High-pressure turbine performance uncertainty evaluation method and device and readable storage medium

Abstract

The invention provides a high-pressure turbine performance uncertainty evaluation method and device and a readable storage medium, and relates to the technical field of aero-engine tests. The high-pressure turbine performance uncertainty evaluation method comprises the following steps: acquiring a plurality of direct measurement value data; performing random valuing on the plurality of direct measurement value data according to normal distribution to obtain a plurality of data groups; wherein each data group comprises a plurality of data in one-to-one correspondence with the plurality of direct measurement value data; the multiple data sets are input into a high-pressure turbine performance evaluation mathematical model, and multiple pieces of performance data are obtained through solving of the high-pressure turbine performance evaluation mathematical model; and determining the performance uncertainty according to the multiple pieces of performance data and a preset confidence interval. According to the evaluation method for the performance uncertainty of the high-pressure turbine, the performance uncertainty is obtained through the multiple direct measurement values and the random error analysis method, effective evaluation on the performance uncertainty is achieved, and the evaluation result is more accurate.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine testing, and in particular to a method and device for evaluating the uncertainty of high-pressure turbine performance, and a readable storage medium. Background Art

[0002] Gas turbine engines consist of several main components that change the state of the airflow through a series of thermodynamic cycles and provide thrust or load. The design of modern turbofan engines follows the concept of a unit body, such as Figure 1 As shown, a typical twin-rotor turbofan engine is composed of several main units: a fan unit 11, a low-pressure compressor (LPC) unit 12, a core engine 13, a low-pressure turbine (LPT) unit 14 and an accessory gearbox 15. The core engine 13 is mainly composed of a compressor (HPC), a combustion chamber and a high-pressure turbine (HPT), including the three major components of high temperature, high pressure and high speed in the engine system.

[0003] In order to support the whole engine test, it is necessary to conduct core engine tests to evaluate the core engine performance under typical working conditions of the engine operating envelope, including core engine cycle power, total pressure ratio, total temperature ratio, high-pressure compressor efficiency and converted flow, high-pressure turbine efficiency and converted flow, and the matching of the common working line. In the core engine test, the working environment temperature of the high-pressure compressor is relatively low, and the inlet and outlet are generally arranged with temperature and pressure measurement points; while the working environment temperature of the high-pressure turbine is very high, and the high-pressure turbine inlet temperature cannot be directly measured, and only the outlet temperature can be measured. Therefore, the efficiency of the high-pressure turbine cannot be directly calculated based on the inlet and outlet temperatures, and needs to be estimated based on the core engine power balance and flow balance. The calculation chain is long, and the calculation results will be affected by the errors of each measurement result in the calculation chain. Therefore, it is difficult to directly use the error transfer formula to evaluate the uncertainty. Summary of the invention

[0004] The purpose of the present invention is to provide a method for evaluating the uncertainty of high-pressure turbine performance, which can improve the technical problem of the difficulty of uncertainty evaluation.

[0005] Another object of the present invention is to provide a high-pressure turbine performance uncertainty assessment device that can improve the technical problem of uncertainty assessment difficulties.

[0006] Another object of the present invention is to provide a readable storage medium that can improve the technical problem of difficulty in uncertainty assessment.

[0007] The embodiments of the present invention can be implemented in the following ways:

[0008] A high pressure turbine performance uncertainty assessment method includes acquiring a plurality of direct measurement value data;

[0009] Randomly sampling the multiple direct measurement data according to normal distribution to obtain multiple data groups; wherein each of the data groups includes multiple data corresponding to the multiple direct measurement data one by one;

[0010] Inputting the plurality of data groups into a high-pressure turbine performance evaluation mathematical model respectively, and solving the high-pressure turbine performance evaluation mathematical model to obtain a plurality of performance data;

[0011] A performance uncertainty is determined based on the plurality of performance data and a preset confidence interval.

[0012] Optionally, the types of performance data include high-pressure turbine efficiency and high-pressure turbine converted flow rate.

[0013] Optionally, the types of the multiple directly measured value data include: compressor inlet flow, compressor inlet temperature, compressor outlet temperature, compressor bleed air temperature, compressor bleed air pressure, high-pressure turbine supply air pressure, combustion chamber outlet pressure, high-pressure turbine outlet pressure and fuel flow.

[0014] Optionally, the high-pressure turbine performance uncertainty assessment method further includes:

[0015] Constructing the high-pressure turbine performance evaluation mathematical model according to the high-pressure turbine core machine for which performance uncertainty evaluation is required;

[0016] Wherein, the high-pressure turbine core engine comprises a compressor, a combustion chamber, a high-pressure turbine first-stage guide vane and a blade row, wherein the compressor, the combustion chamber, the high-pressure turbine first-stage guide vane and the blade row are arranged in sequence, the front side of the compressor has a compressor inlet, a compressor outlet is provided between the compressor and the combustion chamber, a high-pressure turbine inlet is provided between the combustion chamber and the high-pressure turbine first-stage guide vane, a high-pressure turbine first-stage guide vane outlet is provided between the high-pressure turbine first-stage guide vane and the blade row, and the rear side of the blade row has a high-pressure turbine outlet;

[0017] The high-pressure turbine core engine also includes a first bleed air path and a second bleed air path. The first bleed air path introduces cooling air from the compressor into the first-stage guide vane of the high-pressure turbine, and the second bleed air path introduces cooling air from the compressor into the blade row.

[0018] Optionally, the performance data includes the high pressure turbine efficiency η hpt ; The formula for constructing the mathematical model for high-pressure turbine performance evaluation includes:

[0019]

[0020] P hpt =P hpc ;

[0021]

[0022] Among them, W 41 is the outlet flow rate of the first-stage guide vane of the high-pressure turbine, T 41 is the outlet temperature of the first-stage guide vane of the high-pressure turbine; P hpc is the power consumed by the compressor; far 41 is the oil-gas ratio at the outlet of the first-stage guide vane of the high-pressure turbine; P4 is the outlet pressure of the combustion chamber; P 44 is the high pressure turbine outlet pressure;

[0023] The high-pressure turbine first-stage guide vane outlet flow rate W 41 Obtained according to the following formula:

[0024] W 41 =W 40 +W6;

[0025] W 40 =W 25 -W5-W6+W f ;

[0026] W5=θ(P5,T5,P 5T );

[0027] W6=θ(P6,T6,P 6T );

[0028] Among them, W 25 is the compressor inlet flow rate; P5 is the air pressure of the first bleed air path; T5 is the temperature of the first bleed air path; P 5T is the air supply side pressure of the first-stage guide vane of the high-pressure turbine; P6 is the air pressure of the second bleed air path; T6 is the temperature of the second bleed air path; P 6T W is the air supply pressure of the blade row; f is the fuel flow rate;

[0029] The oil-gas ratio at the outlet of the first-stage guide vane of the high-pressure turbine is far 41 Obtained according to the following formula:

[0030]

[0031] The high pressure turbine first stage guide vane outlet temperature T 41 Obtained according to the following formula:

[0032] T 41 =T(h 41 , far 41 );

[0033] h 41 =H 41 / W41 ;

[0034]

[0035] T 40 =T(h 40 , far 40 );

[0036]

[0037]

[0038]

[0039] Among them, T 31 is the compressor outlet temperature; far 31 is the oil-gas ratio at the compressor outlet; LHV is the calorific value of the fuel oil; η B is the combustion efficiency; far6 is the oil-gas ratio of the second bleed air path, far6=0;

[0040] The compressor power consumption P hpc Obtained according to the following formula:

[0041]

[0042] W 31 =W 25 -W5-W6;

[0043] Among them, T 31 is the compressor outlet temperature; far 31 is the oil-gas ratio at the compressor outlet, far 31 =0; far5 is the oil-gas ratio of the first air bleed path, far5=0; T 25 is the compressor inlet temperature; far 25 is the oil-gas ratio at the compressor inlet, far 25 =0.

[0044] Optionally, the plurality of directly measured value data include: combustion chamber outlet pressure P4, high pressure turbine outlet pressure P 44 , compressor inlet flow W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure P6 of the second bleed air path, the temperature T6 of the second bleed air path, the air supply side pressure P 6T 、Fuel flow W f , compressor outlet temperature T 31 and compressor inlet temperature T 25 .

[0045] Optionally, the performance data includes a high pressure turbine converted flow rate W 41，corrected ; The formula for constructing the mathematical model for high-pressure turbine performance evaluation includes:

[0046]

[0047] Among them, W 41 is the outlet flow rate of the first-stage guide vane of the high-pressure turbine, T 41 is the outlet temperature of the first-stage guide vane of the high-pressure turbine; P4 is the outlet pressure of the combustion chamber;

[0048] The high-pressure turbine first-stage guide vane outlet flow rate W 41 Obtained according to the following formula:

[0049] W 41 =W 40 +W6;

[0050] W 40 =W 25 -W5-W6+W f ;

[0051] W5=θ(P5,T5,P 5T );

[0052] W6=θ(P6,T6,P 6T );

[0053] Among them, W 25 is the compressor inlet flow rate; P5 is the air pressure of the first bleed air path; T5 is the temperature of the first bleed air path; P 5T is the air supply side pressure of the first-stage guide vane of the high-pressure turbine; P6 is the air pressure of the second bleed air path; T6 is the temperature of the second bleed air path; P 6T W is the air supply pressure of the blade row; f is the fuel flow rate.

[0054] Optionally, the multiple directly measured value data include: combustion chamber outlet pressure P4, compressor inlet flow rate W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure of the second air bleed path P6, the temperature of the second air bleed path T6, the air supply pressure P of the blade row 6T and fuel flow W f .

[0055] Optionally, the step of randomly sampling the multiple direct measurement data according to normal distribution to obtain multiple data groups includes:

[0056] Each direct measurement value is evaluated according to the preset confidence interval of 99.73%, and a random value is obtained within the preset confidence interval; a data randomly obtained from multiple direct measurement values ​​constitutes a data group;

[0057] The step of determining the performance uncertainty according to the plurality of performance data and the preset confidence interval comprises:

[0058] Calculate a standard deviation S based on the plurality of performance data;

[0059] Evaluated according to the preset confidence interval of 99.73%, the uncertainty is ±3S.

[0060] A high-pressure turbine performance uncertainty assessment device comprises an acquisition module, wherein the acquisition module is used to acquire a plurality of directly measured value data;

[0061] A value taking module, the value taking module is used to randomly take values ​​of the multiple direct measurement value data according to normal distribution to form a data group;

[0062] A high-pressure turbine performance evaluation mathematical model, wherein the high-pressure turbine performance evaluation mathematical model is used to obtain performance data by solving the data set;

[0063] A calculation module is used to determine the performance uncertainty based on the multiple performance data and a preset confidence interval.

[0064] A readable storage medium stores a computer program, wherein the computer program is used to be executed by a processor to implement the high-pressure turbine performance uncertainty assessment method as described above.

[0065] The advantageous effects of the high-pressure turbine performance uncertainty assessment method, device and readable storage medium provided by the embodiments of the present invention include:

[0066] An embodiment of the present invention provides a method for evaluating the uncertainty of high-pressure turbine performance, the method comprising obtaining a plurality of direct measurement data; randomly selecting values ​​of the plurality of direct measurement data according to a normal distribution to obtain a plurality of data groups; wherein each data group comprises a plurality of data corresponding to the plurality of direct measurement data; inputting the plurality of data groups into a high-pressure turbine performance evaluation mathematical model respectively, and obtaining a plurality of performance data by solving the high-pressure turbine performance evaluation mathematical model; and determining the performance uncertainty according to the plurality of performance data and a preset confidence interval. The method for evaluating the uncertainty of high-pressure turbine performance obtains the performance uncertainty through a plurality of direct measurement values ​​and a random error analysis method, thereby achieving an effective evaluation of the performance uncertainty, and the evaluation result is more accurate.

[0067] The embodiment of the present invention also provides a high-pressure turbine performance uncertainty assessment device, which includes an acquisition module, the acquisition module is used to acquire multiple direct measurement value data; a value taking module, the value taking module is used to randomly take values ​​of multiple direct measurement value data according to normal distribution to form a data group; a high-pressure turbine performance assessment mathematical model, the high-pressure turbine performance assessment data model is used to solve the data group to obtain performance data; a calculation module, the calculation module is used to determine the performance uncertainty according to multiple performance data and a preset confidence interval. The high-pressure turbine performance uncertainty assessment device can achieve an effective assessment of the high-pressure turbine performance uncertainty, and the assessment result is accurate.

[0068] An embodiment of the present invention also provides a readable storage medium, in which a computer program stored can be executed by a processor to implement the above-mentioned high-pressure turbine performance uncertainty assessment method, thereby also having the beneficial effect of being able to achieve effective assessment of performance uncertainty and making the assessment results more accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0069] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0070] Figure 1 A schematic diagram of the components of a typical twin-rotor turbofan engine in the prior art is shown;

[0071] Figure 2 A step diagram of a method for evaluating uncertainty in high-pressure turbine performance provided according to one aspect of the present invention is shown;

[0072] Figure 3 A diagram showing the operation process of a high-pressure turbine performance evaluation mathematical model in a high-pressure turbine performance uncertainty evaluation method provided according to one aspect of the present invention;

[0073] Figure 4 A flowchart of the method for evaluating uncertainty in performance of a high-pressure turbine according to one aspect of the present invention when step S03 is executed is shown;

[0074] Figure 5 A schematic structural diagram of a typical high-pressure turbine core engine provided according to one aspect of the present invention is shown.

[0075] Reference numerals:

[0076] 1-compressor; 2-combustion chamber; 3-high-pressure turbine first-stage guide vane; 4-blade row; 5-first bleed air path; 6-second bleed air path; 25-compressor inlet; 31-compressor outlet; 40-high-pressure turbine inlet; 41-high-pressure turbine first-stage guide vane outlet; 44-high-pressure turbine outlet; 100-mathematical model for high-pressure turbine performance evaluation. DETAILED DESCRIPTION

[0077] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0078] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0079] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0080] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0081] For an indirect measurement value y, it has the following functional relationship with the direct measurement value:

[0082] y=f(x1,x2…,x i )

[0083] Where y is the indirect measurement value, x1, x2…, x i is a direct measurement value.

[0084] According to the error transfer formula, the relative error of the indirect measurement value can be calculated by the following formula

[0085]

[0086] In the formula, is the error transfer coefficient, Δxi is the absolute error of the direct measurement value, and Δy is the absolute error of the indirect measurement value.

[0087] In the core engine test, the high-pressure turbine efficiency and converted flow are both indirect measurement values, and some of the parameters used to calculate the efficiency and converted flow are also indirect measurement values. The functional relationship between the high-pressure turbine efficiency, converted flow and direct measurement values ​​is very cumbersome and complicated, and it is impossible to solve the partial derivatives of each direct measurement value for the efficiency and converted flow. Therefore, it is not convenient to directly use the error transfer formula to evaluate the uncertainty of the high-pressure turbine efficiency and converted flow.

[0088] For example, the high-pressure turbine efficiency η hpt , high pressure turbine efficiency η hpt The definition is as follows:

[0089]

[0090] Among them, P hpt ——is the output shaft power of the high-pressure turbine;

[0091] W 41 — is the mass flow rate at the outlet of the first-stage guide vane of the high-pressure turbine;

[0092] Cp 41 ——Specific heat at constant pressure at the outlet of the first-stage guide vane of the high-pressure turbine;

[0093] T 41 ——The absolute total temperature at the outlet of the first-stage guide vane of the high-pressure turbine;

[0094] π——High-pressure turbine expansion ratio, the ratio of inlet and outlet total pressure;

[0095] k——Specific heat ratio of the first-stage guide vane outlet of the high-pressure turbine.

[0096] In the above formula, P hpt , W 41 The above problems cannot be directly measured and need to be calculated using the compressor end flow and temperature parameters. The calculation chain is long. If the error transfer formula is used for uncertainty calculation, the calculation process will be very cumbersome and complicated. In order to improve the above problems, the present invention provides a high-pressure turbine performance uncertainty evaluation method, device and readable storage medium.

[0097] Figure 2 The step diagram of the high pressure turbine performance uncertainty evaluation method provided by this embodiment is shown. Figure 2 , this embodiment provides a method for evaluating uncertainty in high-pressure turbine performance, the method comprising the following steps:

[0098] S01: Acquire multiple direct measurement value data.

[0099] The types of the multiple directly measured data required are determined according to the type of performance data for which uncertainty assessment is required. Optionally, in this embodiment, the types of performance data include high-pressure turbine efficiency and high-pressure turbine converted flow. Further, the types of the multiple directly measured data include: compressor inlet flow, compressor inlet temperature, compressor outlet temperature, compressor bleed air temperature, compressor bleed air pressure, high-pressure turbine supply pressure, combustion chamber outlet pressure, high-pressure turbine outlet pressure, and fuel flow.

[0100] S02: Randomly sample values ​​of a plurality of directly measured data according to a normal distribution to obtain a plurality of data groups.

[0101] Each direct measurement data is randomly selected according to the normal distribution, so that a data group can be obtained after multiple direct measurement data are selected. The number of data in the data group is consistent with the number of multiple direct measurement data, and they correspond one to one. Repeat the above random selection process to obtain multiple data groups.

[0102] Optionally, each directly measured value data is evaluated according to a preset confidence interval of 99.73%, and then a random value is taken within the preset confidence interval. It should be noted that the specific range of the preset confidence interval is not limited here, and it can be understood that other confidence interval ranges can also be used in other embodiments.

[0103] Specifically, according to the preset confidence interval evaluation of 99.73%, the true value distribution of each direct measurement data is within the interval of (measured value - measured value * lower deviation percentage, measured value + measured value * upper deviation percentage), and the standard deviation of the normal distribution = upper deviation or lower deviation / 3.

[0104] S03: Inputting the plurality of data groups into the high-pressure turbine performance evaluation data model respectively, and solving the high-pressure turbine performance evaluation data model to obtain a plurality of performance data.

[0105] Figure 3 This is a diagram of the operation process of the high-pressure turbine performance evaluation mathematical model 100 in the high-pressure turbine performance uncertainty evaluation method provided in this embodiment, Figure 4 This is a flow chart of the high-pressure turbine performance uncertainty assessment method provided in this embodiment when executing step S03. Figure 2-Figure 4 In the present embodiment, a data group including the above-mentioned nine types of directly measured value data is input into the high-pressure turbine performance evaluation mathematical model 100, and a performance data can be obtained by solving the high-pressure turbine performance evaluation mathematical model 100. Specifically, since the types of performance data in the present embodiment include high-pressure turbine efficiency and high-pressure turbine converted flow rate, one performance data includes a high-pressure turbine efficiency data eff and a high-pressure turbine converted flow rate data W.

[0106] Accordingly, by inputting a plurality of data groups into the high-pressure turbine performance evaluation mathematical model 100 respectively, a plurality of high-pressure turbine efficiency data eff1 to effN and a plurality of high-pressure turbine converted flow data W1 to WN can be obtained.

[0107] It should be noted that the execution order of S02 and S03 is not limited here. It can be that step S02 is executed first to obtain multiple data groups, and then step S03 is executed, that is, step S02 is executed before executing step S03; or step S02 can be executed first to obtain a data group, and the data group is input into S03, and then step S02 is repeated to obtain a data group, that is, step S02 and step S03 are executed simultaneously.

[0108] Specifically, in the process of repeatedly executing the step of inputting the data set into the high-pressure turbine performance evaluation mathematical model 100 to obtain the performance data, the loop can also be executed by programming using Matlab or Python.

[0109] Furthermore, the high-pressure turbine performance uncertainty assessment method provided in this embodiment also includes the step of constructing a high-pressure turbine performance assessment mathematical model 100, and the high-pressure turbine performance assessment mathematical model 100 is constructed according to the high-pressure turbine core engine for which performance uncertainty assessment is required.

[0110] Figure 5 A typical high pressure turbine core structure diagram is shown. Figure 5 The construction of the high-pressure turbine performance evaluation mathematical model 100 is described by taking the high-pressure turbine core engine structure shown as an example.

[0111] like Figure 5 As shown, the typical high-pressure turbine core engine includes a compressor 1, a combustion chamber 2, a high-pressure turbine first-stage guide vane 3 and a blade row 4. The compressor 1, the combustion chamber 2, the high-pressure turbine first-stage guide vane 3 and the blade row 4 are arranged in sequence, the compressor 1 has a compressor inlet 25 at the front side, a compressor outlet 31 between the compressor 1 and the combustion chamber 2, a high-pressure turbine inlet 40 between the combustion chamber 2 and the high-pressure turbine first-stage guide vane 3, a high-pressure turbine first-stage guide vane outlet 41 between the high-pressure turbine first-stage guide vane 3 and the blade row 4, and a high-pressure turbine outlet 44 at the rear side of the blade row 4. At the same time, the high-pressure turbine core engine also includes a first bleed air path 5 and a second bleed air path 6. The first bleed air path 5 introduces cooling air from the compressor 1 to the high-pressure turbine first-stage guide vane 3, and the second bleed air path 6 introduces cooling air from the compressor 1 to the blade row 4.

[0112] Specifically, since there are two bleed air paths in this embodiment, accordingly, the compressor bleed air pressure includes the pressure of the first bleed air path and the pressure of the second bleed air path, the compressor bleed air temperature includes the temperature of the first bleed air path and the temperature of the second bleed air path, and the high-pressure turbine supply air pressure includes the supply air side pressure of the first-stage guide vane of the high-pressure turbine and the supply air side pressure of the blade row. At the same time, fuel needs to be supplied to the combustion chamber during use, so the fuel flow rate in the direct measurement value data is the amount of fuel supplied to the combustion chamber.

[0113] It can be understood that in other embodiments, if there are more bleed air paths, the number of specific data included in the compressor bleed air pressure, the compressor bleed air temperature and the high-pressure turbine supply pressure also needs to be adjusted accordingly. At the same time, the specific type of direct measurement value data can also be adjusted according to the specific structure of the core engine.

[0114] The specific process of constructing the high-pressure turbine performance evaluation mathematical model 100 includes:

[0115] For the high-pressure turbine efficiency η hpt :

[0116]

[0117] P hpt =P hpc

[0118]

[0119] Among them, W 41 is the outlet flow rate of the first-stage guide vane of the high-pressure turbine, T 41 is the outlet temperature of the first-stage guide vane of the high-pressure turbine; P hpc is the power consumed by the compressor; far 41 is the oil-gas ratio at the outlet of the first-stage guide vane of the high-pressure turbine; P4 is the outlet pressure of the combustion chamber; P 44 is the high pressure turbine outlet pressure.

[0120] Among them, the outlet flow rate of the high-pressure turbine first-stage guide vane is W 41 Obtained according to the following formula:

[0121] W 41 =W 40 +W6;

[0122] W 40 =W 25 -W5-W6+W f ;

[0123] W5=θ(P5,T5,P 5T );

[0124] W6=θ(P6,T6,P6T );

[0125] Among them, W 25 is the compressor inlet flow rate; P5 is the air pressure of the first bleed air path; T5 is the temperature of the first bleed air path; P 5T is the air supply side pressure of the first-stage guide vane of the high-pressure turbine; P6 is the air pressure of the second bleed air path; T6 is the temperature of the second bleed air path; P 6T W is the air supply pressure of the blade row; f is the fuel flow rate. Meanwhile, θ(x1, x2, x3) is the calculation function.

[0126] High pressure turbine first stage guide vane outlet oil-gas ratio far 41 Obtained according to the following formula:

[0127]

[0128] High pressure turbine first stage guide vane outlet temperature T 41 Obtained according to the following formula:

[0129] T 41 =f(h 41 , Tar 41 );

[0130] h 41 =H 41 / W 41 ;

[0131]

[0132] T 40 =f(h 40 , Tar 40 );

[0133]

[0134]

[0135]

[0136] Among them, T 31 is the compressor outlet temperature; far 31 is the oil-gas ratio at the compressor outlet; LHV is the calorific value of the fuel oil; η B is the combustion efficiency; far6 is the oil-gas ratio of the second bleed air path, far6 = 0. At the same time, f(x1, x2) is the function of temperature, specific enthalpy and oil-gas ratio, is the function of specific enthalpy, temperature and oil-gas ratio, h 31 is the specific enthalpy at the compressor outlet, h 40 is the specific enthalpy at the high-pressure turbine inlet, h 41is the specific enthalpy at the first-stage guide vane of the high-pressure turbine.

[0137] Compressor power consumption P hpc Obtained according to the following formula:

[0138]

[0139] W 31 =W 25 -W5-W6;

[0140] Among them, T 31 is the compressor outlet temperature; Tar 31 is the oil-gas ratio at the compressor outlet, far 31 =0; Tar5 is the oil-gas ratio of the first air bleed path, Tar5=0; T 25 is the compressor inlet temperature; far 25 is the oil-gas ratio at the compressor inlet, far 25 =0.

[0141] It should be noted that in the above data, the fuel calorific value LHV and combustion efficiency η B The values ​​are preset according to the fuel type. Combustion chamber outlet pressure P4, high pressure turbine outlet pressure P 44 , compressor inlet flow W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure P6 of the second bleed air path, the temperature T6 of the second bleed air path, the air supply side pressure P 6T , fuel flow W f , compressor outlet temperature T 31 and compressor inlet temperature T 25 is a directly measured value. In other words, if the high-pressure turbine performance evaluation mathematical model 100 is only used to obtain the high-pressure turbine efficiency η hpt , then the multiple direct measurement data in the high-pressure turbine performance uncertainty assessment method can also be set to include the combustion chamber outlet pressure P4, the high-pressure turbine outlet pressure P 44 , compressor inlet flow W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure P6 of the second bleed air path, the temperature T6 of the second bleed air path, the air supply side pressure P 6T , fuel flow W f , compressor outlet temperature T 31 and compressor inlet temperature T 25 .

[0142] For the high pressure turbine, the converted flow rate W41，corrected :

[0143]

[0144] Among them, W 41 is the outlet flow rate of the first-stage guide vane of the high-pressure turbine, T 41 is the outlet temperature of the first-stage guide vane of the high-pressure turbine; P4 is the outlet pressure of the combustion chamber.

[0145] According to the above high pressure turbine efficiency η hpt The calculation formula for W 41 From the calculation, it can be known that for the high-pressure turbine conversion flow W 41，corrected The direct measurement values ​​include the combustion chamber outlet pressure P4, the compressor inlet flow rate W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure of the second air bleed path P6, the temperature of the second air bleed path T6, the air supply pressure P of the blade row 6T and fuel flow W f In other words, if the high-pressure turbine performance evaluation mathematical model 100 is only used to obtain the high-pressure turbine converted flow rate W 41，corrected , then the multiple direct measurement data in the high-pressure turbine performance uncertainty assessment method can also be set to include the combustion chamber outlet pressure P4, the compressor inlet flow rate W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure of the second air bleed path P6, the temperature of the second air bleed path T6, the air supply pressure P of the blade row 6T and fuel flow W f .

[0146] S04: Determine uncertainty based on multiple performance data and preset confidence intervals.

[0147] S41: Calculate a standard deviation S based on a plurality of performance data.

[0148] Count multiple high-pressure turbine efficiency results, and solve the high-pressure turbine efficiency standard deviation S based on the multiple high-pressure turbine efficiency data eff . Count multiple high-pressure turbine converted flow results, and solve the high-pressure turbine converted flow standard deviation S according to the multiple high-pressure turbine converted flow data w41 .

[0149] S42: Determine performance uncertainty according to the 3 sigma principle.

[0150] The uncertainty is ±3S, as assessed with a pre-set confidence interval of 99.73%.

[0151] Specifically, the uncertainty of the high-pressure turbine efficiency is ±3S eff ; The uncertainty of the high-pressure turbine converted flow is ±3S w41 It should be noted that, in this embodiment, since the performance uncertainty is evaluated according to the 3 sigma principle, the preset confidence interval is 99.73%. It is understandable that in some other embodiments, the specific range of the preset confidence interval can also be set according to requirements.

[0152] The embodiment of the present invention also provides a high-pressure turbine performance uncertainty assessment device, which includes an acquisition module, the acquisition module is used to acquire multiple direct measurement value data; a value taking module, the value taking module is used to randomly take values ​​of the multiple direct measurement value data according to the normal distribution to form a data group; a high-pressure turbine performance assessment mathematical model 100, the high-pressure turbine performance assessment data model is used to obtain performance data according to the data group; a calculation module, the calculation module is used to determine the performance uncertainty according to the multiple performance data and the preset confidence interval. When in use, the value taking module is used to take values ​​multiple times to obtain multiple data groups, and the high-pressure turbine performance assessment mathematical model 100 is solved multiple times according to the multiple data groups to obtain multiple performance data.

[0153] The high-pressure turbine performance uncertainty assessment method and the high-pressure turbine performance uncertainty assessment device provided by the embodiments of the present invention can obtain performance uncertainty by inputting multiple direct measurement values, thereby solving the problem of assessing the uncertainty of high-pressure turbine efficiency and high-pressure turbine converted flow rate in high-pressure turbine core engine tests, and can support core test performance parameter matching with high assessment accuracy.

[0154] The embodiment of the present invention also provides a readable storage medium. Based on such an understanding, the present invention implements all or part of the processes in the above embodiment method, and can also be written by instructing related hardware through a computer program. The computer program exists in a readable storage medium. When the computer program is executed by a processor, the steps in the above high-pressure turbine performance uncertainty assessment method can be implemented. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer readable medium may include: any entity or device that can carry computer program code, recording medium, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium. It should be noted that the content contained in the computer readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the computer readable medium may not include electric carrier signal and telecommunication signal.

[0155] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A method for evaluating uncertainty in high-pressure turbine performance, characterized in that: The high-pressure turbine performance uncertainty assessment method comprises: Acquire multiple direct measurement data; Randomly sampling the multiple direct measurement data according to normal distribution to obtain multiple data groups; wherein each of the data groups includes multiple data corresponding to the multiple direct measurement data one by one; Inputting the plurality of data groups into a high-pressure turbine performance evaluation mathematical model respectively, and solving the high-pressure turbine performance evaluation mathematical model to obtain a plurality of performance data; A performance uncertainty is determined based on the plurality of performance data and a preset confidence interval.

2. The high-pressure turbine performance uncertainty assessment method according to claim 1, characterized in that: The types of performance data include high-pressure turbine efficiency and high-pressure turbine converted flow rate.

3. The high-pressure turbine performance uncertainty assessment method according to claim 2, characterized in that: The types of the multiple directly measured value data include: compressor inlet flow, compressor inlet temperature, compressor outlet temperature, compressor bleed air temperature, compressor bleed air pressure, high-pressure turbine supply air pressure, combustion chamber outlet pressure, high-pressure turbine outlet pressure and fuel flow.

4. The high-pressure turbine performance uncertainty assessment method according to claim 1, characterized in that: The high-pressure turbine performance uncertainty assessment method further includes: Constructing the high-pressure turbine performance evaluation mathematical model according to the high-pressure turbine core machine for which performance uncertainty evaluation is required; Wherein, the high-pressure turbine core engine comprises a compressor, a combustion chamber, a high-pressure turbine first-stage guide vane and a blade row, wherein the compressor, the combustion chamber, the high-pressure turbine first-stage guide vane and the blade row are arranged in sequence, the front side of the compressor has a compressor inlet, a compressor outlet is provided between the compressor and the combustion chamber, a high-pressure turbine inlet is provided between the combustion chamber and the high-pressure turbine first-stage guide vane, a high-pressure turbine first-stage guide vane outlet is provided between the high-pressure turbine first-stage guide vane and the blade row, and the rear side of the blade row has a high-pressure turbine outlet; The high-pressure turbine core engine also includes a first bleed air path and a second bleed air path. The first bleed air path introduces cooling air from the compressor into the first-stage guide vane of the high-pressure turbine, and the second bleed air path introduces cooling air from the compressor into the blade row.

5. The high-pressure turbine performance uncertainty assessment method according to claim 4, characterized in that: The performance data include the high pressure turbine efficiency η hpt ; The formula for constructing the mathematical model for evaluating the performance of the high-pressure turbine includes: P hpt =P hpc ; Among them, W 41 is the outlet flow rate of the first-stage guide vane of the high-pressure turbine, T 41 is the outlet temperature of the first-stage guide vane of the high-pressure turbine; P hpc is the power consumed by the compressor; far 41 is the oil-gas ratio at the outlet of the first-stage guide vane of the high-pressure turbine; P4 is the outlet pressure of the combustion chamber; P 44 is the high pressure turbine outlet pressure; The high-pressure turbine first-stage guide vane outlet flow rate W 41 Obtained according to the following formula: <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 41 <h2 style=";text-align:left;direction:ltr"> =W<h2 style=";text-align:left;direction:ltr"> 40 <h2 style=";text-align:left;direction:ltr"> +W6; <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 40 <h2 style=";text-align:left;direction:ltr"> =W<h2 style=";text-align:left;direction:ltr"> 25 <h2 style=";text-align:left;direction:ltr"> -W5-W6+W<h2 style=";text-align:left;direction:ltr"> f <h2 style=";text-align:left;direction:ltr"> ; W5=θ(P5,T5,P 5T ); <h2 style=";text-align:left;direction:ltr">W6 = θ(P6,T6,P<h2 style=";text-align:left;direction:ltr"> 6T <h2 style=";text-align:left;direction:ltr"> ); Among them, W 25 is the compressor inlet flow rate; P5 is the air pressure of the first bleed air path; T5 is the temperature of the first bleed air path; P 5T is the air supply side pressure of the first-stage guide vane of the high-pressure turbine; P6 is the air pressure of the second bleed air path; T6 is the temperature of the second bleed air path; P 6T W is the air supply pressure of the blade row; f is the fuel flow rate; The oil-gas ratio at the outlet of the first-stage guide vane of the high-pressure turbine is far 41 Obtained according to the following formula: The high pressure turbine first stage guide vane outlet temperature T 41 Obtained according to the following formula: T 41 =f(h 41 ,far 41 ); h 41 =H 41 / W 41 ; T 40 =f(h 40 ,far 40 ); Among them, T 31 is the compressor outlet temperature; far 31 is the oil-gas ratio at the compressor outlet; LHV is the calorific value of the fuel oil; η B is the combustion efficiency; far6 is the oil-gas ratio of the second bleed air path, far6=0; The compressor power consumption P hpc Obtained according to the following formula: <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 31 <h2 style=";text-align:left;direction:ltr"> =W<h2 style=";text-align:left;direction:ltr"> 25 <h2 style=";text-align:left;direction:ltr"> -W5-W6; Among them, T 31 is the compressor outlet temperature; far 31 is the oil-gas ratio at the compressor outlet, far 31 =0; far5 is the oil-gas ratio of the first air bleed path, far5=0; T 25 is the compressor inlet temperature; far 25 is the oil-gas ratio at the compressor inlet, far 25 =0.

6. The high-pressure turbine performance uncertainty assessment method according to claim 5, characterized in that: The multiple directly measured value data include: combustion chamber outlet pressure P4, high pressure turbine outlet pressure P 44 , compressor inlet flow W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure P6 of the second bleed air path, the temperature T6 of the second bleed air path, the air supply side pressure P 6T 、Fuel flow W f , compressor outlet temperature T 31 and compressor inlet temperature T 25 .

7. The high-pressure turbine performance uncertainty assessment method according to claim 4, characterized in that: The performance data includes the high pressure turbine converted flow rate W 41,corrected ; The formula for constructing the mathematical model for evaluating the performance of the high-pressure turbine includes: Among them, W 41 is the outlet flow rate of the first-stage guide vane of the high-pressure turbine, T 41 is the outlet temperature of the first-stage guide vane of the high-pressure turbine; P4 is the outlet pressure of the combustion chamber; The high-pressure turbine first-stage guide vane outlet flow rate W 41 Obtained according to the following formula: <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 41 <h2 style=";text-align:left;direction:ltr"> =W<h2 style=";text-align:left;direction:ltr"> 40 <h2 style=";text-align:left;direction:ltr"> +W6; <h2 style=";text-align:left;direction:ltr">W<h2 style=";text-align:left;direction:ltr"> 40 <h2 style=";text-align:left;direction:ltr"> =W<h2 style=";text-align:left;direction:ltr"> 25 <h2 style=";text-align:left;direction:ltr"> -W5-W6+W<h2 style=";text-align:left;direction:ltr"> f <h2 style=";text-align:left;direction:ltr"> ; W5=θ(P5,T5,P 5T ); <h2 style=";text-align:left;direction:ltr">W6 = θ(P6,T6,P<h2 style=";text-align:left;direction:ltr"> 6T <h2 style=";text-align:left;direction:ltr"> ); Among them, W 25 is the compressor inlet flow rate; P5 is the air pressure of the first bleed air path; T5 is the temperature of the first bleed air path; P 5T is the air supply side pressure of the first-stage guide vane of the high-pressure turbine; P6 is the air pressure of the second bleed air path; T6 is the temperature of the second bleed air path; P 6T W is the air supply pressure of the blade row; f is the fuel flow rate.

8. The high-pressure turbine performance uncertainty assessment method according to claim 7, characterized in that: The multiple directly measured data include: combustion chamber outlet pressure P4, compressor inlet flow rate W 25 , the air pressure P5 of the first bleed air path, the temperature T5 of the first bleed air path, the air supply side pressure P of the first stage guide vane of the high pressure turbine 5T , the air pressure of the second air bleed path P6, the temperature of the second air bleed path T6, the air supply pressure P of the blade row 6T and fuel flow W f .

9. The high-pressure turbine performance uncertainty assessment method according to claim 1, characterized in that: The step of randomly selecting values ​​of the plurality of direct measurement data according to normal distribution to obtain a plurality of data groups comprises: Each direct measurement value is evaluated according to the preset confidence interval of 99.73%, and a random value is obtained within the preset confidence interval; a data randomly obtained from multiple direct measurement values ​​constitutes a data group; The step of determining the performance uncertainty according to the plurality of performance data and the preset confidence interval comprises: Calculate a standard deviation S based on the plurality of performance data; Evaluated according to the preset confidence interval of 99.73%, the uncertainty is ±3S.

10. A high-pressure turbine performance uncertainty assessment device, characterized in that: The high-pressure turbine performance uncertainty assessment device comprises: An acquisition module, the acquisition module is used to acquire a plurality of direct measurement value data; A value taking module, the value taking module is used to randomly take values ​​of the multiple direct measurement value data according to normal distribution to form a data group; A high-pressure turbine performance evaluation mathematical model, wherein the high-pressure turbine performance evaluation mathematical model is used to obtain performance data by solving the data set; A calculation module is used to determine the performance uncertainty based on the multiple performance data and a preset confidence interval.

11. A readable storage medium, characterized in that: The readable storage medium stores a computer program, which is used to be executed by a processor to implement the high-pressure turbine performance uncertainty assessment method as described in any one of claims 1-9.

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