A method and device for calculating and analyzing the operating characteristics of an aeroengine

Abstract

The present application discloses a method and device for calculating and analyzing the operating characteristics of an aeroengine, belonging to the technical field of aeroengines. According to the throttle characteristics, altitude-speed characteristics, and climate characteristic data of the engine, all engine input parameters involved are integrated, including input parameters such as throttle lever angle, aircraft flight altitude and speed, and atmospheric temperature. A full-parameter operating characteristic model is constructed to fit and calculate the output parameters of the aeroengine, breaking through the input and output variable limitations of a single operating characteristic data table, realizing the analysis and calculation of the output parameters during the operation of the engine within the entire aircraft flight envelope, and intuitively presenting the operating characteristics of the aeroengine. It can provide the operating characteristic data of the engine for flight simulator design or flight simulation calculation, and can also provide method and data support for the aviation theory and flight practice training of flight crew or flight mission planning.

Description

Technical Field

[0001] The present application relates to a method and device for calculating and analyzing the operating characteristics of an aeroengine, and belongs to the technical field of aeroengines. Background Art

[0002] During the operation of an aeroengine, it needs to operate under different working conditions, which include external atmospheric conditions (atmospheric pressure, atmospheric temperature, atmospheric humidity), flight conditions (flight speed, altitude), and the operating state of the engine, etc. When these working conditions change, the performance parameters of the engine (thrust, fuel flow rate, rotor speed, exhaust temperature, etc.) will all change accordingly. Generally, the law of the change of engine performance parameters with working conditions is called the operating characteristics of an aeroengine. The purpose of studying the operating characteristics of an aeroengine is to master the change law of the main performance parameters of the engine, determine the flight performance of the aircraft and the most favorable flight state, so as to give full play to the performance of the aircraft. It can also be used to compare the performance of various engines or the same type of engines, and provide decision-making support for flight mission planning.

[0003] The mathematical model of aeroengine characteristics is a mathematical description of the engine working process, that is, it approximately reflects the real engine state through mathematical formulas, charts, etc., and is the mathematical relationship between engine performance parameters and working conditions. Therefore, the mathematical model of aeroengine characteristics is the basis for analyzing the operating characteristics of an aeroengine. An aeroengine is a complex aerodynamic and thermal system, and its internal working mechanism is quite complex. How to describe the engine by mathematical methods, the establishment of the characteristic mathematical model and the simulation research of the overall performance are important contents of the numerical simulation research on the calculation of the operating characteristics of an aeroengine.

[0004] The existing methods for establishing the mathematical model of characteristics include the experimental method and the analytical method. The experimental method obtains the engine characteristics by processing the engine test data, thereby obtaining the engine model. However, the established engine model is a combination of linear differential equations and algebraic equations with piecewise linear coefficients in mathematics. Since the model is not physical, when the characteristics of any component change, in fact, the entire set of coefficients of the model is required to be changed. Due to this method relying on a large amount of test data, the cost is very high, so it is only applicable to the modeling of existing engines. The analytical method uses the identification method, regarding the engine as a black box, ignoring its specific physical meaning, and deriving or fitting the input-output relationship according to the test input-output data. Although this method can consider the influence of various working conditions on the engine characteristics, and no matter which engine component's characteristics change, as long as the model equation describing the component is changed, the analytical method requires a detailed understanding of the physical process inside the engine and can be described by mathematical methods. For new equipment and new models, especially engines introduced from abroad, since there is no component-level working characteristic data, it is difficult to establish the engine working characteristic model of the corresponding model through the analytical method. In addition, when using the analytical method, the working characteristics of the components are obtained through engine component tests, a non-linear equation set is established and solved to determine the common working point of the components, and then the overall engine performance is calculated. Establishing the engine working characteristic model is a currently widely used modeling method. However, since the working characteristic data of aero-engines mainly include throttle characteristics, altitude-speed characteristics, and climate characteristic data sheets, each working characteristic data sheet can only consider the influence of some input parameters. For example, the throttle characteristic data sheet mainly shows the relationship between the engine output parameter values and the throttle lever angle or the engine rotor speed. Therefore, this method can only calculate the engine output parameters under specific conditions such as flight speed, altitude, and external environmental temperature. This makes it difficult to calculate the output parameters of the engine working process within the entire flight envelope of the aircraft directly based on the throttle characteristics, altitude-speed characteristics, and climate characteristic data sheets. Summary of the Invention

[0005] The purpose of this application is to provide a method and device for calculating and analyzing the working characteristics of aero-engines, which can perform fitting calculations on the output parameters of aero-engines based on input parameters such as throttle lever angle, aircraft flight altitude and speed, and atmospheric temperature, and realize the analysis and calculation of the engine working parameters within the entire flight envelope of the aircraft.

[0006] To achieve the above purpose, the first aspect of this application provides a method for calculating and analyzing the working characteristics of aero-engines, including:

[0007] Establish an angular relationship model between the engine state and the throttle lever angle;

[0008] According to the above angle relationship model and different engine characteristic diagrams, corresponding input-output relationship models are established respectively. Among them, the above engine characteristic diagrams include a throttle characteristic diagram, an altitude-speed characteristic diagram, and a climate characteristic diagram. Each of the above input-output relationship models represents the functional relationship between input parameters and output parameters of an aeroengine under the conditions of the corresponding engine characteristic diagram;

[0009] A full-parameter relationship model is established according to each of the above input-output relationship models;

[0010] The above full-parameter relationship model is corrected and calculated to obtain a full-parameter working characteristic model, which is used for fitting calculation of the output parameters of the aeroengine.

[0011] In one implementation manner, the above establishment of the relationship model between the engine state and the throttle lever angle includes:

[0012] According to the engine data and the corresponding relationship between the engine state and the throttle lever angle, using the exponential function fitting and the method of minimizing the sum of squared fitting errors, the angle relationship model between the engine state and the throttle lever angle is established as:

[0013] Condition=f1(α)

[0014] where Condition is the engine state and α is the throttle lever angle.

[0015] In one implementation manner, the above establishment of the corresponding input-output relationship models according to the above angle relationship model and different engine characteristic diagrams includes:

[0016] A first input-output relationship model with the rotor speed as the influencing factor is established according to the above throttle characteristic diagram;

[0017] A second input-output relationship model with the altitude speed as the influencing factor is established according to the above angle relationship model and the above altitude-speed characteristic diagram;

[0018] A third input-output relationship model with the atmospheric temperature as the influencing factor is established according to the above angle relationship model and the above climate characteristic diagram.

[0019] In one implementation manner, the above establishment of the first input-output relationship model with the rotor speed as the influencing factor according to the above throttle characteristic diagram includes:

[0020] According to the throttle characteristic diagram of the aeroengine under the international standard atmospheric conditions, by means of numerical fitting interpolation, the first input-output relationship model between the input parameters (n1, H, V0, T0) and the engine output parameters (F, W g , n2, T4) is:

[0021] [F,W g, n2, T4] = f2(n1, H, V0, T0)

[0022] Among them, n1 is the low-pressure rotor speed, H is the flight altitude of the aircraft, V0 specifically refers to the aircraft flight speed being 0, T0 specifically refers to the atmospheric temperature being 15 degrees Celsius, F is the thrust, W g is the fuel flow rate, n2 is the high-pressure rotor speed, and T4 is the required output temperature of the engine.

[0023] In one implementation, the above-mentioned second input-output relationship model established based on the above angle relationship model and the above altitude-speed characteristic diagram with altitude and speed as influencing factors includes:

[0024] According to the altitude-speed characteristic diagram of the aeroengine under international standard atmospheric conditions, combined with the above angle relationship model, by means of multi-dimensional numerical fitting and interpolation, the input parameters (Condition, H, V, T0) and the engine output parameters (F, W g , n1, n2, T4) of the second input-output relationship model are:

[0025] [F, W g , n1, n2, T4] = f3(α, H, V, T0)

[0026] Among them, V is the flight speed of the aircraft.

[0027] In one implementation, the above-mentioned third input-output relationship model established based on the above angle relationship model and the above climate characteristic diagram with atmospheric temperature as an influencing factor includes:

[0028] According to the engine climate characteristic diagram under the condition that the aircraft flight speed is 0, combined with the above angle relationship model, by means of multi-dimensional numerical fitting and interpolation, the input parameters (Condition, H, V0, T) and the engine output parameters (F, W g , n1, n2, T4) of the third input-output relationship model are:

[0029] [F, W g , n1, n2, T4] = f4(α, H, V0, T)

[0030] Among them, T is the atmospheric temperature.

[0031] In one implementation, the above-mentioned full-parameter relationship model established based on each of the above input-output relationship models includes:

[0032] According to the above engine data, under the condition that the aeroengine is under international standard atmospheric conditions and the aircraft flight speed is 0, by means of exponential function fitting and the method of minimizing the sum of squared fitting errors, the relationship between the low-pressure rotor speed n1 and the throttle lever angle α and the aircraft flight altitude H is:

[0033] n1 = f5(α, H, V0, T0)

[0034] Combining the above second input-output relationship model and the above third input-output relationship model, the relationship between the low-pressure rotor speed n1 and the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T is obtained. That is, the above full-parameter relationship model is:

[0035]

[0036] In one implementation, the above-mentioned correction calculation of the above full-parameter relationship model to obtain the full-parameter working characteristic model includes:

[0037] Determine the importance ranking of the influence degree of each input parameter on the engine output parameter according to the above input-output relationship models. Among them, the above importance ranking is the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T in sequence;

[0038] Based on the above importance ranking, substitute the above full-parameter relationship model into the above first input-output relationship model to obtain:

[0039] [F, W g , n1, n2, T4] = f6(α, H, V0, T0).

[0040] Combine and correct the above second input-output relationship model to obtain:

[0041]

[0042] Combine and correct the above third input-output relationship model to obtain the above full-parameter working characteristic model as:

[0043]

[0044] The second aspect of the present application provides an aero-engine working characteristic calculation and analysis device, including: a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the steps in the above first aspect or any implementation manner of the above first aspect are implemented.

[0045] The third aspect of the present application provides a computer-readable storage medium. The computer-readable storage medium stores a computer program, and is characterized in that when the computer program is executed by a processor, the steps in the above first aspect or any implementation manner of the above first aspect are implemented.

[0046] As can be seen from the above, the present application provides a method and device for calculating and analyzing the operating characteristics of an aeroengine. By simply integrating all the engine input parameters involved according to the throttle characteristics, altitude-speed characteristics, and climate characteristics data of the engine, including input parameters such as throttle lever angle, aircraft flight altitude and speed, and atmospheric temperature, a full-parameter operating characteristic model can be constructed and the fitting calculation of the output parameters of the aeroengine can be realized. This overcomes the disadvantages of high cost in the experimental method and difficult modeling in the analytical method, breaks through the input-output variable limitations of a single operating characteristic data table, realizes the analysis and calculation of the output parameters during the operation of the engine within the entire aircraft flight envelope, and intuitively presents the operating characteristics of the aeroengine. Compared with the existing method of obtaining the output parameters of the engine in a specific state through the experimental method, a large amount of experimental costs and labor costs are saved. It can provide the operating characteristic data of the engine for the design of flight simulators or flight simulation calculations, and can also provide method and data support for the aviation theory and flight practice training of flight crew or flight mission planning. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for use in the embodiments or the description of the prior art. Obviously, the following drawings are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0048] Figure 1 It is a schematic flowchart of a method for calculating and analyzing the operating characteristics of an aeroengine provided by an embodiment of the present application;

[0049] Figure 2 It is a calculation flowchart of a full-parameter operating characteristic model provided by an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0050] In the following description, specific details such as specific system structures and technologies are presented for the purpose of illustration rather than limitation, so as to thoroughly understand the embodiments of the present application. However, those skilled in the art should clearly understand that the present application can also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid unnecessary details from interfering with the description of the present application.

[0051] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, wholes, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or their combinations.

[0052] It should also be understood that the terms used in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application. As used in the specification of this application and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include the plural forms.

[0053] The following will clearly and completely describe the technical solutions in the embodiments of this application with reference to the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in this application without creative efforts shall fall within the scope of protection of this application.

[0054] Many specific details are set forth in the following description to facilitate a thorough understanding of this application, but this application may also be implemented in other ways different from those described herein. Those skilled in the art may make similar extensions without departing from the connotation of this application. Therefore, this application is not limited by the specific embodiments disclosed below.

[0055] Establishing a mathematical calculation model for aero-engine performance calculation is the focus of studying its working characteristics. Based on the understanding of the internal working conditions of the engine, the differences in the description methods and the complexity of the main component characteristics, the research on the aero-engine characteristic mathematical model can be divided into three levels: The first level is that the internal thermal process of the engine is unknown, and the engine is regarded as a black box, and various fitting relationships or empirical relationships are used to describe the performance of the engine. Many engine manufacturers provide throttle characteristics, altitude-speed characteristics, and climate characteristics to users with this model. This kind of aero-engine characteristic mathematical model obtained through identification methods is often used in the simulation research of engine control systems; The second level is that each component of the engine is a black box, and component characteristics are given through component tests. A non-linear equation set is established and solved to determine the common working point and complete the overall engine performance calculation. This is a widely used aero-engine characteristic mathematical model, and its core is the establishment and solution of the component characteristics of the engine and the equation set. In fact, it is still a performance calculation based on tests; The third level is to describe the details of the internal working medium flow of the engine with the help of fluid dynamics technology, establish a virtual simulation engine, and there is no black box model in the entire flow path of the engine. Due to the enormity and complexity of this work, the aero-engine characteristic mathematical model at this level is still in development, and there is no mature such model yet.

[0056] The method proposed in the embodiments of this application is based on the engine operating characteristic diagram. According to the degree of influence of relevant input parameters on the engine output parameters, the multi-dimensional numerical engineering fitting method is used based on the black box theory to iteratively correct the engine output parameters in sequence, breaking through the input and output variable limitations of a single operating characteristic data table, and realizing the calculation of the engine operating process output parameters within the entire aircraft flight envelope. Among them, the main factors affecting the engine output data in the engine operating characteristic diagram include the engine operating state, flight altitude and speed, and atmospheric temperature. To construct an engine operating characteristic model with the throttle lever angle, flight altitude and speed, and atmospheric temperature as input parameters, it is first necessary to establish the relationship between the engine state and the throttle lever angle, and then establish input-output relationship models mainly with the rotor speed, altitude and speed, and atmospheric temperature as influencing factors according to the throttle characteristic, altitude-speed characteristic, and climate characteristic diagrams respectively. Finally, by synthesizing the three input-output relationship models and introducing four variables, namely the throttle lever angle, flight altitude and speed, and atmospheric temperature, for correction calculation, the final full-parameter operating characteristic model can be obtained.

[0057] Embodiment 1

[0058] The embodiments of this application provide a method for calculating and analyzing the operating characteristics of an aeroengine, as Figure 1 and 2 shown. Specifically, this method includes:

[0059] Step 11: Establish an angular relationship model between the engine state and the throttle lever angle;

[0060] Further, the above-mentioned establishment of the relationship model between the engine state and the throttle lever angle includes:

[0061] According to the engine data and the corresponding relationship between the engine state and the throttle lever angle, using the exponential function fitting and the method of minimizing the sum of squared fitting errors, establish the angular relationship model between the engine state and the throttle lever angle as:

[0062] Condition = f1(α)

[0063] where Condition is the engine state and α is the throttle lever angle.

[0064] Optionally, the above-mentioned engine state includes multiple states such as the maximum state, design state, and idle state. The above-mentioned method of using exponential function fitting and minimizing the sum of squared fitting errors can be implemented by using the Power function in the cftool toolbox of Matlab software and taking the parameters with the minimum SSE.

[0065] Optionally, the numerical interpolation methods involved in the embodiments of the present application can all adopt the ScatteredInterpolant scattered point interpolation function of Matlab software, and the interpolation method is "natural". Alternatively, it can also be implemented through other functions or methods, which are not limited herein.

[0066] Step 12: Establish corresponding input-output relationship models according to the above angle relationship model and different engine characteristic diagrams, where the above engine characteristic diagrams include a throttle characteristic diagram, an altitude-speed characteristic diagram, and a climate characteristic diagram, and each of the above input-output relationship models respectively represents the functional relationship between the input parameters and the output parameters of the aero-engine under the conditions of the corresponding engine characteristic diagram;

[0067] Specifically, the above throttle characteristic diagram, altitude-speed characteristic diagram, and climate characteristic diagram can respectively provide throttle characteristic data, altitude-speed characteristic data, and climate characteristic data.

[0068] Further, the establishment of the corresponding input-output relationship models according to the above angle relationship model and different engine characteristic diagrams includes:

[0069] Establish a first input-output relationship model with the rotor speed as the influencing factor according to the above throttle characteristic diagram;

[0070] Establish a second input-output relationship model with the altitude-speed as the influencing factor according to the above angle relationship model and the above altitude-speed characteristic diagram;

[0071] Establish a third input-output relationship model with the atmospheric temperature as the influencing factor according to the above angle relationship model and the above climate characteristic diagram.

[0072] Further, the establishment of the first input-output relationship model with the rotor speed as the influencing factor according to the above throttle characteristic diagram includes:

[0073] According to the throttle characteristic diagram of the aero-engine under the conditions of the international standard atmosphere, establish a first input-output relationship model between the input parameters (n1, H, V0, T0) and the engine output parameters (F, W g 、n2、T4) through the method of numerical fitting interpolation as:

[0074] [F,W g ,n2,T4] = f2(n1, H, V0, T0)

[0075] where n1 is the low-pressure rotor speed, H is the flight altitude of the aircraft, V0 specifically refers to the aircraft flight speed of 0, T0 specifically refers to the atmospheric temperature of 15 degrees Celsius (i.e., the atmospheric temperature under the conditions of the international standard atmosphere), F is the thrust, W gV0 is the fuel flow rate, n2 is the high-pressure rotor speed, and T4 is the required output temperature of the engine. Optionally, the above V0 and T0 are constants, and can also be adjusted to other values as needed in actual applications; the above output temperature T4 can refer to the combustion chamber temperature, the temperature after the turbine, and / or the exhaust gas temperature, etc. according to different types of engines in actual applications. The method of numerical fitting and interpolation of the above values can be implemented by using the Interp3 function of Matlab software with the default parameter settings.

[0076] It should be noted that since the input parameters of the constructed full-parameter working characteristic model are the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T, and the input parameters of the above first input-output relationship model include the low-pressure rotor speed n1, a full-parameter relationship model of n1 with α, H, V, and T needs to be established subsequently.

[0077] Further, the establishment of the second input-output relationship model with altitude and speed as influencing factors based on the above angle relationship model and the above altitude-speed characteristic diagram includes:

[0078] According to the altitude-speed characteristic diagram of the aero-engine under international standard atmospheric conditions, a functional relationship between the input parameters (Condition, H, V, T0) and the engine output parameters (F, W g , n1, n2, T4) is established through the method of multi-dimensional numerical fitting and interpolation as:

[0079] [F, W g , n1, n2, T4] = f3(Condition, H, V, T0)

[0080] Combined with the above angle relationship model, the above second input-output relationship model is obtained as:

[0081] [F, W g , n1, n2, T4] = f3(α, H, V, T0)

[0082] Among them, V is the aircraft flight speed, and this aircraft flight speed is a variable, which can be the real-time flight speed of the aircraft or a preset flight speed. Optionally, the above multi-dimensional numerical fitting and interpolation can be implemented by using the Interp3 function of Matlab software with the default parameter settings.

[0083] Further, the establishment of the third input-output relationship model with atmospheric temperature as an influencing factor based on the above angle relationship model and the above climate characteristic diagram includes:

[0084] According to the engine climate characteristic diagram under the condition that the aircraft flight speed is 0 (i.e., V0 = 0), a functional relationship between the input parameters (Condition, H, V0, T) and the engine output parameters (F, Wg , n1, n2, T4) is a functional relationship as follows:

[0085] [F, W g , n1, n2, T4] = f4(Condition, H, V0, T)

[0086] Combining the above angular relationship model, the above third input-output relationship model is obtained as follows:

[0087] [F, W g , n1, n2, T4] = f4(α, H, V0, T)

[0088] Where T is the atmospheric temperature, and this atmospheric temperature is a variable. Optionally, the above multi-dimensional numerical fitting and interpolation can be implemented by using the Interp3 function of Matlab software with default parameter settings.

[0089] Step 13: Establish a full-parameter relationship model according to each of the above input-output relationship models;

[0090] Furthermore, the establishment of the full-parameter relationship model according to each of the above input-output relationship models includes:

[0091] According to the above engine data, under the condition of the international standard atmosphere (i.e., T0 = 15 °C) and the condition of the aircraft flight speed being 0 (i.e., V0 = 0) for the aero-engine, through the exponential function fitting and the method of minimizing the sum of squared fitting errors, the relationship between the low-pressure rotor speed n1 and the throttle lever angle α and the aircraft flight altitude H is obtained as follows:

[0092] n1 = f5(α, H, V0, T0)

[0093] The low-pressure rotor speed n1 under different throttle lever angles α and aircraft flight altitudes H can be calculated through this formula; if it is necessary to calculate the low-pressure rotor speed n1 under different aircraft flight speeds V, it is also necessary to combine the above second input-output relationship model and introduce the aircraft flight speed variable, and the relationship between the low-pressure rotor speed n1 and the throttle lever angle α, the aircraft flight altitude H, and the aircraft flight speed V is obtained as follows:

[0094]

[0095] If it is necessary to calculate the low-pressure rotor speed n1 under different aircraft flight speeds V and atmospheric temperatures T, it is also necessary to continue to combine the above third input-output relationship model and introduce the atmospheric temperature variable, and the relationship between the low-pressure rotor speed n1 and the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T is obtained as follows:

[0096]

[0097] Combining the two relational expressions obtained above by integrating the second input-output relationship model and the third input-output relationship model, the full-parameter relationship model can be obtained as follows:

[0098]

[0099] Optionally, the above exponential function fitting and the method of minimizing the sum of squared fitting errors can be implemented by using the Power function in the cftool toolbox of Matlab software to fit and taking the parameters with the minimum SSE.

[0100] Step 14: Perform correction calculations on the above full-parameter relationship model to obtain a full-parameter working characteristic model for fitting calculations of the output parameters of the aeroengine.

[0101] Furthermore, the above correction calculations on the full-parameter relationship model to obtain the full-parameter working characteristic model include:

[0102] Comprehensively analyze the data of the three engine characteristic diagrams, and determine the importance ranking of the influence degrees of each of the above input parameters on the engine output parameters according to the above input-output relationship models. Among them, the above importance ranking is, in sequence, the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T;

[0103] Based on the above importance ranking, use the multi-dimensional numerical engineering fitting method based on the black box theory to iteratively correct the engine output parameters in sequence. First, substitute the above full-parameter relationship model into the above first input-output relationship model to obtain:

[0104] [F,W g ,n1,n2,T4] = f6(α,H,V0,T0).

[0105] Then, according to the engine throttle characteristic data and altitude-speed characteristic data, combine the above second input-output relationship model, that is, introduce the dual variables of the throttle lever angle and the aircraft flight altitude for correction, to obtain:

[0106]

[0107] Finally, according to the engine climate characteristic data, combine the above third input-output relationship model, that is, introduce the atmospheric temperature variable to continue the correction, and the above full-parameter working characteristic model is obtained as:

[0108]

[0109] Through this full-parameter working characteristic model, the functional relationship between the engine output parameters and the four input variables of α, H, V, and T is obtained, and the fitting calculation of the output parameters of the aeroengine can be realized.

[0110] As can be seen from the above, the embodiment of the present application provides a method for calculating and analyzing the working characteristics of an aeroengine. The intuitive presentation of the working characteristics of the aeroengine can provide the working characteristic data of the engine for the design of a flight simulator or flight simulation calculation, and can also provide method and data support for the aviation theory and flight practice training of flight crew or flight mission planning. According to the throttle characteristics, altitude-speed characteristics and climate characteristic data of the engine, the three characteristic data of the engine are integrated, and sequential iterative correction is performed according to the degree of influence on the engine output parameters, and the influence laws of input parameters such as throttle lever angle, flight altitude-speed, and atmospheric temperature on output parameters such as engine thrust, fuel flow rate, rotor speed, and exhaust temperature are comprehensively analyzed. Based on the black box theory, a numerical fitting method is used to establish a working characteristic model of the engine's full parameters, and the fitting calculation of the engine output parameters within the entire aircraft flight envelope is realized.

[0111] Embodiment 2

[0112] The embodiment of the present application provides a device for calculating and analyzing the working characteristics of an aeroengine. The device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. Among them, the memory is used to store software programs and modules, and the processor executes various functional applications and data processing by running the software programs and modules stored in the memory. The memory and the processor are connected by a bus. Specifically, when the processor runs the above computer program stored in the memory, any step in the first embodiment is implemented.

[0113] It should be understood that in the embodiment of the present application, the so-called processor may be a central processing unit (CPU), and the processor may also be other general-purpose processors, digital signal processors (DSPs), application specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc.

[0114] The memory may include a read-only memory, a flash memory, and a random access memory, and provides instructions and data to the processor. A part or all of the memory may also include a non-volatile random access memory.

[0115] As can be seen from the above, an aircraft engine operating characteristic calculation and analysis device provided by an embodiment of the present application integrates all engine input parameters involved according to the throttle characteristics, altitude-speed characteristics, and climate characteristic data of the engine, including input parameters such as throttle lever angle, aircraft flight altitude and speed, and atmospheric temperature, etc., and constructs a full-parameter operating characteristic model to fit and calculate the output parameters of the aircraft engine, breaking through the input and output variable limitations of a single operating characteristic data table, realizing the analysis and calculation of the output parameters during the engine operation within the entire aircraft flight envelope, and intuitively presenting the operating characteristics of the aircraft engine. It can provide the operating characteristic data of the engine for the design of flight simulators or flight simulation calculations, and can also provide methods and data support for the aviation theory and flight practice training of flight crew or flight mission planning.

[0116] It should be understood that if the above integrated module / unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, all or part of the processes of the above method embodiments of the present application can also be completed by a computer program instructing related hardware. The above computer program can be stored in a computer-readable storage medium. When the computer program is executed by a processor, the steps of the above method embodiments can be implemented. Among them, the above computer program includes computer program code, and the above computer program code can be in the form of source code, object code, executable file, or some intermediate form, etc. The above computer-readable medium can include: any entity or device capable of carrying the above computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electrical carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the content included in the above computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction.

[0117] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present application. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to these embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0118] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the above-mentioned division of each functional unit and module is used as an example. In actual applications, the above functions can be allocated to different functional units and modules according to needs, that is, the internal structure of the above-mentioned device can be divided into different functional units or modules to complete all or part of the functions described above. Each functional unit and module in the embodiment can be integrated into a processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of a software functional unit. In addition, the specific names of each functional unit and module are only for the convenience of mutual distinction and do not limit the protection scope of this application. The specific working processes of the units and modules in the above system can refer to the corresponding processes in the foregoing method embodiments and will not be elaborated herein.

[0119] It should be noted that the methods and their detailed examples provided in the above embodiments can be combined with the devices and equipment provided in the embodiments, and reference can be made to each other and will not be elaborated herein.

[0120] Those of ordinary skill in the art can realize that the units and algorithm steps of each example described in combination with the embodiments disclosed in this article can be implemented by electronic hardware, or by a combination of computer software and electronic hardware. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Professional technicians can use different methods for each specific application to implement the described functions, but such implementation should not be considered to exceed the scope of this application.

[0121] In the embodiments provided in this application, it should be understood that the disclosed device / terminal device and method can be implemented in other ways. For example, the device / equipment embodiments described above are only illustrative. For example, the above-mentioned division of modules or units is only a logical function division. In actual implementation, there can be other division methods. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed.

[0122] The above embodiments are only used to illustrate the technical solutions of this application, rather than to limit them; although this application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of each embodiment of this application, and should all be included in the protection scope of this application.

Claims

1. A calculation and analysis method for the operating characteristics of an aeroengine, characterized in that including: establishing an angular relationship model between the engine state and the throttle lever angle; respectively establishing corresponding input-output relationship models according to the angular relationship model and different engine characteristic diagrams, wherein the engine characteristic diagrams include a throttle characteristic diagram, an altitude-speed characteristic diagram, and a climate characteristic diagram, and each of the input-output relationship models respectively represents the functional relationship between the input parameters and the output parameters of the aeroengine under the conditions of the corresponding engine characteristic diagram; establishing a full-parameter relationship model according to each of the input-output relationship models, wherein the full-parameter relationship model is used to represent the functional relationship between the input parameters and the output parameters of the aeroengine under the conditions of all the engine characteristic diagrams; performing a correction calculation on the full-parameter relationship model to obtain a full-parameter working characteristic model for performing a fitting calculation on the output parameters of the aeroengine.

2. The calculation and analysis method for the operating characteristics of an aero-engine according to claim 1, characterized in that, The establishing of the angular relationship model between the engine state and the throttle lever angle includes: According to the engine data and the corresponding relationship between the engine state and the throttle lever angle, using the exponential function fitting and the method of minimizing the sum of squared fitting errors, the angular relationship model between the engine state and the throttle lever angle is established as: Condition = f1(α) where Condition is the engine state and α is the throttle lever angle.

3. The method for calculating and analyzing the operating characteristics of an aeroengine according to claim 2, wherein, The respectively establishing corresponding input-output relationship models according to the angular relationship model and different engine characteristic diagrams includes: establishing a first input-output relationship model with the rotor speed as the influencing factor according to the throttle characteristic diagram; establishing a second input-output relationship model with the altitude-speed as the influencing factor according to the angular relationship model and the altitude-speed characteristic diagram; establishing a third input-output relationship model with the atmospheric temperature as the influencing factor according to the angular relationship model and the climate characteristic diagram.

4. The method for calculating and analyzing the operating characteristics of an aeroengine according to claim 3, characterized in that The establishing of the first input-output relationship model with the rotor speed as the influencing factor according to the throttle characteristic diagram includes: According to the throttle characteristic diagram of an aeroengine under international standard atmospheric conditions, a first input-output relationship model between the input parameters (n1, H, V0, T0) and the engine output parameters (F, W g , n2, T4) is established by means of numerical fitting and interpolation as follows: [F,W g , n2, T4] = f2(n1, H, V0, T0) Among them, n1 is the low-pressure rotor speed, H is the aircraft flight altitude, V0 specifically refers to the aircraft flight speed being 0, T0 specifically refers to the atmospheric temperature being 15 degrees Celsius, F is the thrust, and W g is the fuel flow rate, n2 is the high-pressure rotor speed, and T4 is the required output temperature of the engine.

5. The method for calculating and analyzing the operating characteristics of an aeroengine according to claim 4, characterized in that, The establishing of the second input-output relationship model with the altitude-speed as the influencing factor according to the angular relationship model and the altitude-speed characteristic diagram includes: According to the altitude-speed characteristic diagram of an aeroengine under international standard atmospheric conditions, combined with the said angle relationship model, a second input-output relationship model between input parameters (Condition, H, V, T0) and engine output parameters (F, W g , n1, n2, T4) is established by means of multi-dimensional numerical fitting and interpolation as follows: [F, W g , n1, n2, T4] = f3(α, H, V, T0) where V is the aircraft flight speed.

6. The method for calculating and analyzing the operating characteristics of an aero-engine according to claim 5, wherein The establishing of the third input-output relationship model with the atmospheric temperature as the influencing factor according to the angular relationship model and the climate characteristic diagram includes: According to the engine climate characteristic diagram under the condition that the aircraft flight speed is 0, combined with the angle relationship model, the third input-output relationship model between the input parameters (Condition, H, V0, T) and the engine output parameters (F, W g , n1, n2, T4) is established by the method of multi-dimensional numerical fitting and interpolation as follows: [F,W g , n1, n2, T4] = f4(α, H, V0, T) where T is the atmospheric temperature.

7. The method for calculating and analyzing the operating characteristics of an aeroengine according to claim 6, wherein The establishing of the full-parameter relationship model according to each of the input-output relationship models includes: According to the engine data, under the conditions of the international standard atmosphere and the aircraft flight speed of 0 for the aeroengine, through the exponential function fitting and the method of minimizing the sum of squared fitting errors, the relationship between the low-pressure rotor speed n1, the throttle lever angle α, and the aircraft flight altitude H is obtained as: n1 = f5(α, H, V0, T0) Combining the second input-output relationship model and the third input-output relationship model, the relationship between the low-pressure rotor speed n1, the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T is obtained, that is, the full-parameter relationship model is:

8. The calculation and analysis method for the operating characteristics of an aero-engine according to claim 7, characterized in that The performing of the correction calculation on the full-parameter relationship model to obtain the full-parameter working characteristic model includes: Determine the importance ranking of the influence degrees of each input parameter on the engine output parameter according to each of the input-output relationship models, wherein the importance ranking is, in sequence, the throttle lever angle α, the aircraft flight altitude H, the aircraft flight speed V, and the atmospheric temperature T; Based on the importance ranking, substitute the full-parameter relationship model into the first input-output relationship model to obtain: [F,W g , n1, n2, T4] = f6(α, H, V0, T0) Combine with the second input-output relationship model for correction to obtain: Continue to correct in combination with the third input-output relationship model to obtain the full-parameter working characteristic model as:

9. An aircraft engine operating characteristic calculation and analysis device, comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method according to any one of claims 1 to 8 when executing the computer program.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, the steps of the method according to any one of claims 1 to 8 are implemented.

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