A method and system for evaluating performance of an engine test piece in a low-pressure environment

Abstract

The application relates to the field of aero-engine testing, and discloses a performance evaluation method and system for an engine test piece in a low-pressure environment. The method measures the pressure difference between an inlet measuring section of the test piece and the test environment pressure, and the pressure difference between the inlet measuring section and an outlet measuring section, so that the deviation of the pressure difference measurement value of the inlet measuring section and the pressure difference measurement value of the inlet and outlet changes in the same direction. The method can avoid the problem that the absolute error of the inlet and outlet pressures of the test piece is large in the prior art, which needs to measure the pressure differences between the inlet measuring section and the environment and between the outlet measuring section and the environment respectively. The method can effectively reduce the engine performance evaluation error caused by the measurement error of the inlet and outlet pressures of the engine test piece in the low-pressure environment, and realizes high-precision performance evaluation of the engine or engine components.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing, and discloses a method and system for evaluating the performance of engine test pieces under low-pressure conditions. Background Technology

[0002] When an aero-engine operates in a low-pressure environment, atmospheric pressure and internal engine airflow pressure are significantly lower than at ground level. Traditional pressure testing systems exhibit relatively small errors in conventional ground tests. However, in tests simulating low-pressure conditions, the relative testing error increases significantly due to the decrease in pressure measurements. This leads to a substantial increase in the error in evaluating engine parts, components, or engine performance, making it difficult to meet the accuracy requirements for performance evaluation. Summary of the Invention

[0003] The purpose of this invention is to provide a method and system for evaluating the performance of engine test pieces under low-pressure conditions. This method can effectively reduce the engine performance evaluation error caused by the measurement error of the inlet and outlet pressure of the engine test pieces under low-pressure conditions, and achieve high-precision performance evaluation of the engine or engine components.

[0004] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0005] A method for performance evaluation of engine test specimens under low-pressure conditions includes:

[0006] The pressure ratio of the aero-engine test piece is obtained through simulation. Based on the inlet pressure of the test piece and the pressure ratio under the operating conditions to be analyzed, the outlet pressure analysis value of the test piece is obtained.

[0007] Based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece is located, the range specification of the first scanning valve for measuring the first pressure difference is determined; based on the second pressure difference between the outlet pressure analysis value and the inlet pressure, the scanning valve with the smallest range specification for measuring the second pressure difference is selected as the second scanning valve.

[0008] The first differential pressure measurement value of the inlet measurement section of the test specimen is collected using the selected first scanning valve, and the second differential pressure measurement value between the outlet measurement section and the inlet measurement section of the test specimen is collected using the selected second scanning valve.

[0009] Based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperatures of the inlet and outlet measurement sections during measurement, the isentropic efficiency of the test specimen and the minimum threshold of the isentropic efficiency confidence interval are analyzed and obtained.

[0010] If the minimum threshold of the isentropic efficiency confidence interval is greater than the isentropic efficiency design requirement, then the performance of the test specimen meets the design requirements.

[0011] Furthermore, the isentropic efficiency of the test piece is based on Analysis yielded, among which The isentropic efficiency of the test specimen. The first differential pressure measurement value obtained by the first scanning valve. To test environmental stress, The second differential pressure measurement value obtained from the second scanning valve. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

[0012] Further, a first confidence interval boundary threshold for the first differential pressure measurement is calculated based on the measurement error of the selected first scanning valve, and a second confidence interval boundary threshold for the second differential pressure measurement is calculated based on the measurement error of the selected second scanning valve.

[0013] Based on the first confidence interval threshold and the second confidence interval threshold, using The minimum threshold of the isentropic efficiency confidence interval was obtained through analysis. ;in This is the upper or lower limit of the threshold value of the first confidence interval for the first differential pressure measurement. To test environmental stress, This refers to the upper or lower limit of the threshold value of the second confidence interval for the second differential pressure measurement. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

[0014] Furthermore, the method for determining the range specification of the first scanning valve for measuring the first differential pressure includes: selecting a scanning valve with the smallest range specification for measuring the first differential pressure as the first scanning valve based on the first differential pressure between the inlet pressure and the test environment pressure.

[0015] To achieve the above-mentioned technical effects, the present invention also provides a performance evaluation system for engine test specimens under low-pressure conditions, comprising:

[0016] The simulation analysis module is used to simulate and obtain the pressure ratio of the aero-engine test piece. Based on the inlet pressure of the test piece and the pressure ratio under the operating conditions to be analyzed, the outlet pressure analysis value of the test piece is obtained.

[0017] The scanning valve specification determination module is used to determine the range specification of the first scanning valve for measuring the first pressure difference based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece is located; and to select the scanning valve with the smallest range specification for measuring the second pressure difference as the second scanning valve based on the second pressure difference between the outlet pressure analysis value and the inlet pressure.

[0018] The data acquisition module is used to acquire the first differential pressure measurement value of the inlet measurement section of the test specimen using the selected first scanning valve, and to acquire the second differential pressure measurement value between the outlet measurement section and the inlet measurement section of the test specimen using the selected second scanning valve;

[0019] The data analysis module is used to analyze and obtain the isentropic efficiency and the minimum threshold of the isentropic efficiency confidence interval of the test piece based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperature of the inlet and outlet measurement sections during measurement.

[0020] The evaluation module is used to compare the minimum threshold of the isentropic efficiency confidence interval with the design requirement value of isentropic efficiency. If the minimum threshold of the isentropic efficiency confidence interval is greater than the design requirement value of isentropic efficiency, then the performance of the test piece meets the design requirements.

[0021] Furthermore, in the data analysis module, the isentropic efficiency of the test piece is based on... Analysis yielded, among which The isentropic efficiency of the test specimen. The first differential pressure measurement value obtained by the first scanning valve. To test environmental stress, The second differential pressure measurement value obtained from the second scanning valve. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

[0022] Furthermore, the method for determining the preset threshold in the evaluation module includes:

[0023] Calculate the first confidence interval boundary threshold of the first differential pressure measurement value based on the measurement error of the selected first scanning valve, and calculate the second confidence interval boundary threshold of the second differential pressure measurement value based on the measurement error of the selected second scanning valve;

[0024] Based on the first confidence interval threshold and the second confidence interval threshold, using The minimum threshold of the isentropic efficiency confidence interval was obtained through analysis. ;in This is the upper or lower limit of the threshold value of the first confidence interval for the first differential pressure measurement. To test environmental stress, This refers to the upper or lower limit of the threshold value of the second confidence interval for the second differential pressure measurement. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

[0025] Furthermore, in the scanning valve specification determination module, based on the first pressure difference between the inlet pressure and the test environment pressure, a scanning valve with the smallest range specification for measuring the first pressure difference is selected as the first scanning valve.

[0026] Furthermore, the first scanning valve includes a first reference end and a first measuring end. The first measuring end is connected to a pressure probe at the inlet measuring section of the aero-engine test piece via a connecting pipeline, and is used to collect the pressure at the inlet measuring section of the test piece.

[0027] The second scanning valve includes a second reference end and a second measuring end. The second reference end is connected to the connecting pipeline through a tee connector, and the second measuring end is connected to a pressure probe at the outlet measuring section of the aero-engine test piece for collecting the pressure at the outlet measuring section of the test piece.

[0028] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention achieves the same direction of deviation between the pressure difference between the inlet measuring section and the test environment pressure, and between the inlet measuring section and the outlet measuring section by measuring the pressure difference between the inlet measuring section and the outlet measuring section. It also avoids the problem of large absolute errors in the inlet and outlet pressures of the test piece in the prior art, which requires separate measurement of the pressure difference between the inlet measuring section and the environment and the pressure difference between the outlet measuring section and the environment. It can effectively reduce the engine performance evaluation error caused by the inlet and outlet pressure measurement error of the engine test piece under low-pressure environment conditions, and achieve high-precision performance evaluation of the engine or engine components. Attached Figure Description

[0029] Figure 1 This is a flowchart of the performance evaluation method for engine test specimens under low-pressure conditions in Example 1 or 2;

[0030] Figure 2 This is a schematic diagram showing the installation of the first scanning valve, the second scanning valve, and the test piece in Example 1 or 2.

[0031] Figure 3 This is a block diagram of the performance evaluation system for engine test specimens under low-pressure conditions in Example 1;

[0032] Figure 4 This is a schematic diagram of the scanning valve installation for measuring the compressor inlet and outlet pressures in Example 2;

[0033] The components include: 1. Test piece; 2. First scanning valve; 3. Second scanning valve; 4. Inlet measurement section; 5. Outlet measurement section; 6. Simulation analysis module; 7. Scanning valve specification determination module; 8. Data acquisition module; 9. Data analysis module; 10. Evaluation module; and 11. Pressure probe. Detailed Implementation

[0034] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0035] Example 1

[0036] See Figure 1 , Figure 2 and Figure 3 A method for evaluating the performance of engine test pieces under low-pressure conditions, comprising:

[0037] The pressure ratio of the aero-engine test piece 1 is obtained through simulation. Based on the inlet pressure of the test piece 1 under the operating conditions to be analyzed and the pressure ratio, the outlet pressure analysis value of the test piece 1 is obtained through analysis.

[0038] Based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece 1 is located, the range specification of the first scanning valve 2 for measuring the first pressure difference is determined; based on the second pressure difference between the outlet pressure analysis value and the inlet pressure, the scanning valve with the smallest range specification for measuring the second pressure difference is selected as the second scanning valve 3.

[0039] The first differential pressure measurement value of the inlet measuring section 4 of the test specimen 1 is collected using the selected first scanning valve 2, and the second differential pressure measurement value of the outlet measuring section 5 and the inlet measuring section 4 of the test specimen 1 is collected using the selected second scanning valve 3.

[0040] Based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperatures of the inlet measurement section 4 and the outlet measurement section 5 during measurement, the isentropic efficiency of the test piece 1 is analyzed and obtained.

[0041] If the minimum threshold of the isentropic efficiency confidence interval is greater than the isentropic efficiency design requirement, then the performance of the test specimen meets the design requirements.

[0042] In this embodiment, the pressure ratio of the aero-engine test piece 1 is obtained through simulation to determine the outlet pressure analysis value of the test piece 1. Based on the pressure difference between the outlet pressure analysis value and the inlet pressure, a scanning valve with the smallest range specification for measuring the second pressure difference is selected as the second scanning valve 3. The selected first scanning valve 2 is used to collect the pressure difference measurement value between the inlet measurement section 4 of the test piece 1 and the test environment pressure. The selected second scanning valve 3 is used to collect the pressure difference measurement value between the inlet measurement section 4 and the outlet measurement section 5 of the test piece 1. Based on the pressure difference measurement value between the inlet measurement section 4 and the outlet measurement section 5, the test environment pressure, and the temperature data during measurement, the isentropic efficiency of the test piece 1 is calculated. The measurement error of the first scanning valve 2 and the measurement error of the second scanning valve 3 are used to calculate the pressure difference. The invention calculates the minimum threshold of the confidence interval for isentropic efficiency by taking the test error and then determining whether the performance of test piece 1 meets the design requirements. This invention enables the deviations between the calculated pressure values ​​at the inlet measuring section 4 and the outlet measuring section 5 to change in the same direction, resulting in a narrower confidence interval for isentropic efficiency. It also avoids the problem in existing technologies where separate measurements of the pressure difference between the inlet measuring section 4 and the environment, and the pressure difference between the outlet measuring section 5 and the environment, lead to large absolute errors in the inlet and outlet pressures of test piece 1, and the independent inlet and outlet pressure errors result in a wider confidence interval for isentropic efficiency. This invention effectively reduces engine performance evaluation errors caused by inlet and outlet pressure measurement errors in engine test piece 1 under low-pressure conditions, achieving high-precision performance evaluation of the engine or engine components.

[0043] Based on the same inventive concept, this embodiment also provides a performance evaluation system for engine test piece 1 under low-pressure conditions, including:

[0044] The simulation analysis module 6 is used to simulate and obtain the pressure ratio of the aero-engine test piece 1. Based on the inlet pressure of the test piece 1 under the operating conditions to be analyzed and the pressure ratio, the outlet pressure analysis value of the test piece 1 is obtained.

[0045] The scanning valve specification determination module 7 is used to determine the range specification of the first scanning valve 2 for measuring the first pressure difference based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece 1 is located; and to select the scanning valve with the smallest range specification for measuring the second pressure difference as the second scanning valve 3 based on the second pressure difference between the outlet pressure analysis value and the inlet pressure.

[0046] The data acquisition module 8 is used to acquire the first differential pressure measurement value of the inlet measuring section 4 of the test piece 1 using the selected first scanning valve 2, and to acquire the second differential pressure measurement value between the outlet measuring section 5 and the inlet measuring section 4 of the test piece 1 using the selected second scanning valve 3;

[0047] Data analysis module 9 is used to analyze and obtain the isentropic efficiency of the test piece 1 based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperature of the inlet measurement section 4 and the outlet measurement section 5 during measurement.

[0048] Evaluation module 10 is used to compare the minimum threshold of the isentropic efficiency confidence interval with the design requirement value of isentropic efficiency. If the minimum threshold of the isentropic efficiency confidence interval is greater than the design requirement value of isentropic efficiency, then the performance of the test piece 1 meets the design requirements.

[0049] Example 2

[0050] See Figure 1 and Figure 2 This embodiment uses a compressor as test piece 1 as an example to describe in detail the performance evaluation method flow of the engine test piece 1 under low pressure environment of the present invention. The evaluation method flow is as follows:

[0051] Step 1: Simulate to obtain the pressure ratio of test specimen 1 of the aero-engine. Based on the inlet pressure of test specimen 1 and the pressure ratio under the operating conditions to be analyzed, analyze and obtain the outlet pressure analysis value of test specimen 1.

[0052] In this embodiment, the true pressure ratio of the compressor was obtained through simulation analysis. The test conditions simulated a high-altitude atmospheric environment, with an inlet pressure of [missing information]. Therefore, the outlet pressure analysis value of the test piece 1 was obtained through analysis. .

[0053] Step 2: Based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece 1 is located, determine the range specification of the first scanning valve 2 for measuring the first pressure difference; based on the second pressure difference between the outlet pressure analysis value and the inlet pressure, select the scanning valve with the smallest range specification for measuring the second pressure difference as the second scanning valve 3.

[0054] In this embodiment, a large-range scanning valve is used as the first scanning valve 2 to measure the compressor inlet pressure, which is the first pressure difference between the compressor inlet measurement section 4 and the atmospheric environment. Since the second pressure difference (5 kPa) between the outlet pressure analysis value and the inlet pressure is less than the outlet pressure analysis value (10 kPa), a small-range scanning valve is used as the second scanning valve 3 to measure the compressor inlet-outlet pressure difference, which is the second pressure difference between the outlet pressure analysis value and the inlet pressure. The large-range scanning valve has a range of 100 kPa and a measurement error of 0.5‰ of full scale, i.e., a measurement error of ±50 Pa. The small-range scanning valve has a range of 10 kPa and a measurement error of 0.5‰ of full scale, i.e., a measurement error of ±5 Pa. Therefore, the compressor inlet pressure measurement value is within the range of 5000 ± 50 Pa, and the compressor inlet-outlet pressure difference measurement value is within the range of 5000 ± 5 Pa, significantly reducing the measurement error.

[0055] Step 3: Use the selected first scanning valve 2 to collect the first differential pressure measurement value at the inlet measurement section 4 of test piece 1. The second differential pressure measurement value between the outlet measuring section 5 and the inlet measuring section 4 of the test specimen 1 is collected using the selected second scanning valve 3. ;

[0056] In this embodiment, the first scanning valve 2 includes a first reference end and a first measuring end. The first measuring end is connected to the pressure probe 11 of the inlet measuring section 4 of the aero-engine test piece 1 through a connecting pipeline, and is used to collect the pressure of the inlet measuring section 4 of the test piece 1.

[0057] The second scanning valve 3 includes a second reference end and a second measuring end. The second reference end is connected to the connecting pipeline through a three-way pipe joint. The second measuring end is connected to the pressure probe 11 at the outlet measuring section 5 of the aero-engine test piece 1, and is used to collect the pressure at the outlet measuring section 5 of the test piece 1.

[0058] Step 4: Based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperatures of the inlet measurement section 4 and the outlet measurement section 5 during measurement, analyze and obtain the isentropic efficiency of the test piece 1.

[0059] In this embodiment, the isentropic efficiency of the test piece 1 is based on Analysis yielded, among which The isentropic efficiency of test piece 1, The first differential pressure measurement value obtained by the first scanning valve 2. To test environmental stress, The second differential pressure measurement value obtained by the second scanning valve 3. The temperature of the inlet measuring section 4, The temperature of section 5 at the outlet is measured.

[0060] Step 5: Determine the difference between the minimum threshold of the isentropic efficiency confidence interval and the design requirement value of the isentropic efficiency. If the minimum threshold of the isentropic efficiency confidence interval is greater than the design requirement value of the isentropic efficiency, then the performance of the test piece meets the design requirements.

[0061] The preset threshold in this embodiment is determined according to the following steps:

[0062] 5.1 Calculate the first confidence interval boundary threshold of the first differential pressure measurement value based on the measurement error of the selected first scanning valve 2, and calculate the second confidence interval boundary threshold of the second differential pressure measurement value based on the measurement error of the selected second scanning valve 3;

[0063] 5.2 Based on the first confidence interval threshold and the second confidence interval threshold, using... The minimum threshold of the isentropic efficiency confidence interval was obtained through analysis. ;in This is the upper or lower limit of the threshold value of the first confidence interval for the first differential pressure measurement. To test environmental stress, This refers to the upper or lower limit of the threshold value of the second confidence interval for the second differential pressure measurement. The temperature of the inlet measuring section 4, The temperature at the outlet section 5 was measured. The minimum threshold of this confidence interval was set to fully consider the possible error range during the measurement process. Through the analysis of the confidence interval, the scientific validity and rationality of the threshold were ensured, ensuring that the performance of engine test piece 1 under low-pressure environment could be effectively evaluated, thereby providing strong support for engine research and development and optimization.

[0064] See Figure 4 In existing technology, two large-range scanning valves are used to directly measure the compressor inlet and outlet pressures. The scanning valve range is 100 kPa, and the measurement error is 0.5‰ of full scale, i.e., ±50 Pa. Therefore, the measured compressor inlet pressure is within the range of 5000 ± 50 Pa, and the measured compressor outlet pressure is within the range of 10000 ± 50 Pa. Based on this, the calculated isentropic efficiency of the compressor is within the range of 85.9% to 90.1%, corresponding to an absolute error of -2.1% to 2.1%, which is relatively large.

[0065] According to the evaluation method of this embodiment, based on the isentropic efficiency calculation formula of test piece 1... It can be seen that the calculated isentropic efficiency of the compressor is in the range of 87.4% to 88.8%, and the absolute error of the efficiency calculation is in the range of -0.6% to +0.8%, which is a significant reduction in error.

[0066] To further reduce the measurement error of the first scanning valve 2 and achieve high-precision performance evaluation of the compressor, in some other embodiments, based on the first pressure difference between the inlet pressure and the test environment pressure, the scanning valve with the smallest range specification for measuring the first pressure difference is selected as the first scanning valve 2, such as a large-range scanning valve with a range of 50 kPa.

[0067] The above are merely 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 within the scope of protection of the present invention.

Claims

1. A method for performance evaluation of engine test specimens under low-pressure conditions, characterized in that, include: The pressure ratio of the aero-engine test piece is obtained through simulation. Based on the inlet pressure of the test piece and the pressure ratio under the operating conditions to be analyzed, the outlet pressure analysis value of the test piece is obtained. Based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece is located, the range specification of the first scanning valve for measuring the first pressure difference is determined; based on the second pressure difference between the outlet pressure analysis value and the inlet pressure, the scanning valve with the smallest range specification for measuring the second pressure difference is selected as the second scanning valve. The first differential pressure measurement value of the inlet measurement section of the test specimen is collected using the selected first scanning valve, and the second differential pressure measurement value between the outlet measurement section and the inlet measurement section of the test specimen is collected using the selected second scanning valve. Based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperatures of the inlet and outlet measurement sections during measurement, the isentropic efficiency of the test specimen and the minimum threshold of the isentropic efficiency confidence interval are analyzed and obtained. If the minimum threshold of the isentropic efficiency confidence interval is greater than the isentropic efficiency design requirement, then the performance of the test specimen meets the design requirements.

2. The performance evaluation method according to claim 1, characterized in that, The isentropic efficiency of the test piece is based on Analysis yielded, among which The isentropic efficiency of the test specimen. The first differential pressure measurement value obtained by the first scanning valve. To test environmental stress, The second differential pressure measurement value obtained from the second scanning valve. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

3. The performance evaluation method according to claim 2, characterized in that, Calculate the first confidence interval boundary threshold of the first differential pressure measurement value based on the measurement error of the selected first scanning valve, and calculate the second confidence interval boundary threshold of the second differential pressure measurement value based on the measurement error of the selected second scanning valve; Based on the first confidence interval threshold and the second confidence interval threshold, using The minimum threshold of the isentropic efficiency confidence interval was obtained through analysis. ;in This is the upper or lower limit of the threshold value of the first confidence interval for the first differential pressure measurement. To test environmental stress, This refers to the upper or lower limit of the threshold value of the second confidence interval for the second differential pressure measurement. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

4. The performance evaluation method according to claim 1, characterized in that, The method for determining the range specification of the first scanning valve for measuring the first differential pressure includes: selecting the scanning valve with the smallest range specification for measuring the first differential pressure as the first scanning valve based on the first differential pressure between the inlet pressure and the test environment pressure.

5. A performance evaluation system for engine test pieces under low-pressure conditions, characterized in that, include: The simulation analysis module is used to simulate and obtain the pressure ratio of the aero-engine test piece. Based on the inlet pressure of the test piece and the pressure ratio under the operating conditions to be analyzed, the outlet pressure analysis value of the test piece is obtained. The scanning valve specification determination module is used to determine the range specification of the first scanning valve for measuring the first pressure difference based on the first pressure difference between the inlet pressure and the test environment pressure where the test piece is located; and to select the scanning valve with the smallest range specification for measuring the second pressure difference as the second scanning valve based on the second pressure difference between the outlet pressure analysis value and the inlet pressure. The data acquisition module is used to acquire the first differential pressure measurement value of the inlet measurement section of the test specimen using the selected first scanning valve, and to acquire the second differential pressure measurement value between the outlet measurement section and the inlet measurement section of the test specimen using the selected second scanning valve; The data analysis module is used to analyze and obtain the isentropic efficiency and the minimum threshold of the isentropic efficiency confidence interval of the test piece based on the first differential pressure measurement value, the second differential pressure measurement value, the test environment pressure, and the temperature of the inlet and outlet measurement sections during measurement. The evaluation module is used to compare the minimum threshold of the isentropic efficiency confidence interval with the design requirement value of isentropic efficiency. If the minimum threshold of the isentropic efficiency confidence interval is greater than the design requirement value of isentropic efficiency, then the performance of the test piece meets the design requirements.

6. The performance evaluation system according to claim 5, characterized in that, In the data analysis module, the isentropic efficiency of the test piece is based on Analysis yielded, among which The isentropic efficiency of the test specimen. The first differential pressure measurement value obtained by the first scanning valve. To test environmental stress, The second differential pressure measurement value obtained from the second scanning valve. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

7. The performance evaluation system according to claim 6, characterized in that, The method for determining the minimum threshold of the isentropic efficiency confidence interval in the data analysis module includes: Calculate the first confidence interval boundary threshold of the first differential pressure measurement value based on the measurement error of the selected first scanning valve, and calculate the second confidence interval boundary threshold of the second differential pressure measurement value based on the measurement error of the selected second scanning valve; Based on the first confidence interval threshold and the second confidence interval threshold, using The minimum threshold of the isentropic efficiency confidence interval was obtained through analysis. ;in This is the upper or lower limit of the threshold value of the first confidence interval for the first differential pressure measurement. To test environmental stress, This refers to the upper or lower limit of the threshold value of the second confidence interval for the second differential pressure measurement. For the temperature of the inlet measuring section, The temperature of the outlet section is measured.

8. The performance evaluation system according to claim 5, characterized in that, In the scanning valve specification determination module, based on the first pressure difference between the inlet pressure and the test environment pressure, the scanning valve with the smallest range specification for measuring the first pressure difference is selected as the first scanning valve.

9. The performance evaluation system according to claim 5, characterized in that, The first scanning valve includes a first reference end and a first measuring end. The first measuring end is connected to a pressure probe at the inlet measuring section of the aero-engine test piece via a connecting pipeline, and is used to collect the pressure at the inlet measuring section of the test piece. The second scanning valve includes a second reference end and a second measuring end. The second reference end is connected to the connecting pipeline through a tee connector, and the second measuring end is connected to a pressure probe at the outlet measuring section of the aero-engine test piece for collecting the pressure at the outlet measuring section of the test piece.

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