A method for calibrating engine in-flight performance parameters to the same operating point

Abstract

The application belongs to the field of aero-engine design, and a calculation method for calibrating engine in-flight performance parameters to the same working condition point is provided. First, a high-altitude performance reference point is selected. Then, after obtaining steady-state performance data of different test working condition points in the engine working envelope, the relative relationship of performance correction factors of each component under different working condition points and the high-altitude performance reference point is obtained through identification calculation. The relationship considers the influence of different engine states and inlet flow conditions on the performance of each component of the engine. Meanwhile, the identification calculation result of the current test data considers the influence of performance attenuation. Finally, the in-flight performance parameter calibration calculation is completed according to the high-altitude performance reference point, the relative relationship of performance correction factors of each component of different working condition points, the current test data and the steady-state performance model. The method effectively improves the parameter calculation accuracy of the in-flight performance test data calibration calculation to the same high-altitude performance reference point.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to a calculation method for calibrating engine air performance parameters to the same operating point. Background Technology

[0002] During each flight mission within its operational envelope, an aero-engine typically operates at varying altitudes, Mach numbers, ambient temperatures, and engine speeds. To compare performance parameter changes at different high-altitude operating points and effectively identify and monitor potential parameter anomalies and performance variations, it is necessary to calibrate and calculate performance test data from different flight sorties to the same high-altitude performance reference point for unified comparative analysis.

[0003] The existing technical solution involves using dimensionless parameter similarity conversion to obtain performance parameter values ​​for a high-altitude performance reference point based on test data from different flight sorties, and then conducting comparative analysis. The main calculation steps are as follows:

[0004] Step 1: Set the altitude, Mach number, ambient temperature deviation, and engine status of the high-altitude performance reference point;

[0005] Step 2: Select and process steady-state performance data at the current operating point and under the engine's operating conditions;

[0006] Step 3: Based on the relationship between the current test performance parameters and the rotational speed, interpolate and calculate the performance parameters at the reference point rotational speed.

[0007] Step 4: Obtain the performance parameters of the reference point through dimensionless parameter similarity conversion, where P in formulas (1-3) ref T represents the total pressure at the reference point. ref X represents the total temperature at the reference point. C This represents the result after similarity conversion;

[0008]

[0009]

[0010]

[0011] The problem with existing technical solutions is that the premise for the validity of similarity conversion results is that the similarity parameters characterizing the engine flow field (geometric configuration, gas constant, specific heat ratio, engine state, Mach number, and Reynolds number) are equal. Among these, the gas constant and specific heat ratio have relatively small effects. Engines will experience a certain degree of performance degradation during long-term operation. If the dimensionless parameter conversion is performed with the exponents θ and δ remaining constant during the calculation process, the similarity conversion results will have small deviations when the difference between the operating points is small. However, when the difference between the operating points is large and the influence of the incoming flow conditions (Mach number and Reynolds number) is significant, the similarity conversion results will have large deviations.

[0012] Therefore, how to more accurately calibrate the engine's air performance parameters to the same high-altitude performance reference point for comparative analysis is a problem that needs to be solved. Summary of the Invention

[0013] The purpose of this application is to provide a calculation method for calibrating engine air performance parameters to the same operating point, so as to solve the problem in the prior art that test results of engine performance parameters at different operating points during high-altitude flight cannot be directly compared.

[0014] The technical solution of this application is: a calculation method for calibrating engine air performance parameters to the same operating condition point, comprising:

[0015] Select typical operating conditions of the aircraft as reference points for high-altitude performance, and set specific parameter values ​​corresponding to the high-altitude performance reference points.

[0016] Select and process the steady-state performance data of the engine at the current test operating point;

[0017] Based on the relationship between the performance parameters at the current test point and the rotational speed, the test results of the performance parameters at the reference point rotational speed are calculated by interpolation.

[0018] Obtain steady-state performance test results of the engine at different altitudes, Mach numbers and engine states within the working envelope; identify and calculate the performance correction factors of each component corresponding to the test data at the current operating point; and calculate the relative relationship of the performance correction factors of each component between test data at different operating points and reference points.

[0019] Based on the relative relationship between the performance correction factors of each component and the test data of different operating points and reference points, the performance correction factors of each component at the reference point corresponding to the test data of the current operating point are calculated.

[0020] Input the altitude, Mach number, ambient temperature deviation, and performance correction factors of each component after conversion of the high-altitude performance reference point, and calculate the performance parameter values ​​of the current test point at the high-altitude performance reference point through the steady-state performance model.

[0021] Preferably, the steady-state performance data is obtained by averaging and includes operating parameters, control parameters, overall performance parameters, and cross-sectional temperature and pressure parameters.

[0022] Preferably, the formula for calculating the performance parameter value of the reference point rotational speed state is:

[0023]

[0024] In formula (4), Y represents the engine performance parameter, N1r represents the low-pressure rotor conversion speed, the subscript start represents the starting speed of the interpolation calculation, the subscript end represents the ending speed of the interpolation calculation, and the subscript current represents the speed corresponding to the high-altitude performance reference point.

[0025] Preferably, the steady-state performance test data of different altitudes, Mach numbers and engine states within the engine's working envelope are selected to identify and calculate the performance correction factors of each component corresponding to different test conditions; the performance correction factors of each component corresponding to the high-altitude performance reference point are identified and calculated based on the test data of the reference condition point; the relative relationship of the performance correction factors of each component at different test conditions and the high-altitude performance reference point is calculated by combining formula (5), and a numerical table of three dimensions of environmental pressure, Mach number and engine state is formed.

[0026]

[0027] Wherein, AnsynCurrent is the performance correction factor for each component identified and calculated based on the test data at the current operating point, AnsynReference is the performance correction factor for each component identified and calculated based on the test data at the reference operating point, and AnsynRelative is the relative value of the performance correction factor for each component between the reference operating point and the current test point.

[0028] Preferably, the calculation method for the performance correction factors of each component is as follows:

[0029] The specific formula for calculating and analyzing the engine's airflow performance is as follows:

[0030] Z = h(X)(6)

[0031] In the formula, h represents the functional relationship between the measurement parameters and the component performance correction factor, which is expressed by the steady-state performance model, Z represents the measurement parameter vector, and X represents the component performance correction factor vector.

[0032] If the performance of a component changes, δ represents the degree of parameter change. A first-order Taylor series expansion of h(x) at a given operating point yields:

[0033] h(X+δX)=h(X)+H·δX+HOT(7)

[0034] The influence parameter matrix H is obtained, and its mathematical expression is:

[0035]

[0036] Ignoring the influence of higher-order terms in the parameter matrix H, we obtain:

[0037] h(X+δX)=h(X)+H·δX(9)

[0038] The following was obtained through matrix transformation:

[0039] δX=(H T H) -1 H T δZ(10)

[0040] The nonlinear equations are solved using the Newton-Raphson algorithm to obtain the calculated values ​​of the performance correction factors for each component that meet the accuracy requirements of the objective function measurement parameters.

[0041] Preferably, the formula for calculating the performance correction factor of each component corresponding to the current test data at the high-altitude performance reference point is as follows:

[0042] AnsynRelative=f(N1r,Pamb,Ma)(11)

[0043] AnsynReference_Test=AnsynRelative*AnsynCurrent(12)

[0044] In formula (11), N1r represents the converted speed of the low-pressure rotor at the high-altitude performance reference point, Pamb represents the ambient pressure at the current test operating point, Ma represents the Mach number at the current test operating point, and f represents the 3D linear interpolation calculation; in formula (12), AnsynCurrent is the performance correction factor of each component identified and calculated based on the test data at the current operating point, AnsynRelative is the relative ratio of the performance correction factors of each component at the current test operating point and the high-altitude performance reference point, and AnsynReference_Test is the performance correction factor of each component at the high-altitude performance reference point corresponding to the test data at the current operating point.

[0045] Preferably, the formula for calculating the performance parameter value at the high-altitude performance reference point corresponding to the current operating point test data is as follows:

[0046] Reference point performance parameters = f(Pamb,Ma,ΔTamb,N1r,AnsynReference_Test)(13)

[0047] In the formula, Pamb represents the ambient pressure at the high-altitude performance reference point, N1r represents the converted speed of the low-pressure rotor at the high-altitude performance reference point, Ma represents the Mach number at the high-altitude performance reference point, ΔTamb represents the ambient temperature deviation at the high-altitude performance reference point, AnsynReference_Test is the performance correction factor for each component at the high-altitude performance reference point corresponding to the test data at the current operating point, and f is the engine steady-state performance model.

[0048] This application discloses a calculation method for calibrating engine in-flight performance parameters to the same operating point. First, a high-altitude performance reference point is selected and specific parameter values ​​are set. After obtaining steady-state performance test data at different test operating points within the engine's operating envelope, performance correction factors for each component at different test operating points are identified and calculated. The relative relationship between these component performance correction factors under different operating points and the high-altitude performance reference point is obtained. This relationship considers the influence of different engine states and incoming flow conditions (Mach number and Reynolds number) on the performance of each engine component. Simultaneously, the impact of performance degradation is considered in the identification and calculation of the current test data. Finally, calibration calculations are completed based on the high-altitude performance reference point, the converted component performance correction factors, the current test data, and the steady-state performance model. This method effectively improves the accuracy of parameter calculations for calibrating in-flight test data to the same high-altitude performance reference point, providing a strong basis for designers to conduct engine gas path performance analysis. Attached Figure Description

[0049] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0050] Figure 1 This is a schematic diagram of the overall process of this application. Detailed Implementation

[0051] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0052] A calculation method for calibrating engine in-flight performance parameters to the same operating point, such as... Figure 1 As shown, it includes the following steps:

[0053] Step S100: Select typical operating conditions commonly used by the aircraft as high-altitude performance reference points, and set the specific parameter values ​​for the corresponding high-altitude performance reference points.

[0054] Typical operating conditions commonly used in aircraft flight are selected. The parameters of the high-altitude performance reference point include altitude, Mach number, ambient temperature deviation, and engine status. Specific parameter values ​​are set according to the actual working conditions of the engine.

[0055] Step S200: Select and process the steady-state performance data of the engine operating state at the current test condition point;

[0056] Steady-state performance data are obtained through mean calculation, including operating parameters, control parameters, overall performance parameters, and cross-sectional temperature and pressure parameters. Random errors in the measurement results can be removed using a moving average method.

[0057] Step S300: Based on the relationship between the performance parameter test results at the current operating point and the rotational speed, interpolate and calculate the performance parameter test results at the reference point rotational speed.

[0058] Preferably, the formula for calculating the performance parameter test results at the reference point speed state is:

[0059]

[0060] In formula (1), Y represents the engine performance parameters, N1r represents the low-pressure rotor conversion speed, the subscript start represents the starting speed of the interpolation calculation, the subscript end represents the ending speed of the interpolation calculation, and the subscript current represents the speed corresponding to the high-altitude performance reference point.

[0061] By interpolating the results at a given reference point speed, the test results at different operating points are unified to the same speed, thus avoiding the impact of engine speed deviation.

[0062] Step S400: Obtain the steady-state performance test results at different altitudes, Mach numbers and engine states within the engine's working envelope, and calculate the relative relationship between the performance correction factors of each component corresponding to the test data of different operating points and high-altitude performance reference points.

[0063] Steady-state performance test results were selected at different altitudes, Mach numbers, and engine states within the engine's operating envelope. The engine should not show significant performance degradation. The corresponding performance correction factors for each component were identified and calculated through the steady-state performance model. The engine states included idle, throttle, cruise, climb, continuous, and takeoff operating states.

[0064] Preferably, the calculation method for the relative relationship between the performance correction factors of each component corresponding to the test data of different operating points and high-altitude performance reference points is as follows:

[0065] Steady-state performance test data at different altitudes, Mach numbers and engine states are selected within the engine's working envelope. Performance correction factors for each component corresponding to different test conditions are identified and calculated. Performance correction factors for each component corresponding to the high-altitude performance reference point are identified and calculated based on the test data of the reference condition point. The relative relationship between performance correction factors for each component at different test conditions and the high-altitude performance reference point is calculated using formula (2). Numerical tables for three dimensions—environmental pressure, Mach number and engine state—are formed.

[0066]

[0067] Wherein, AnsynCurrent is the performance correction factor for each component identified and calculated based on the test data at the current operating point, AnsynReference is the performance correction factor for each component identified and calculated based on the test data at the reference point, and AnsynRelative is the relative value of the performance correction factor for each component between the reference point and the current test point.

[0068] The performance correction factors for each component include the efficiency and converted flow correction of the fan, booster stage, high-pressure compressor, high-pressure turbine, and low-pressure turbine, as well as the nozzle flow coefficient correction.

[0069] Step S500: Identify and calculate the performance correction factors for each component in the current operating condition test data;

[0070] Since the performance parameters of components cannot be directly measured, it is necessary to calculate and analyze the changes in the performance of each component by measuring the changes in the parameters.

[0071] The calculation method for the performance correction factor of each component is as follows:

[0072] At a given engine operating point, the gas path performance is calculated and analyzed. The specific formula is as follows:

[0073] Z=h(X) (3)

[0074] In the formula, h represents the functional relationship between the measurement parameters and the component performance correction factor, which is expressed by the steady-state performance model, Z represents the measurement parameter vector, and X represents the component performance correction factor vector.

[0075] If the performance of a component changes, δ represents the degree of parameter change. A first-order Taylor series expansion of h(x) at a given operating point yields:

[0076] h(X+δX)=h(X)+H·δX+HOT (4)

[0077] The influence parameter matrix H is obtained, and its mathematical expression is:

[0078]

[0079] Ignoring the influence of higher-order terms in the parameter matrix H, we obtain:

[0080] h(X+δX)=h(X)+H·δX (6)

[0081] The following was obtained through matrix transformation:

[0082] δX=(H T H) -1 H T δZ (7)

[0083] Based on the parameter relationship in formula (7), the nonlinear equation system is solved by the Newton-Raphson algorithm to obtain the calculated values ​​of the performance correction factors of each component that meet the accuracy requirements of the objective function measurement parameters.

[0084] The performance correction factor vector X of each component is solved by formulas (3) to (7), thereby accurately obtaining the numerical solution of the performance correction factor of each engine component. The engine components include components such as fan, compressor, turbine and nozzle.

[0085] The calculated results of the performance correction factors of each component correspond to the test results (altitude, Mach number and engine condition) at the actual operating conditions, so that the relative relationship of the component performance correction factors between different test operating conditions can be obtained.

[0086] Step S600: Based on the relative relationship of component performance correction factors at different operating points, interpolate and calculate the performance correction factors of each component at the high-altitude performance reference point corresponding to the current test operating point.

[0087] Using formula (10), the relative relationship between the performance correction factors of each component at the reference point and the current operating point is calculated by interpolation of N1r, Pamb and Ma. Using formula (11), the component performance correction factor AnsynReference_Test at the high-altitude performance reference point of the test data at the current operating point is calculated.

[0088] AnsynRelative=f(N1r,Pamb,Ma)(10)

[0089] AnsynReference_Test=AnsynRelative*AnsynCurrent(11)

[0090] In formula (10), N1r represents the converted speed of the low-pressure rotor at the high-altitude performance reference point, Pamb represents the ambient pressure at the current test operating point, Ma represents the Mach number at the current test operating point, and f represents the 3D linear interpolation calculation; in formula (11), AnsynCurrent is the performance correction factor of each component identified and calculated based on the test data at the current operating point, AnsynRelative is the relative ratio of the performance correction factors of each component at the current test operating point and the high-altitude performance reference point, and AnsynReference_Test is the performance correction factor of each component at the high-altitude performance reference point corresponding to the test data at the current operating point.

[0091] Step S700: Input the altitude, Mach number, ambient temperature deviation, engine status, and performance correction factors of each component after conversion of the high-altitude performance reference point. Calculate the performance parameter values ​​of the current test point at the high-altitude performance reference point using the steady-state performance model.

[0092] The calculation formula for the performance parameters of the current test point at the high-altitude performance reference point is as follows:

[0093] Reference point performance parameters = f(Pamb,Ma,ΔTamb,N1r,AnsynReference_Test)(12)

[0094] In formula (12), Pamb represents the ambient pressure at the high-altitude performance reference point, N1r represents the converted speed of the low-pressure rotor at the high-altitude performance reference point, Ma represents the Mach number at the high-altitude performance reference point, ΔTamb represents the ambient temperature deviation at the high-altitude performance reference point, AnsynReference_Test is the performance correction factor of each component at the high-altitude performance reference point corresponding to the test data at the current operating point, and f is the engine steady-state performance model.

[0095] This step allows for the calibration and conversion of aerial performance parameters at different operating points to the same high-altitude performance reference point, enabling unified comparison and ensuring the effectiveness of test data analysis.

[0096] This application first selects a high-altitude performance reference point. Then, after obtaining steady-state performance data at different test operating points within the engine's operating envelope, it identifies and calculates the relative relationships of performance correction factors for each component under different operating points and the high-altitude performance reference point. This relationship considers the influence of different engine states and incoming flow conditions (Mach number and Reynolds number) on the performance of each engine component. Simultaneously, the identification and calculation results of the current test data consider the impact of performance degradation. Finally, based on the high-altitude performance reference point, the relative relationships of performance correction factors for each component at different operating points, the current test data, and the steady-state performance model, the airborne performance parameter calibration calculation is completed. This method effectively improves the accuracy of parameter calculations from airborne performance test data calibration to the same high-altitude performance reference point, providing a strong basis for designers to conduct engine gas path performance analysis.

[0097] As a specific implementation method, a calculation method for calibrating engine air performance parameters to the same operating point is provided, which uniformly compares and analyzes the performance parameters of H=11km, Ma=0.8, standard day, N1r=100% (cruise state) and H=8km, Ma=0.6, standard day, N1r=100% (cruise state).

[0098] Specifically, the steps include the following:

[0099] With H = 10km (Pamb = 26.5kPa), Ma = 0.7, and a standard day set as the high-altitude performance reference point, the performance factors AnsynReference of each component of the engine under different operating conditions (N1r = 100%, N1r = 90%, N1r = 80%, etc.) at the high-altitude performance reference point were identified and calculated based on the high-altitude test results at H = 10km and Ma = 0.7. The performance correction factors of each component include the efficiency and converted flow correction of the fan, booster stage, high-pressure compressor, high-pressure turbine, and low-pressure turbine, as well as the nozzle flow coefficient correction, etc.

[0100] Based on the high-altitude test data obtained from the high-altitude test station or flight test station, the component performance correction factors corresponding to different altitudes, Mach numbers and engine states are identified and calculated respectively. The specific values ​​in Table 1 are the schematic calculation results of the performance correction factor of a certain component. The performance correction factors of other components are calculated by formula (2) to form the table data in Tables 1 to 4.

[0101] Table 1. Relative values ​​of performance correction factors for a certain component when engine condition N1r = 100%.

[0102]

[0103]

[0104] Table 2. Relative values ​​of performance correction factors for a certain component when engine condition N1r = 95%.

[0105]

[0106] Table 3. Relative values ​​of performance correction factors for a certain component when engine condition N1r = 90%.

[0107]

[0108] Table 4. Relative values ​​of performance correction factors for a certain component when engine condition N1r = 85%.

[0109]

[0110]

[0111] Under the conditions of H = 11 km (Pamb = 22.7 kPa), Ma = 0.8, and N1r = 100%, the relative relationship of the performance correction factor of a certain component can be calculated as 0.9907 by two-dimensional linear interpolation according to Table 1. Assuming that the performance correction factor of a certain component after the identification and calculation of the test data is 1.0151, the performance correction factor of a certain component at the corresponding reference point is calculated as 1.0246 according to formula (2). Similarly, the calculation results of the performance correction factors of other components can be calculated to form the calculation result of AnsynReference_Test corresponding to the test point.

[0112] With H = 8 km (Pamb = 35.6 kPa) and Ma = 0.6, and N1r = 100%, the relative relationship of the performance correction factor for a certain component can be calculated as 0.9967 using two-dimensional linear interpolation according to Table 1. Assuming that the performance correction factor for a certain component after the identification and calculation of the test data is 1.0081, the performance correction factor for a certain component at the corresponding reference point is calculated as 1.0114 according to formula (2). Similarly, the calculation results of the performance correction factors of other components can be calculated to form the calculation result of AnsynReference_Test corresponding to the test point.

[0113] Then, the performance parameters corresponding to the high-altitude performance reference points at test points H=8km, Ma=0.6 and H=11km, Ma=0.8 are calculated respectively, thereby achieving a unified comparison of performance parameters. The corresponding reference point performance parameter results are calculated according to formula (12).

[0114] The input parameter values ​​for the calculation, where H = 11km and Ma = 0.8, are as follows: Pamb = 26.5kPa, Ma = 0.7, ΔTamb = 0, N1r = 100%, and AnsynReference_Test is the performance correction factor for each component, which includes the interpolation calculation result of 1.0246.

[0115] The input parameter values ​​for the calculation, where H = 8 km and Ma = 0.6, are as follows: Pamb = 26.5 kPa, Ma = 0.7, ΔTamb = 0, N1r = 100%, and AnsynReference_Test is the performance correction factor for each component, which includes the interpolation calculation result of 1.0114.

[0116] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A calculation method for calibrating engine in-flight performance parameters to the same operating condition point, characterized in that, include: Typical operating conditions commonly used by aircraft are selected as high-altitude performance reference points, and specific parameter values ​​for the high-altitude performance reference points are set, including altitude, Mach number, ambient temperature deviation, and engine status. Select and process the steady-state performance data of the engine under different operating conditions at the current test point; Based on the relationship between the performance parameter test results at the current test operating point and the rotation speed, the performance parameter test results at the high-altitude performance reference point under the rotation speed condition are interpolated and calculated. Based on the steady-state performance test results at different heights, Mach numbers and engine states within the engine's working envelope, the performance correction factors for each component corresponding to the test data at each operating point are identified and calculated. Calculate the relative relationship between the performance correction factors of each component corresponding to the test data of different test conditions and high-altitude performance reference points, and form a 3D numerical table of altitude, Mach number and engine speed. Based on the relative relationship of component performance correction factors at different operating points, calculate the component performance correction factors at the high-altitude performance reference point corresponding to the test results at the current operating point. Input the altitude, Mach number, ambient temperature deviation, engine status, and performance correction factors of each component after conversion of the high-altitude performance reference point, and calculate the performance parameter values ​​of the current operating point test results at the high-altitude performance reference point through the steady-state performance model. The calculation method for the relative relationship between the performance correction factors of each component at different operating points and the high-altitude performance reference point is as follows: Steady-state performance was selected within the engine's operating envelope at different altitudes, Mach numbers, and engine states. Based on the test data, the performance correction factors of each component corresponding to different test conditions can be identified and calculated. Based on the test data of the reference working point, the performance correction factors of each component corresponding to the high-altitude performance reference point are identified and calculated. Combined with formula (2), the relative relationship of the performance correction factors of each component at different test working points and high-altitude performance reference points is calculated, and a numerical table of three dimensions of environmental pressure, Mach number and engine status is formed. （2） In formula (2), AnsynCurrent is the performance correction factor of each component identified and calculated based on the test data of the current operating point, AnsynReference is the performance correction factor of each component identified and calculated based on the test data of the reference operating point, and AnsynRelative is the relative ratio of the performance correction factors of each component at the current test point and the high-altitude performance reference point.

2. The calculation method for calibrating engine air performance parameters to the same operating condition point as described in claim 1, characterized in that: Steady-state performance data of operating parameters, control parameters, overall performance parameters, and cross-sectional temperature and pressure parameters are obtained by averaging.

3. The calculation method for calibrating engine air performance parameters to the same operating condition point as described in claim 1, characterized in that, The formula for calculating the test results of performance parameters at the high-altitude performance reference point speed state by interpolation is as follows: （1） In formula (1), Y represents the engine performance parameters, N1r represents the low-pressure rotor conversion speed, the subscript start represents the starting speed of the interpolation calculation, the subscript end represents the ending speed of the interpolation calculation, and the subscript current represents the current interpolation speed.

4. The calculation method for calibrating engine air performance parameters to the same operating condition point as described in claim 1, characterized in that, The calculation method for the performance correction factors of each component is as follows: The specific formula for calculating and analyzing the engine's airflow performance is as follows: （3） In formula (3), h represents the functional relationship between the measurement parameters and the component performance correction factor, which is expressed by the steady-state performance model, Z represents the measurement parameter vector, and X represents the component performance correction factor vector; If the performance of a component changes, δ represents the degree of parameter change. A first-order Taylor series expansion of h(x) at a given operating point yields: （4） The influence parameter matrix H is obtained, and its mathematical expression is: （5） Ignoring the influence of higher-order terms in the parameter matrix H, we obtain: （6） The following was obtained through matrix transformation: （7） The nonlinear equations are solved using the Newton-Raphson algorithm to obtain the calculated values ​​of the performance correction factors for each component that meet the accuracy requirements of the objective function measurement parameters.

5. The calculation method for calibrating engine air performance parameters to the same operating condition point as described in claim 1, characterized in that, The formula for calculating the performance correction factor of each component at the high-altitude performance reference point corresponding to the test results at the current operating point is as follows: （8） （9） In formula (8), N1r represents the converted speed of the low-pressure rotor, Pamb represents the ambient pressure at the current test operating point, Ma represents the Mach number at the current test operating point, and f represents 3D linear interpolation calculation; in formula (9), AnsynCurrent is the performance correction factor of each component identified and calculated based on the test data at the current operating point, AnsynRelative is the relative ratio of the performance correction factors of each component at the current test operating point and the high-altitude performance reference point, and AnsynReference_Test is the performance correction factor of each component at the high-altitude performance reference point corresponding to the test data at the current operating point.

6. The calculation method for calibrating engine air performance parameters to the same operating condition point as described in claim 1, characterized in that, The formula for calculating the performance parameter values ​​at the high-altitude performance reference point based on the current operating condition test results using the steady-state performance model is as follows: （10） In formula (10), Pamb represents the ambient pressure at the high-altitude performance reference point, N1r represents the converted speed of the low-pressure rotor, and Ma represents the Mach number at the high-altitude performance reference point. Tamb represents the ambient temperature deviation of the high-altitude performance reference point, AnsynReference_Test is the performance correction factor of each component at the high-altitude performance reference point corresponding to the test data at the current operating point, and f is the engine steady-state performance model.

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