Method, device, equipment and medium for analyzing engine performance at high altitude and low Reynolds number

Abstract

The present disclosure provides an engine performance analysis method, device, equipment and medium under high altitude and low Reynolds number, which relates to the technical field of aviation engine test analysis, including: determining the design point parameters of the target engine based on the zero-dimensional engine model of the target engine to be analyzed, and the design point information; determining the inlet total temperature and inlet total pressure of multiple rotating parts in the target engine based on the zero-dimensional engine model of the target engine and the non-design point information within the design point parameters; determining the performance parameters of each rotating part based on the inlet total temperature, inlet total pressure, outlet static pressure and three-dimensional simulation model associated with each rotating part; if it is determined that the flow and power balance is achieved between multiple rotating parts, then determining the total performance parameters of the target engine under high altitude and low Reynolds number conditions according to the zero-dimensional engine model and the performance parameters of multiple rotating parts. The present disclosure can improve the accuracy of the engine performance analysis results obtained under high altitude and low Reynolds number conditions.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine testing and analysis, and in particular to a method, device, equipment and medium for analyzing engine performance at high altitude and low Reynolds number. Background Art

[0002] When an aircraft engine is flying at high altitude, the air density at high altitude is much lower than that on the ground, and the Reynolds number is also much lower than that on the ground. At this time, there is a significant difference in engine performance compared to the ground.

[0003] In the related art, in order to clarify the engine performance under high altitude and low Reynolds number conditions, the general characteristics of the components can be corrected through empirical correction methods to understand the performance of the rotating components in the engine under high altitude and low Reynolds number conditions.

[0004] However, the engine performance analysis method based on empirical correction usually remains at the performance analysis level of engine component characteristics, resulting in incomplete engine performance analysis results under high-altitude and low Reynolds number conditions, and requires a large amount of experimental data, which has high economic costs. Summary of the invention

[0005] The present disclosure provides a method, device, equipment and medium for analyzing engine performance at high altitude and low Reynolds number, which reduces the cost of engine performance analysis and improves the accuracy of the obtained engine performance analysis results. The technical solution of the present disclosure is as follows:

[0006] According to a first aspect of the present disclosure, a method for analyzing engine performance at high altitude and low Reynolds number is provided, comprising:

[0007] Determining design point parameters of the target engine based on a zero-dimensional engine model of the target engine to be analyzed and design point information;

[0008] Determining, within the design point parameters, an inlet total temperature and an inlet total pressure of a plurality of rotating components in the target engine based on a zero-dimensional engine model and non-design point information of the target engine;

[0009] Determining a performance parameter of each rotating component based on an inlet total temperature, an inlet total pressure, an outlet static pressure, and a three-dimensional simulation model associated with each rotating component;

[0010] If it is determined based on the performance parameters of each rotating component that flow and power balance is achieved between the multiple rotating components, the overall performance parameters of the target engine under high altitude and low Reynolds number conditions are determined based on the zero-dimensional engine model and the performance parameters of the multiple rotating components.

[0011] According to a second aspect of the present disclosure, there is provided an engine performance analysis device at high altitude and low Reynolds number, comprising:

[0012] A first determination module is configured to determine a design point parameter of the target engine based on a zero-dimensional engine model of the target engine to be analyzed and design point information;

[0013] A second determination module is configured to determine an inlet total temperature and an inlet total pressure of a plurality of rotating components in the target engine within the design point parameters based on a zero-dimensional engine model of the target engine and non-design point information;

[0014] A third determination module is configured to determine a performance parameter of each rotating component based on an inlet total temperature, an inlet total pressure, an outlet static pressure and a three-dimensional simulation model associated with each rotating component;

[0015] The fourth determination module is configured to determine the total performance parameters of the target engine under high altitude and low Reynolds number conditions based on the zero-dimensional engine model and the performance parameters of the multiple rotating components if flow and power balance is achieved between the multiple rotating components based on the performance parameters of each rotating component.

[0016] According to a third aspect of the present disclosure, there is provided an electronic device, including:

[0017] Processor; and

[0018] Memory for storing programs,

[0019] The program includes instructions, which, when executed by the processor, cause the processor to execute the method as described in the first aspect.

[0020] According to a fourth aspect of the present disclosure, a non-transitory computer-readable storage medium storing computer instructions is provided, wherein the computer instructions are used to cause the computer to execute the method as described in the first aspect.

[0021] The engine performance analysis method, device, equipment and medium under high altitude and low Reynolds number provided by the present invention can, on the one hand, determine the performance of rotating components separately through the three-dimensional simulation model of the rotating components without relying on a large amount of test data, so as to further determine the performance of the whole machine through the zero-dimensional model of the engine, thereby reducing the economic cost; on the other hand, the performance of the rotating components can be determined separately through the three-dimensional simulation model of each rotating component, thereby improving the simulation accuracy of the performance of each rotating component, and can also deeply explore the performance of the rotating components under high altitude and low Reynolds number conditions at the flow field level, as well as the overall performance of the engine, thereby improving the richness and accuracy of the engine performance analysis results obtained under high altitude and low Reynolds number conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Further details, features and advantages of the present disclosure are disclosed in the following description of exemplary embodiments in conjunction with the accompanying drawings, in which:

[0023] Figure 1 A flow chart showing a method for analyzing engine performance at high altitude and low Reynolds number according to an exemplary embodiment of the present disclosure is shown;

[0024] Figure 2 A cross-sectional characteristic diagram of a target engine of an exemplary embodiment of the present disclosure is shown;

[0025] Figure 3 A three-dimensional simulation model diagram of an axial flow compressor according to an exemplary embodiment of the present disclosure is shown;

[0026] Figure 4 A three-dimensional simulation model diagram of a centrifugal compressor according to an exemplary embodiment of the present disclosure is shown;

[0027] Figure 5 A three-dimensional simulation model diagram of a turbine according to an exemplary embodiment of the present disclosure is shown;

[0028] Figure 6 A graph showing the relationship between an engine intake air flow rate and an engine speed according to an exemplary embodiment of the present disclosure is shown;

[0029] Figure 7 A graph showing the relationship between the fuel flow rate of an engine and the engine speed according to an exemplary embodiment of the present disclosure is shown;

[0030] Figure 8 A graph showing the relationship between engine thrust and engine speed according to an exemplary embodiment of the present disclosure is shown;

[0031] Fig. 9 A graph showing the relationship between engine exhaust temperature and engine speed according to an exemplary embodiment of the present disclosure is shown;

[0032] Fig.10 Another relationship diagram between engine intake air flow and engine speed according to an exemplary embodiment of the present disclosure is shown;

[0033] Fig.11 Another engine fuel flow and engine speed relationship diagram of an exemplary embodiment of the present disclosure is shown;

[0034] Fig.12 Another engine thrust and engine speed relationship diagram of an exemplary embodiment of the present disclosure is shown;

[0035] Fig.13 Another engine exhaust temperature and engine speed relationship diagram of an exemplary embodiment of the present disclosure is shown;

[0036] Fig.14 A schematic block diagram of an engine performance analysis device at high altitude and low Reynolds number according to an exemplary embodiment of the present disclosure is shown;

[0037] Fig.15 A schematic block diagram of a chip according to an exemplary embodiment of the present disclosure is shown;

[0038] Fig.16 A structural block diagram of an exemplary electronic device that can be used to implement the embodiments of the present disclosure is shown. DETAILED DESCRIPTION

[0039] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0040] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0041] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0042] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0043] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0044] In the related technology, during the performance analysis of aviation engines, the general characteristics of the rotating parts in the engine can be corrected through empirical correction methods to understand the component performance of the rotating parts at high altitudes and low Reynolds numbers. Among them, the mass flow rate and efficiency in the characteristics of the engine rotating parts can be corrected based on the zero-dimensional engine performance simulation model. The rotating parts may include compression parts and turbines, etc., and the compression parts may include axial flow compressors and centrifugal compressors.

[0045] However, the engine performance analysis method based on empirical correction usually stays at the performance analysis of component characteristics, and cannot go deep into the flow field characteristics level to explore the performance of rotating components, and cannot obtain the overall performance of the engine, resulting in incomplete engine performance analysis results under high-altitude and low Reynolds number conditions; and in the process of correcting the general characteristics of rotating components based on experience, it is necessary to rely on a large amount of experimental data, resulting in high cost of engine performance analysis under high-altitude and low Reynolds number conditions.

[0046] Figure 1 A flowchart of an engine performance analysis method at high altitude and low Reynolds number according to an exemplary embodiment of the present disclosure is shown. The method can be applied to a terminal device, which can be a computer, a notebook or a tablet computer. Figure 1 As shown, the method of the embodiment of the present disclosure may include:

[0047] Step S101, determining the design point parameters of the target engine based on the zero-dimensional engine model of the target engine to be analyzed and the design point information;

[0048] Step S102, determining the inlet total temperature and inlet total pressure of multiple rotating parts in the target engine within the design point parameters based on the zero-dimensional engine model and non-design point information of the target engine;

[0049] Step S103, determining the performance parameters of each rotating component based on the inlet total temperature, inlet total pressure, outlet static pressure and the three-dimensional simulation model associated with each rotating component;

[0050] Step S104: If it is determined based on the performance parameters of each rotating component that the flow and power balance is achieved between the multiple rotating components, the total performance parameters of the target engine under high altitude and low Reynolds number conditions are determined based on the zero-dimensional engine model and the performance parameters of the multiple rotating components.

[0051] In summary, the engine performance analysis method under high altitude and low Reynolds number provided by the embodiment of the present disclosure can determine the design point parameters of the target engine to be analyzed based on the zero-dimensional engine model of the target engine and the design point information; within the design point parameters, based on the zero-dimensional engine model of the target engine and the non-design point information, determine the inlet total temperature and inlet total pressure of multiple rotating components in the target engine; and determine the performance parameters of each rotating component based on the inlet total temperature, inlet total pressure, outlet static pressure and three-dimensional simulation model associated with each rotating component; then, if it is determined based on the performance parameters of each rotating component that the flow and power balance is achieved between the multiple rotating components, then the total performance parameters of the target engine under high altitude and low Reynolds number conditions are determined based on the zero-dimensional engine model and the performance parameters of the multiple rotating components. On the one hand, without relying on a large amount of test data, the performance of the rotating components can be determined separately through the three-dimensional simulation model of the rotating components, so as to further determine the performance of the whole machine through the zero-dimensional model of the engine, thereby reducing the economic cost; on the other hand, the performance of the rotating components can be determined separately through the three-dimensional simulation model of each rotating component, thereby improving the simulation accuracy of the performance of each rotating component, and can also deeply explore the performance of the rotating components under high-altitude and low Reynolds number conditions at the flow field level, as well as the overall performance of the engine, thereby improving the richness and accuracy of the engine performance analysis results under high-altitude and low Reynolds number conditions.

[0052] The following Figure 1 The specific implementation methods of each step in the embodiment shown are described in detail:

[0053] In step S101 , the terminal device may determine the design point parameters of the target engine based on the zero-dimensional engine model of the target engine to be analyzed and the design point information.

[0054] In an embodiment of the present disclosure, a zero-dimensional engine model of the target engine may be pre-constructed; wherein the design point information may include a preset altitude, Mach number, engine operating conditions and control laws, etc., and the design point parameters may include an axial compressor pressure ratio, a centrifugal compressor pressure ratio and a turbine inlet temperature, etc.

[0055] In an optional embodiment, the process of determining the design point parameters of the target engine based on the zero-dimensional engine model of the target engine to be analyzed and the design point information by the terminal device may include: inputting the design point information into the zero-dimensional engine model of the target engine to obtain the performance parameters of the target engine, and repeating the process of obtaining the performance parameters of the target engine until the performance parameters of the target engine meet the performance parameter index, and obtaining the design point parameters of the target engine when the performance parameters of the target engine meet the performance parameter index. The performance parameters may include thrust and / or fuel consumption rate.

[0056] In step S102 , the terminal device may determine the inlet total temperature and inlet total pressure of multiple rotating components in the target engine within the design point parameters based on the zero-dimensional engine model and non-design point information of the target engine.

[0057] In the embodiment of the present disclosure, the non-design point information may include the engine operating conditions and control laws of the non-design points.

[0058] In an optional embodiment, the process of determining the inlet total temperature and inlet total pressure of multiple rotating parts in the target engine based on the zero-dimensional engine model and non-design point information of the target engine by the terminal device may include: obtaining the non-design point information of the target engine under the condition of high altitude and low Reynolds number, and inputting the non-design point information under the condition of high altitude and low Reynolds number into the zero-dimensional engine model of the target engine to obtain the boundary condition parameters of the rotating parts in the target engine, and then extracting the inlet total temperature and inlet total pressure from the boundary condition parameters of each rotating part. Among them, the boundary condition parameters of each rotating part may include the inlet total temperature, inlet total pressure and rotation speed of the rotating part.

[0059] The process of the terminal device acquiring the non-design point information of the target engine under the condition of high altitude and low Reynolds number may include: in response to the input operation of acquiring the non-design point information for the target engine, acquiring the non-design point information of the target engine under the condition of high altitude and low Reynolds number; or, in response to acquiring the performance analysis instruction, searching the target information table of the terminal device for the non-design point information of the target engine under the condition of high altitude and low Reynolds number associated with the engine identifier carried in the performance analysis instruction. The target information table is used to store the non-design point information of each engine to be analyzed under the condition of high altitude and low Reynolds number.

[0060] In step S103, the terminal device may determine the performance parameters of each rotating component based on the inlet total temperature, inlet total pressure, outlet static pressure and the three-dimensional simulation model associated with each rotating component.

[0061] In the embodiments of the present disclosure, the performance parameters of the rotating components may include the flow rate, pressure ratio, efficiency and power of the rotating components. The three-dimensional simulation model associated with each rotating component may be pre-built, wherein the outlet static pressure may be an estimated value, which may be determined based on actual needs, and the embodiments of the present disclosure do not limit this.

[0062] In an optional embodiment, the process of determining the performance parameters of each rotating component by the terminal device based on the inlet total temperature, inlet total pressure, outlet static pressure and a three-dimensional simulation model associated with each rotating component may include: inputting the inlet total temperature, inlet total pressure and outlet static pressure associated with each rotating component into the three-dimensional simulation model corresponding to each rotating component to obtain the performance parameters of each rotating component.

[0063] In step S104, if flow and power balance is achieved among multiple rotating components based on the performance parameters of each rotating component, the terminal device can determine the total performance parameters of the target engine under high altitude and low Reynolds number conditions based on the zero-dimensional engine model and the performance parameters of the multiple rotating components.

[0064] In the disclosed embodiment, during the performance analysis of the engine, in order to further improve the accuracy of the analysis results obtained, the volumetric effect is taken into account during the engine performance analysis. Therefore, it is necessary to achieve flow and power balance between multiple rotating components. Among them, the total performance parameters of the target engine under high altitude and low Reynolds number conditions may include engine thrust, engine fuel consumption rate, engine intake flow rate and engine exhaust temperature, etc.

[0065] In an optional embodiment, the plurality of rotating components include a compressor and a turbine, and the performance parameters include flow and power of the rotating components. The process of determining whether flow and power balance is achieved among the plurality of rotating components based on the performance parameters of each rotating component by the terminal device may include: determining, for each group of adjacent rotating components among the plurality of rotating components, a flow difference between an inlet flow of a first rotating component and an outlet flow of a second rotating component, and determining a ratio of the flow difference to an inlet flow of the first rotating component, to obtain a flow balance parameter associated with each group of adjacent rotating components; then, determining a ratio of compressor power to mechanical efficiency, The total power of the compressor is obtained, and the difference between the turbine power and the total power of the compressor is determined to obtain the power difference, and the ratio of the power difference to the turbine power is determined to obtain the power balance parameter; further, if the absolute values ​​of the flow balance parameters associated with each group of adjacent rotating parts are less than the first threshold value, and the absolute value of the power balance parameter is less than the second threshold value, it is determined that the flow and power balance is achieved between the multiple rotating parts, wherein, in each group of adjacent rotating parts, the gas first flows into the second rotating part and then flows into the first rotating part. The first threshold value and the second threshold value can be determined based on actual needs, and the embodiments of the present disclosure do not limit this. It is possible to determine whether the target engine meets the equilibrium state based on the flow information and power information of multiple rotating parts in the target engine while considering the volumetric effect of the engine, so as to ensure the rapid realization of the equilibrium state of the target engine.

[0066] The process of the terminal device determining the flow balance parameter associated with each group of adjacent rotating components can be implemented based on Formula 1, which is:

[0067]

[0068] In Formula 1, W in,i represents the inlet flow rate of the first rotating component i, W out,j represents the outlet flow rate of the second rotating component j, ΔWr Represents the flow balance parameter.

[0069] The process of the terminal device determining the power balance parameter between the multiple rotating components can be implemented based on Formula 2, which is:

[0070]

[0071] In Formula 2, PW turbine Indicates turbine power, PW compressor represents compressor power, η m Indicates mechanical efficiency, ΔPW r represents the power balance parameter; where ∑PW compressor Indicates the sum of the powers of multiple compressors when there are multiple compressors.

[0072] In an optional embodiment, the process of determining the total performance parameters of the target engine under high altitude and low Reynolds number conditions based on the zero-dimensional engine model and the performance parameters of multiple rotating components by the terminal device may include: inputting the performance parameters of multiple rotating components into the zero-dimensional engine model to determine the total performance parameters of the target engine under high altitude and low Reynolds number conditions.

[0073] It can be understood that in the embodiment of the present disclosure, if the absolute value of the flow balance parameter associated with any group of adjacent rotating components is greater than or equal to the first threshold, or the absolute value of the power balance parameter is greater than or equal to the second threshold, it is determined that the flow and power balance is not achieved between the multiple rotating components.

[0074] In an optional embodiment, if the terminal device determines the flow and power imbalance among multiple rotating components based on the performance parameters of each rotating component, the outlet static pressure of each rotating component is iteratively updated based on the aerodynamic and thermal parameters and the outlet static pressure associated with each rotating component to obtain the updated outlet static pressure of the multiple rotating components, and the updated performance parameters of each rotating component are determined based on the inlet total temperature, inlet total pressure, updated outlet static pressure and three-dimensional simulation model associated with each rotating component; then, the process of determining the updated performance parameters of each rotating component is repeated until the flow and power balance is determined between the multiple rotating components based on the updated performance parameters of each rotating component, and the total performance parameters of the target engine under high altitude and low Reynolds number conditions are determined based on the zero-dimensional engine model and the updated performance parameters of each rotating component. When the flow and power imbalance among multiple rotating components is determined, the outlet static pressure of each rotating component can be iteratively updated according to the aerodynamic and thermal parameters and the outlet static pressure associated with each rotating component until the flow and power balance is achieved among the multiple rotating components, and then the total performance parameters of the target engine under high altitude and low Reynolds number conditions are determined, so as to improve the accuracy and reliability of the total performance parameters of the target engine under high altitude and low Reynolds number conditions obtained while considering the volumetric effect of the engine.

[0075] In an optional embodiment, the rotating component includes an axial flow compressor, and the aerodynamic and thermal parameters associated with the axial flow compressor include an axial flow compressor static temperature, an axial flow compressor inlet flow rate, and an axial flow compressor outlet flow rate. The terminal device iteratively updates the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters and the outlet static pressure associated with each rotating component. The process of obtaining the updated outlet static pressures of multiple rotating components may include: determining a first correction value according to the axial flow compressor static temperature, the axial flow compressor inlet flow rate, the axial flow compressor outlet flow rate, and a first target volume; and Then, based on the outlet static pressure of the axial compressor and the first correction value, the updated outlet static pressure of the axial compressor is determined, wherein the first target volume is the volume at the outlet of the axial compressor in the cross-sectional characteristic information, the cross-sectional characteristic information is used to characterize the design structure of the target engine, and the cross-sectional characteristic information is determined by the terminal device after determining the design point parameters of the target engine and introducing the volume effect, according to the performance parameters of the target engine that meet the design point requirements, and the cross-sectional characteristic information may include a cross-sectional characteristic diagram, and the volume of each volume in the cross-sectional characteristic diagram of the target engine. In the case where the rotating part includes an axial compressor, the outlet static pressure of the axial compressor can be updated to improve the accuracy of the obtained performance parameters of the axial compressor, and to improve the accuracy of the total performance parameters of the engine including the axial compressor under high altitude and low Reynolds number conditions.

[0076] Among them, the process of the terminal device determining the updated outlet static pressure of the axial flow compressor based on the outlet static pressure of the axial flow compressor and the first correction value may include: determining the sum of the outlet static pressure of the axial flow compressor and the first correction value as the updated outlet static pressure of the axial flow compressor; or determining the weighted sum of the outlet static pressure of the axial flow compressor and the first correction value as the updated outlet static pressure of the axial flow compressor.

[0077] It should be noted that the weight values ​​of the outlet static pressure and the first correction value assigned to the axial flow compressor by the terminal device can be determined based on actual needs, and the embodiments of the present disclosure do not limit this. The sum of the weight values ​​of the outlet static pressure and the first correction value assigned to the axial flow compressor can be 1.

[0078] Optionally, the process of determining the updated outlet static pressure of the axial flow compressor by the terminal device can be implemented based on Formula 3.

[0079] Formula 3 is:

[0080]

[0081] In formula 3, P s23 represents the static pressure at the outlet of the axial compressor, T s23 represents the static temperature of the axial compressor, W a2 represents the inlet flow rate of the axial compressor, W a23 represents the axial compressor outlet flow rate, V1 represents the first target volume, Δt is the time step, k is the gas adiabatic index, R is the gas constant, and α is the iteration period.

[0082] It can be understood that in formula 3 is the first correction value.

[0083] In an optional embodiment, the rotating component includes a turbine, and the aerodynamic and thermal parameters associated with the turbine include turbine static temperature, turbine outlet flow rate, and nozzle inlet flow rate. The terminal device iteratively updates the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters and outlet static pressure associated with each rotating component. The process of obtaining the updated outlet static pressure of multiple rotating components may include: determining a second correction value based on the turbine static temperature, turbine outlet flow rate, nozzle inlet flow rate, and the second target volume; then, determining the updated outlet static pressure of the turbine based on the outlet static pressure of the turbine and the second correction value, wherein the second target volume is the volume at the turbine outlet position in the cross-sectional feature information. When the rotating component includes a turbine, the outlet static pressure of the turbine may be updated to improve the accuracy of the obtained performance parameters of the turbine, and to improve the accuracy of the total performance parameters of the engine including the turbine under high altitude and low Reynolds number conditions.

[0084] Among them, the process of the terminal device determining the updated outlet static pressure of the turbine based on the outlet static pressure of the turbine and the second correction value may include: determining the sum of the outlet static pressure of the turbine and the second correction value as the updated outlet static pressure of the turbine; or determining the weighted sum of the outlet static pressure of the turbine and the second correction value as the updated outlet static pressure of the turbine.

[0085] It should be noted that the weight values ​​of the outlet static pressure and the second correction value assigned to the turbine by the terminal device can be determined based on actual needs, and the embodiment of the present disclosure does not limit this. The sum of the weight values ​​of the outlet static pressure and the second correction value assigned to the turbine can be 1.

[0086] Optionally, the process of the terminal device determining the updated outlet static pressure of the turbine can be implemented based on Formula 4, which is:

[0087]

[0088] In Formula 4, P s5 represents the turbine outlet static pressure, T s5 represents the turbine static temperature, W g5 represents the turbine outlet flow rate, W g9 represents the nozzle inlet flow rate, and V3 represents the second target volume.

[0089] In an optional embodiment, when the rotating component includes a turbine, the aerodynamic and thermal parameters associated with the turbine also include turbine power, axial compressor power and centrifugal compressor power. After iteratively updating the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters and outlet static pressure associated with each rotating component to obtain updated outlet static pressures of multiple rotating components, the terminal device can also: determine the updated inlet total temperature of the turbine based on the turbine power, axial compressor power, centrifugal compressor power and mechanical efficiency; and update the inlet total temperature of the turbine when the rotating component includes a turbine, so as to further improve the accuracy of the obtained performance parameters of the turbine, and further improve the accuracy of the obtained total performance parameters of the engine including the turbine under high altitude and low Reynolds number conditions.

[0090] It can be understood that after the total inlet temperature of the turbine is updated, the terminal device determines the updated performance parameters of each rotating component based on the updated inlet total temperature, inlet total pressure, updated outlet static pressure and three-dimensional simulation model associated with each rotating component. The process may include: determining the updated performance parameters of the turbine based on the updated inlet total temperature, inlet total pressure, updated outlet static pressure and three-dimensional simulation model associated with the turbine.

[0091] The process of determining the updated inlet total temperature of the turbine by the terminal device according to the turbine power, the axial flow compressor power, the centrifugal compressor power and the mechanical efficiency may include: determining the updated inlet total temperature of the turbine based on the turbine power, the axial flow compressor power, the centrifugal compressor power, the mechanical efficiency and a preset formula, wherein the preset formula may be:

[0092]

[0093] In Formula 5, PW axial compressor Indicates the axial compressor power, PW centrifugal compressor represents the centrifugal compressor power, and ΔPW represents the updated total inlet temperature of the turbine.

[0094] In an optional embodiment, the rotating component includes a centrifugal compressor, and the aerodynamic and thermal parameters of the centrifugal compressor include the total pressure at the centrifugal compressor outlet. The terminal device iteratively updates the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters and the outlet static pressure associated with each rotating component. The process of obtaining the updated outlet static pressure of multiple rotating components may include: determining a third correction value based on the total pressure at the centrifugal compressor outlet, the Mach number of the current iteration cycle, the Mach number of the previous iteration cycle, and the outlet static pressure of the centrifugal compressor; then, determining the updated outlet static pressure of the centrifugal compressor based on the outlet static pressure of the centrifugal compressor and the third correction value. In the case where the rotating component includes a centrifugal compressor, the outlet static pressure of the centrifugal compressor may be updated to improve the accuracy of the obtained performance parameters of the centrifugal compressor, and to improve the accuracy of the total performance parameters of the engine including the centrifugal compressor under high altitude and low Reynolds number conditions.

[0095] Among them, the process of the terminal device determining the updated outlet static pressure of the centrifugal compressor based on the outlet static pressure of the centrifugal compressor and the third correction value may include: determining the sum of the outlet static pressure of the centrifugal compressor and the third correction value as the updated outlet static pressure of the centrifugal compressor; or, determining the weighted sum of the outlet static pressure of the centrifugal compressor and the third correction value as the updated outlet static pressure of the centrifugal compressor.

[0096] It should be noted that the weight values ​​of the outlet static pressure and the third correction value assigned to the centrifugal compressor by the terminal device can be determined based on actual needs, and the embodiments of the present disclosure do not limit this. The sum of the weight values ​​of the outlet static pressure and the third correction value assigned to the centrifugal compressor can be 1.

[0097] Optionally, the process of determining the updated outlet static pressure of the centrifugal compressor by the terminal device can be implemented based on Formula 6.

[0098] Formula 6 is:

[0099]

[0100] In formula 6, Ps3 represents the outlet static pressure of the centrifugal compressor, Pt3 represents the outlet total pressure of the centrifugal compressor, Ma3 is the Mach number, represents the Mach number of the current iteration cycle, represents the Mach number of the previous iteration cycle, and f(Ma3) is an adjustment coefficient for the outlet static pressure of the centrifugal compressor determined based on the Mach number. The adjustment coefficient can be an estimated value based on the Mach number.

[0101] It should be noted that in the embodiments of the present disclosure, the terminal device can obtain the flow field characteristics of multiple rotating components in the target engine under different high-altitude and low-Reynolds number conditions, the performance parameters of multiple rotating components, and the overall performance parameters of the target engine under high-altitude and low-Reynolds number conditions based on the engine performance analysis process provided in the above embodiments, so as to achieve in-depth component performance analysis of flow field characteristics under high-altitude and low-Reynolds number conditions, as well as whole-machine performance analysis.

[0102] For example, for a target engine, the terminal device can determine the design point parameters and cross-sectional feature information of the target engine based on the zero-dimensional engine model of the target engine and the design point information, wherein: Figure 2 A cross-sectional characteristic diagram in the cross-sectional characteristic information of a target engine provided in an embodiment of the present disclosure is shown. Figure 2 It can be seen that the rotating parts in the target engine may include an axial flow compressor, a centrifugal compressor and a turbine. The target engine also includes a combustion chamber, a tail nozzle and three volumes, wherein volume module 1 is located between the axial flow compressor and the offline compressor, volume module 2 is located between the centrifugal compressor and the turbine, and volume module 3 is located between the turbine and the tail nozzle.

[0103] Next, the terminal device can determine the inlet total temperature and inlet total pressure of the axial compressor, centrifugal compressor and turbine in the target engine within the design point parameters based on the zero-dimensional engine model and non-design point information of the target engine; and determine the performance parameters of the axial compressor based on the inlet total temperature, inlet total pressure, outlet static pressure and three-dimensional simulation model associated with the axial compressor; at the same time, determine the performance parameters of the centrifugal compressor based on the inlet total temperature, inlet total pressure, outlet static pressure and three-dimensional simulation model associated with the centrifugal compressor; at the same time, determine the performance parameters of the turbine based on the inlet total temperature, inlet total pressure, outlet static pressure and three-dimensional simulation model associated with the turbine, wherein the three-dimensional simulation model of the axial compressor is as follows: Figure 3 As shown in Figure 2, the three-dimensional simulation model of the centrifugal compressor is as follows: Figure 4 As shown in Figure 2, the three-dimensional simulation model of the turbine is as follows: Figure 5 shown.

[0104] Furthermore, if the terminal equipment determines that the flow balance is satisfied between the axial flow compressor and the centrifugal compressor, between the centrifugal compressor and the turbine, and between the turbine and the tail nozzle, and the power balance is satisfied between the axial flow compressor, the centrifugal compressor and the turbine, then the performance parameters of the axial flow compressor, the centrifugal compressor and the turbine can be input into the zero-dimensional engine model of the target engine to obtain the total performance parameters of the target engine under high altitude and low Reynolds number conditions.

[0105] Optional, for example Figure 2 For the target engine shown, the terminal device can determine the total performance parameters of the target engine under the high-altitude and low-Reynolds number conditions (H=10km, Ma=0.6) at a flight altitude of 10 kilometers and a Mach number of 0.6 by using a zero-dimensional simulation method, an empirical correction method, and a variable-dimensional simulation method (the engine performance analysis method under the high-altitude and low-Reynolds number provided in the embodiment of the present disclosure), wherein the engine intake flow rate of the target engine under the high-altitude and low-Reynolds number conditions (H=10km, Ma=0.6) at a flight altitude of 10 kilometers and a Mach number of 0.6 is as follows: Figure 6 As shown, the engine fuel flow is Figure 7 As shown, the engine thrust is Figure 8 As shown, the engine exhaust temperature is Fig. 9 As shown, wherein the abscissa is the engine speed;

[0106] The terminal device can also determine the total performance parameters of the target engine under the high-altitude low Reynolds number conditions (H=14km, Ma=0.55) of the target engine at a flight altitude of 14 kilometers and a Mach number of 0.55, obtained by the zero-dimensional simulation method, the empirical correction method and the variable-dimensional simulation method. Among them, the engine intake flow of the target engine under the high-altitude low Reynolds number conditions of the flight altitude of 14 kilometers and a Mach number of 0.55 is as follows Fig.10 As shown, the engine fuel flow is Fig.11 As shown, the engine thrust is Fig.12 As shown, the engine exhaust temperature is Fig.13 As shown, the combination Fig.10 It can be seen that compared with the empirically corrected high-altitude low Reynolds number engine performance analysis method, the difference between the engine intake flow rate determined based on the embodiment of the present disclosure and the test data is smaller, reducing the calculation deviation by 9.54%.

[0107] The above mainly introduces the solution provided by the embodiment of the present disclosure from the perspective of the terminal device. It is understandable that in order to realize the above functions, the terminal device includes a hardware structure and / or software module corresponding to the execution of each function. Those skilled in the art should easily realize that, in combination with the units and algorithm steps of each example described in the embodiments disclosed in this article, the present disclosure can be implemented in the form of hardware or a combination of hardware and computer software. Whether a function is executed in the form of hardware or computer software driving hardware depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of the present disclosure.

[0108] The embodiments of the present disclosure may divide the functional units of the terminal device according to the above method examples. For example, each functional module may be divided corresponding to each function, or two or more functions may be integrated into one processing module. The above integrated modules may be implemented in the form of hardware or in the form of software functional modules. It should be noted that the division of modules in the embodiments of the present disclosure is schematic and is only a logical function division. There may be other division methods in actual implementation.

[0109] In the case of dividing each functional module according to each function, an exemplary embodiment of the present disclosure provides an engine performance analysis device at high altitude and low Reynolds number, which can be a terminal device or a chip applied to a terminal device. Fig.14 FIG. 2 shows a schematic block diagram of functional modules of an engine performance analysis device at high altitude and low Reynolds number according to an exemplary embodiment of the present disclosure. Fig.14 As shown, the high altitude low Reynolds number engine performance analysis device 1400 includes:

[0110] The first determination module 1401 is configured to determine the design point parameters of the target engine based on the zero-dimensional engine model of the target engine to be analyzed and the design point information;

[0111] A second determination module 1402 is configured to determine an inlet total temperature and an inlet total pressure of a plurality of rotating components in the target engine within the design point parameters based on a zero-dimensional engine model of the target engine and non-design point information;

[0112] A third determination module 1403 is configured to determine the performance parameter of each rotating component based on the inlet total temperature, inlet total pressure, outlet static pressure and the three-dimensional simulation model associated with each rotating component;

[0113] The fourth determination module 1404 is configured to determine the total performance parameters of the target engine under high altitude and low Reynolds number conditions based on the zero-dimensional engine model and the performance parameters of the multiple rotating components if it is determined that flow and power balance is achieved between the multiple rotating components based on the performance parameters of each rotating component.

[0114] Optional, such as Fig.14 As shown, the device further includes an updating module 1405 configured to:

[0115] If the flow and power imbalance among the multiple rotating components is determined based on the performance parameters of each rotating component, the outlet static pressure of each rotating component is iteratively updated based on the aerodynamic and thermal parameters associated with each rotating component and the outlet static pressure to obtain updated outlet static pressures of the multiple rotating components, and the updated performance parameters of each rotating component are determined based on the inlet total temperature, inlet total pressure, the updated outlet static pressure and the three-dimensional simulation model associated with each rotating component;

[0116] The process of determining the updated performance parameters of each rotating component is repeated until flow and power balance is achieved among the multiple rotating components based on the updated performance parameters of each rotating component, and then the total performance parameters of the target engine under high altitude and low Reynolds number conditions are determined based on the zero-dimensional engine model and the updated performance parameters of each rotating component.

[0117] Optionally, the rotating component includes an axial flow compressor, and the aerodynamic and thermal parameters associated with the axial flow compressor include the static temperature of the axial flow compressor, the inlet flow rate of the axial flow compressor, and the outlet flow rate of the axial flow compressor.

[0118] The updating module 1405 is configured to:

[0119] Determining a first correction value according to the static temperature of the axial compressor, the inlet flow rate of the axial compressor, the outlet flow rate of the axial compressor and a first target volume, wherein the first target volume is the volume at the outlet of the axial compressor in the cross-sectional characteristic information, and the cross-sectional characteristic information is used to characterize the design structure of the target engine;

[0120] An updated outlet static pressure of the axial flow compressor is determined based on the outlet static pressure of the axial flow compressor and the first correction value.

[0121] Optionally, the rotating component includes a turbine, and the aerodynamic and thermal parameters associated with the turbine include turbine static temperature, turbine outlet flow rate and nozzle inlet flow rate,

[0122] The updating module 1405 is configured to:

[0123] Determining a second correction value according to the turbine static temperature, the turbine outlet flow rate, the nozzle inlet flow rate and a second target volume, wherein the second target volume is the volume at the turbine outlet position in the cross-sectional characteristic information;

[0124] An updated outlet static pressure of the turbine is determined based on the outlet static pressure of the turbine and the second correction value.

[0125] Optionally, the rotating component includes a turbine, and the aerodynamic and thermal parameters associated with the turbine include turbine power, axial compressor power, and centrifugal compressor power. The device further includes a fifth determining module 1406 configured to:

[0126] determining an updated inlet total temperature of the turbine according to the turbine power, the axial compressor power, the centrifugal compressor power and the mechanical efficiency;

[0127] Determining the updated performance parameters of each rotating component according to the inlet total temperature, the inlet total pressure, the updated outlet static pressure and the three-dimensional simulation model associated with each rotating component includes:

[0128] Updated performance parameters of the turbine are determined based on the updated inlet total temperature, the inlet total pressure, the updated outlet static pressure and the three-dimensional simulation model associated with the turbine.

[0129] Optionally, the rotating component includes a centrifugal compressor, and the aerodynamic and thermal parameters of the centrifugal compressor include the total pressure at the centrifugal compressor outlet,

[0130] The updating module 1405 is configured to:

[0131] Determine a third correction value according to the total pressure at the centrifugal compressor outlet, the Mach number of the current iteration cycle, the Mach number of the previous iteration cycle, and the outlet static pressure of the centrifugal compressor;

[0132] An updated outlet static pressure of the centrifugal compressor is determined based on the outlet static pressure of the centrifugal compressor and the third correction value.

[0133] Optionally, the plurality of rotating components include a compressor and a turbine, the performance parameters include flow and power of the rotating components, and the apparatus further includes a determination module configured as 1407:

[0134] For each group of adjacent rotating components among the plurality of rotating components, a flow difference between an inlet flow of a first rotating component and an outlet flow of a second rotating component is determined, and a ratio of the flow difference to an inlet flow of the first rotating component is determined to obtain a flow balance parameter associated with each group of adjacent rotating components, wherein in each group of adjacent rotating components, gas first flows into the second rotating component and then flows into the first rotating component;

[0135] Determining a ratio of compressor power to mechanical efficiency to obtain a total compressor power, determining a difference between turbine power and the total compressor power to obtain a power difference, and determining a ratio of the power difference to the turbine power to obtain a power balance parameter;

[0136] If the absolute value of the flow balance parameter associated with each group of adjacent rotating components is less than the first threshold, and the absolute value of the power balance parameter is less than the second threshold, it is determined that flow and power balance is achieved between the plurality of rotating components.

[0137] Fig.15 Schematic block diagram of a chip according to an exemplary embodiment of the present disclosure is shown. Fig.15 As shown, the chip 1500 includes one or more (including two) processors 1501 and a communication interface 1502. The communication interface 1502 can support the terminal device to execute the data sending and receiving steps in the above-mentioned high-altitude low Reynolds number engine performance analysis method, and the processor 1501 can support the terminal device to execute the data processing steps in the above-mentioned high-altitude low Reynolds number engine performance analysis method.

[0138] Optional, such as Fig.15 As shown, the chip 1500 also includes a memory 1503, which may include a read-only memory and a random access memory, and provides operation instructions and data to the processor. A portion of the memory may also include a non-volatile random access memory (NVRAM).

[0139] In some embodiments, Fig.15As shown, the processor 1501 performs corresponding operations by calling the operation instructions stored in the memory (the operation instructions may be stored in the operating system). The processor 1501 controls the processing operations of any one of the terminal devices, and the processor may also be called a central processing unit (CPU). The memory 1503 may include a read-only memory and a random access memory, and provides instructions and data to the processor 1501. A portion of the memory 1503 may also include NVRAM. For example, in an application, the memory, the communication interface, and the memory are coupled together through a bus system, wherein the bus system may include a power bus, a control bus, and a status signal bus in addition to a data bus. However, for the sake of clarity, in Fig.15 Various buses are labeled as bus system 1504.

[0140] The method disclosed in the above-mentioned embodiment of the present disclosure can be applied to a processor or implemented by a processor. The processor may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by an integrated logic circuit of hardware in the processor or an instruction in the form of software. The above-mentioned processor may be a general-purpose processor, a digital signal processor (digital signal processing, DSP), an ASIC, a field-programmable gate array (field-programmable gate array, FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present disclosure can be implemented or executed. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in conjunction with the embodiment of the present disclosure can be directly embodied as being executed by a hardware decoding processor, or executed by a combination of hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, etc. The storage medium is located in a memory, and the processor reads the information in the memory and completes the steps of the above method in conjunction with its hardware.

[0141] The exemplary embodiment of the present disclosure also provides an electronic device, comprising: at least one processor; and a memory connected to the at least one processor in communication. The memory stores a computer program that can be executed by the at least one processor, and the computer program is used to cause the electronic device to perform the method according to the embodiment of the present disclosure when executed by the at least one processor.

[0142] The exemplary embodiments of the present disclosure also provide a non-transitory computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor of a computer, is used to cause the computer to perform the method according to the embodiments of the present disclosure.

[0143] The exemplary embodiments of the present disclosure further provide a computer program product, including a computer program, wherein when the computer program is executed by a processor of a computer, the computer is used to enable the computer to perform the method according to the embodiments of the present disclosure.

[0144] refer to Fig.16 , a block diagram of an electronic device 1600 that can be used as a terminal device of the present disclosure will now be described, which is an example of a hardware device that can be applied to various aspects of the present disclosure. The electronic device is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workbenches, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples, and are not intended to limit the implementation of the present disclosure described and / or required herein.

[0145] like Fig.16 As shown, the electronic device 1600 includes a computing unit 1601, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 1602 or a computer program loaded from a storage unit 1608 into a random access memory (RAM) 1603. In the RAM 1603, various programs and data required for the operation of the electronic device 1600 can also be stored. The computing unit 1601, the ROM 1602, and the RAM 1603 are connected to each other via a bus 1604. An input / output (I / O) interface 1605 is also connected to the bus 1604.

[0146] Multiple components in the electronic device 1600 are connected to the I / O interface 1605, including: an input unit 1606, an output unit 1607, a storage unit 1608, and a communication unit 1609. The input unit 1606 can be any type of device that can input information to the electronic device 1600, and the input unit 1606 can receive input digital or character information, and generate key signal input related to user settings and / or function control of the electronic device. The output unit 1607 can be any type of device that can present information, and can include but is not limited to a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. The storage unit 1608 can include but is not limited to a disk, an optical disk. The communication unit 1609 allows the electronic device 1600 to exchange information / data with other devices through a computer network such as the Internet and / or various telecommunication networks, and can include but is not limited to a modem, a network card, an infrared communication device, a wireless communication transceiver, and / or a chipset, such as a Bluetooth TM device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0147] The computing unit 1601 may be a variety of general and / or special processing components with processing and computing capabilities. Some examples of the computing unit 1601 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 1601 performs the various methods and processes described above. For example, in some embodiments, the method of the exemplary embodiment of the present disclosure may be implemented as a computer software program, which is tangibly included in a machine-readable medium, such as a storage unit 1608. In some embodiments, part or all of the computer program may be loaded and / or installed on the electronic device 1600 via the ROM 1602 and / or the communication unit 1609. In some embodiments, the computing unit 1601 may be configured to perform the method of the exemplary embodiment of the present disclosure by any other appropriate means (e.g., by means of firmware).

[0148] The program code for implementing the method of the present disclosure may be written in any combination of one or more programming languages. These program codes may be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, so that the program code, when executed by the processor or controller, enables the functions / operations specified in the flow chart and / or block diagram to be implemented. The program code may be executed entirely on the machine, partially on the machine, partially on the machine and partially on a remote machine as a stand-alone software package, or entirely on a remote machine or server.

[0149] In the context of the present disclosure, a machine-readable medium may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. A machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or equipment, or any suitable combination of the foregoing. A more specific example of a machine-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0150] As used in this disclosure, the terms "machine-readable medium" and "computer-readable medium" refer to any computer program product, apparatus, and / or device (e.g., disk, optical disk, memory, programmable logic device (PLD)) for providing machine instructions and / or data to a programmable processor, including a machine-readable medium that receives machine instructions as a machine-readable signal. The term "machine-readable signal" refers to any signal for providing machine instructions and / or data to a programmable processor.

[0151] To provide interaction with a user, the systems and techniques described herein can be implemented on a computer having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and pointing device (e.g., a mouse or trackball) through which the user can provide input to the computer. Other types of devices can also be used to provide interaction with the user; for example, the feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including acoustic input, voice input, or tactile input).

[0152] The systems and techniques described herein may be implemented in a computing system that includes back-end components (e.g., as a data server), or a computing system that includes middleware components (e.g., an application server), or a computing system that includes front-end components (e.g., a user computer with a graphical user interface or a web browser through which a user can interact with implementations of the systems and techniques described herein), or a computing system that includes any combination of such back-end components, middleware components, or front-end components. The components of the system may be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include: a local area network (LAN), a wide area network (WAN), and the Internet.

[0153] A computer system may include clients and servers. Clients and servers are generally remote from each other and usually interact through a communication network. The relationship of client and server is generated by computer programs running on respective computers and having a client-server relationship to each other.

[0154] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented by software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer programs or instructions. When the computer program or instruction is loaded and executed on a computer, the process or function described in the embodiment of the present disclosure is executed in whole or in part. The computer may be a general-purpose computer, a special-purpose computer, a computer network, a terminal, a user device or other programmable device. The computer program or instruction may be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium, for example, the computer program or instruction may be transmitted from one website site, computer, server or data center to another website site, computer, server or data center by wired or wireless means. The computer-readable storage medium may be any available medium that a computer can access or a data storage device such as a server, data center, etc. that integrates one or more available media. The available medium may be a magnetic medium, for example, a floppy disk, a hard disk, a tape; it may also be an optical medium, for example, a digital video disc (DVD); it may also be a semiconductor medium, for example, a solid state drive (SSD).

[0155] Although the present disclosure has been described in conjunction with specific features and embodiments thereof, it is apparent that various modifications and combinations may be made thereto without departing from the spirit and scope of the present disclosure. Accordingly, this specification and the drawings are merely exemplary illustrations of the present disclosure as defined by the appended claims, and are deemed to have covered any and all modifications, variations, combinations or equivalents within the scope of the present disclosure. Obviously, those skilled in the art may make various modifications and variations to the present disclosure without departing from the spirit and scope of the present disclosure. Thus, if these modifications and variations of the present disclosure fall within the scope of the claims of the present disclosure and their equivalents, the present disclosure is also intended to include these modifications and variations.

Claims

1. A method for analyzing engine performance at high altitude and low Reynolds number, characterized in that: include: Determining design point parameters of the target engine based on a zero-dimensional engine model of the target engine to be analyzed and design point information; Determining, within the design point parameters, a total inlet temperature and a total inlet pressure of a plurality of rotating components in the target engine based on a zero-dimensional engine model and non-design point information of the target engine, the plurality of rotating components including a compressor and a turbine; Determine the performance parameters of each rotating component based on the inlet total temperature, inlet total pressure, outlet static pressure and the three-dimensional simulation model associated with each rotating component, wherein the performance parameters include the flow rate and power of the rotating component; If it is determined based on the performance parameters of each rotating component that flow and power balance is achieved among the plurality of rotating components, then determining the total performance parameters of the target engine under high altitude and low Reynolds number conditions based on the zero-dimensional engine model and the performance parameters of the plurality of rotating components; Wherein, based on the performance parameters of each rotating component, determining whether the flow and power balance is achieved among the plurality of rotating components comprises: for each group of adjacent rotating components among the plurality of rotating components, determining the flow difference between the inlet flow of the first rotating component and the outlet flow of the second rotating component, and determining the ratio of the flow difference to the inlet flow of the first rotating component, and obtaining the flow balance parameter associated with each group of adjacent rotating components, wherein in each group of adjacent rotating components, the gas first flows into the second rotating component and then flows into the first rotating component; Determining a ratio of compressor power to mechanical efficiency to obtain a total compressor power, determining a difference between turbine power and the total compressor power to obtain a power difference, and determining a ratio of the power difference to the turbine power to obtain a power balance parameter; If the absolute value of the flow balance parameter associated with each group of adjacent rotating components is less than the first threshold, and the absolute value of the power balance parameter is less than the second threshold, it is determined that flow and power balance is achieved between the plurality of rotating components.

2. The method for analyzing engine performance at high altitude and low Reynolds number as claimed in claim 1, characterized in that: The method further comprises: If the flow and power imbalance among the multiple rotating components is determined based on the performance parameters of each rotating component, the outlet static pressure of each rotating component is iteratively updated based on the aerodynamic and thermal parameters associated with each rotating component and the outlet static pressure to obtain updated outlet static pressures of the multiple rotating components, and the updated performance parameters of each rotating component are determined based on the inlet total temperature, inlet total pressure, the updated outlet static pressure and the three-dimensional simulation model associated with each rotating component; The process of determining the updated performance parameters of each rotating component is repeated until flow and power balance is achieved among the multiple rotating components based on the updated performance parameters of each rotating component, and then the total performance parameters of the target engine under high altitude and low Reynolds number conditions are determined based on the zero-dimensional engine model and the updated performance parameters of each rotating component.

3. The method for analyzing engine performance at high altitude and low Reynolds number as claimed in claim 2, characterized in that: The rotating component includes an axial flow compressor, and the aerodynamic and thermal parameters associated with the axial flow compressor include the static temperature of the axial flow compressor, the inlet flow rate of the axial flow compressor, and the outlet flow rate of the axial flow compressor. The iterative updating of the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters associated with each rotating component and the outlet static pressure to obtain the updated outlet static pressures of the multiple rotating components includes: Determining a first correction value according to the static temperature of the axial compressor, the inlet flow rate of the axial compressor, the outlet flow rate of the axial compressor and a first target volume, wherein the first target volume is the volume at the outlet of the axial compressor in the cross-sectional characteristic information, and the cross-sectional characteristic information is used to characterize the design structure of the target engine; An updated outlet static pressure of the axial flow compressor is determined based on the outlet static pressure of the axial flow compressor and the first correction value.

4. The method for analyzing engine performance at high altitude and low Reynolds number as claimed in claim 2, characterized in that: The rotating component includes a turbine, and the aerodynamic and thermal parameters associated with the turbine include turbine static temperature, turbine outlet flow rate and nozzle inlet flow rate, The iterative updating of the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters associated with each rotating component and the outlet static pressure to obtain the updated outlet static pressures of the multiple rotating components includes: Determining a second correction value according to the turbine static temperature, the turbine outlet flow, the nozzle inlet flow, and a second target volume, wherein the second target volume is the volume at the turbine outlet position in the cross-sectional feature information; An updated outlet static pressure of the turbine is determined based on the outlet static pressure of the turbine and the second correction value.

5. The method for analyzing engine performance at high altitude and low Reynolds number as claimed in claim 2, characterized in that: The rotating component includes a turbine, and the aerodynamic and thermal parameters associated with the turbine include turbine power, axial compressor power and centrifugal compressor power. After iteratively updating the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters associated with each rotating component and the outlet static pressure to obtain updated outlet static pressures of the plurality of rotating components, the method further includes: Determining the updated inlet total temperature of the turbine according to the turbine power, the axial compressor power, the centrifugal compressor power and the mechanical efficiency; Determining the updated performance parameters of each rotating component according to the inlet total temperature, the inlet total pressure, the updated outlet static pressure and the three-dimensional simulation model associated with each rotating component includes: Updated performance parameters of the turbine are determined based on the updated inlet total temperature, the inlet total pressure, the updated outlet static pressure and the three-dimensional simulation model associated with the turbine.

6. The method for analyzing engine performance at high altitude and low Reynolds number as claimed in claim 2, characterized in that: The rotating component includes a centrifugal compressor, and the aerodynamic and thermal parameters of the centrifugal compressor include the total pressure at the centrifugal compressor outlet, The iterative updating of the outlet static pressure of each rotating component based on the aerodynamic and thermal parameters associated with each rotating component and the outlet static pressure to obtain the updated outlet static pressures of the multiple rotating components includes: Determine a third correction value according to the total pressure at the centrifugal compressor outlet, the Mach number of the current iteration cycle, the Mach number of the previous iteration cycle, and the outlet static pressure of the centrifugal compressor; An updated outlet static pressure of the centrifugal compressor is determined based on the outlet static pressure of the centrifugal compressor and the third correction value.

7. An engine performance analysis device at high altitude and low Reynolds number, characterized in that: include: A first determination module is configured to determine a design point parameter of the target engine based on a zero-dimensional engine model of the target engine to be analyzed and design point information; A second determination module is configured to determine, within the design point parameters, an inlet total temperature and an inlet total pressure of a plurality of rotating components in the target engine based on a zero-dimensional engine model and non-design point information of the target engine, the plurality of rotating components comprising a compressor and a turbine; A third determination module is configured to determine a performance parameter of each rotating component based on an inlet total temperature, an inlet total pressure, an outlet static pressure and a three-dimensional simulation model associated with each rotating component, wherein the performance parameter includes a flow rate and a power of the rotating component; a fourth determination module configured to determine, if it is determined based on the performance parameters of each rotating component that a flow and power balance is achieved among the plurality of rotating components, an overall performance parameter of the target engine under high altitude and low Reynolds number conditions according to the zero-dimensional engine model and the performance parameters of the plurality of rotating components; a determination module configured to determine, for each group of adjacent rotating components among the plurality of rotating components, a flow difference between an inlet flow of a first rotating component and an outlet flow of a second rotating component, and determine a ratio of the flow difference to an inlet flow of the first rotating component, to obtain a flow balance parameter associated with each group of adjacent rotating components, wherein, in each group of adjacent rotating components, gas first flows into the second rotating component and then flows into the first rotating component; Determining a ratio of compressor power to mechanical efficiency to obtain a total compressor power, determining a difference between turbine power and the total compressor power to obtain a power difference, and determining a ratio of the power difference to the turbine power to obtain a power balance parameter; If the absolute value of the flow balance parameter associated with each group of adjacent rotating components is less than the first threshold, and the absolute value of the power balance parameter is less than the second threshold, it is determined that flow and power balance is achieved between the plurality of rotating components.

8. An electronic device, characterized in that: include: processor; as well as Memory for storing programs, The program includes instructions, which, when executed by the processor, cause the processor to perform the method according to any one of claims 1 to 6.

9. A non-transitory computer-readable storage medium storing computer instructions, characterized in that: The computer instructions are used to cause the computer to execute the method according to any one of claims 1 to 6.

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