value using a first functional relationship; and reversely calculate, based on the second functional relationship, a second speed-up angular acceleration limit value corresponding to the steady-speed accuracy limit value;

[0050] A first analysis module 5 is configured to analyze and obtain an angular acceleration limit value of the motor during the speed-up process under load conditions based on 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;

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

[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 based on 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 test compressor rotor.

[0053] Considering that emergency braking may be required during the test, it is necessary to quickly decelerate the motor to a stop under the condition that the motor will not become unstable, so as to achieve safe emergency braking and ensure 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 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 debugging of a certain type of compressor tester power unit motor as an example to describe in detail the debugging method process 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 α0 / 2 for a gradient speed-up test or a gradient speed-down test. Figure 3 For example, during a ramp-up test, the motor speed is increased from a standstill to the rated speed at an angular acceleration level of α0 / 2. The angular acceleration level is then increased to α0 / 2 + α0 / 10, and the motor speed is then increased from a standstill to the rated speed. This process is repeated until the motor becomes unstable during the ramp-up process at a certain angular acceleration level. The deceleration 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 a preset angular acceleration gradient. Each time the angular acceleration is increased by one level, the motor is subjected to a speed-up test and a speed-down test under no-load conditions until instability occurs during the operation of the motor; and the maximum speed overshoot and the maximum steady-speed accuracy are recorded during each step speed at the corresponding angular acceleration level value of each test; the speed-up test is to step-up the motor speed from a stationary state to a rated speed at each angular acceleration level value, and the speed-down test is to step-down the motor speed from the 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 during the target speed stabilization phase, n min is the lowest speed of fluctuation in the target speed stabilization stage, and n is the rated speed of the motor.

[0060] Step 3: Using each angular acceleration level before instability in the speed-up test as an independent variable and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as dependent variables, establish a first functional relationship between the maximum speed overshoot and the angular acceleration level in the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed-up test;

[0061] Step 4: Using each angular acceleration level before instability in the speed reduction test as an independent variable and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as dependent variables, establish a third functional relationship between the maximum speed overshoot and the angular acceleration level in the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed reduction test;

[0062] Step 5: Based on the compressor tester speed overshoot limit value and the steady speed accuracy limit value, reversely calculate using the first functional relationship to obtain a first speed-up angular acceleration limit value corresponding to the compressor tester speed overshoot limit value; and reversely calculate using the second functional relationship to obtain a 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 based on 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 test 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 between 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 tested compressor rotor.

[0065] Step 7: Based on the compressor tester speed overshoot limit value and the steady speed accuracy limit value, reversely calculate using the third functional relationship to obtain a first deceleration angular acceleration limit value corresponding to the compressor tester speed overshoot limit value; and reversely calculate using the fourth functional relationship to obtain a second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value;

[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: Based on the angular acceleration level α1 of the stable deceleration operation within the rated speed before the 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, use 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 scope of protection 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 a preset angular acceleration gradient. Each time the angular acceleration is increased by one level, the motor is subjected to a speed-up test and a speed-down test under no-load conditions until instability occurs during the operation of the motor; and the maximum speed overshoot and the maximum steady-speed accuracy are recorded during each step speed at the corresponding angular acceleration level value of each test; the speed-up test is to increase the motor speed from a stationary state to a rated speed at each angular acceleration level value, and the speed-down test is to decrease the motor speed from the rated speed to a stationary state at each angular acceleration level value; Taking each angular acceleration level before instability in the speed-up test as the independent variable, and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as the dependent variables, a first functional relationship between the maximum speed overshoot and the angular acceleration level in the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed-up test were established. Taking each angular acceleration level before instability in the speed reduction test as the independent variable, and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level as the dependent variables, a third functional relationship between the maximum speed overshoot and the angular acceleration level in the speed reduction test, and a fourth functional relationship between the maximum speed stabilization accuracy and the angular acceleration level in the speed reduction test were established. Based on the speed overshoot limit value and the speed stabilization 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 a first functional relationship; and a second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value is obtained by reverse calculation using a second functional relationship; The angular acceleration limit value of the motor during the speed-up process under load conditions is obtained by analyzing 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. Based on the speed overshoot limit value and the speed stabilization accuracy limit value of the compressor tester, a first speed reduction 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; and a second speed reduction angular acceleration limit value corresponding to the speed stabilization accuracy limit value is obtained by reverse calculation using the fourth functional relationship; The angular acceleration limit value of the motor during deceleration under load conditions is obtained by analysis based on 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.

2. The method for debugging a power unit of an aero-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 aero-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 aero-engine compressor tester according to claim 1, characterized in that: 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, 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: A 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 a speed-up test and a speed-down test under no-load conditions; the speed-up test is to gradually increase the angular acceleration of the motor from a preset initial angular acceleration according to a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped 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 a preset angular acceleration gradient, and each time the angular acceleration is increased by one level, the motor speed is stepped from the rated speed to a static state under no-load conditions until the motor becomes unstable during operation; A speed-up model construction module is used to establish a first functional relationship between the maximum speed overshoot and the angular acceleration level value in the speed-up test, and a second functional relationship between the maximum speed stabilization accuracy and the angular acceleration level value in the speed-up test, using each angular acceleration level value before instability in the speed-up test as an independent variable and the maximum speed overshoot and the maximum speed stabilization accuracy under the corresponding angular acceleration level value as dependent variables; A deceleration model construction module is used to establish a third functional relationship between the maximum speed overshoot and the angular acceleration level value of the deceleration test, and a fourth functional relationship between the maximum speed overshoot and the angular acceleration level value of the deceleration test, using each angular acceleration level value before instability of the deceleration test as an independent variable and the maximum speed overshoot and maximum speed stabilization accuracy at the corresponding angular acceleration level value as dependent variables; The speed-up model analysis module is used to reversely calculate, based on the speed overshoot limit value and the speed stabilization 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 using a first functional relationship; and reversely calculate, based on the second functional relationship, a second speed-up angular acceleration limit value corresponding to the speed stabilization accuracy limit value; The first analysis module is configured to analyze and obtain the angular acceleration limit value of the motor during the speed-up process under load conditions based on 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; a deceleration model analysis module for reversely calculating, based on the compressor tester speed overshoot limit value and the steady speed accuracy limit value, a first deceleration angular acceleration limit value corresponding to the compressor tester speed overshoot limit value using a third functional relationship; and reversely calculating, based on the fourth functional relationship, a second deceleration angular acceleration limit value corresponding to the steady speed accuracy limit value; 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 based on 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 test compressor rotor.

6. The aircraft engine compressor tester power unit debugging system according to claim 5, characterized in that: In the first analysis module, the minimum value α of the first acceleration increase angular acceleration limit value and the second acceleration increase angular acceleration limit value is calculated. 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 the 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 deceleration test results. Analyze and obtain the angular acceleration limit value α of the motor during emergency braking under load conditions j .

Images