Joint simulation method and system for three-dimensional performance of aircraft engine core under whole-machine matching constraints

Abstract

A method and system for joint simulation of the three-dimensional performance of an aero-engine core machine under the constraint of whole-machine matching, and relates to the field of aero-engine simulation. The problem that the existing simulation method is difficult to converge in overall modeling is solved. The method includes: determining the initial values ​​of the boundary conditions of the compressor, combustion chamber and turbine according to the overall matching value; calculating the deviation of the solution quantity of adjacent components, and updating the back pressure of the compressor outlet and the combustion chamber outlet of the next iteration according to the deviation; updating the boundary conditions of the compressor outlet and the combustion chamber outlet according to the relaxation iteration method; calculating the compressor outlet flow, extracting the total temperature of the compressor outlet flow and transferring it to the combustion chamber inlet, extracting the total pressure and total temperature of the outlet and transferring it to the turbine inlet, calculating the deviation of the solution quantity of adjacent components, and judging whether the deviation meets the given value. If so, the iteration ends, otherwise, the boundary conditions of the compressor outlet and the combustion chamber outlet continue to be updated until the deviation meets the given value and the simulation is completed. The present invention is used for joint simulation of the three-dimensional performance of engine core machines / whole machines of different configurations.

Description

Technical Field

[0001] The invention relates to the field of aero-engine simulation, and in particular to a method for jointly simulating the three-dimensional performance of an aero-engine core machine under the constraint of whole-machine matching. Background Art

[0002] As the computing power of computer clusters continues to improve, three-dimensional numerical simulation methods are widely used in the research of aerodynamic design, optimization and numerical simulation algorithms of aircraft engine components. In contrast, there is not much research work on the three-dimensional numerical simulation of the whole machine. The numerical simulation of a single engine component has the characteristics of unrealistic boundary conditions, loose matching relationship between adjacent components, and inability to reflect the multi-component and multi-disciplinary flow characteristics inside the whole machine. Therefore, single component calculation needs to be combined with technologies such as numerical transfer to realize the numerical simulation of the whole engine. With the development of computer clusters and computational fluid dynamics, the numerical simulation of large-scale complex regional flow fields with multi-field coupling has been realized. By performing whole machine coupling calculations, the interaction between different components can be solved, the flow field details of the engine under whole machine matching can be understood, and the whole machine test design can be assisted to reduce the test risk.

[0003] The different flow characteristics of various aircraft engine components determine that the three-dimensional calculation models and algorithms used are not exactly the same. Impeller machinery such as compressors and turbines are compressible flows, while combustion chambers are usually incompressible flows. Therefore, numerical calculation methods suitable for the flow characteristics of different components are selected to describe the flow conditions of different components. However, one of the existing simulation methods is to calculate through the overall modeling of the aircraft engine, model the compressor, combustion chamber, and turbine together, and then use CFX for calculation, which makes it difficult for the simulation method to converge and the amount of calculation increases significantly. The other method is to use precice for coupled calculations and perform boundary transfer during calculations. Since the boundary transfer is too direct and there is no algorithm processing, it is difficult to converge. Summary of the invention

[0004] Aiming at the problems that the existing simulation methods are difficult to converge due to overall modeling, the amount of calculation increases greatly, and the coupling calculation using precice is difficult to converge without any algorithm processing, the present invention proposes a three-dimensional performance joint simulation method of an aero-engine core machine under the constraint of whole machine matching, and the method comprises:

[0005] S1: Determine the initial values ​​of the compressor, combustion chamber and turbine boundary conditions based on the overall matching value;

[0006] S2: Calculate the deviation of the solution quantity of adjacent components, and update the back pressure of the compressor outlet and the combustion chamber outlet of the next iteration according to the deviation;

[0007] S3: Update the compressor outlet and combustion chamber outlet boundary conditions according to the relaxation iteration method;

[0008] S4: Calculate the compressor outlet flow rate. After the calculation is completed, extract the total temperature of the compressor outlet flow rate and transfer it to the combustion chamber inlet. After the combustion chamber calculation is completed, extract the total outlet pressure and total temperature and transfer them to the turbine inlet. After the turbine calculation is completed, calculate the deviation of the solution of adjacent components to determine whether the deviation meets the given value. If so, the iteration ends. If not, continue to update the boundary conditions of the compressor outlet and combustion chamber outlet according to the relaxation iteration method until the deviation meets the given value and the simulation is completed.

[0009] Furthermore, a preferred embodiment is proposed, wherein S1 comprises:

[0010]

[0011] in, is the total pressure at the compressor outlet of the nth iteration, is the total pressure at the compressor inlet of the nth iteration, is the total temperature of the compressor inlet at the nth iteration, is the mass flow rate at the combustion chamber outlet of the nth iteration, is the mass flow rate at the combustion chamber inlet of the nth iteration, is the fuel mass flow rate added, is the turbine inlet mass flow rate at the nth iteration, is the total pressure at the turbine inlet of the nth iteration, is the total temperature of turbine inlet at the nth iteration, P turb,out,n is the turbine outlet static pressure at the nth iteration.

[0012] Furthermore, a preferred method is proposed, wherein the calculation of the deviation of the solution amount of adjacent components in step S2 includes:

[0013]

[0014] Among them, P comp,out,n+1 is the static pressure at the compressor outlet of the n+1th iteration, ε 1 is the total pressure deviation between the compressor outlet and the combustion chamber inlet, P comb,out,n+1 is the static pressure at the combustion chamber outlet at the n+1th iteration, ε 2 is the mass flow rate deviation between the combustion chamber outlet and the turbine inlet.

[0015] Furthermore, a preferred method is proposed, wherein step S3 comprises:

[0016] The convergence and convergence speed of the iteration are controlled by the relaxation factor:

[0017]

[0018] in, is the compressor outlet total pressure updated in the n+1th iteration, α 1To control the relaxation factor of the deviation of the total pressure solution at the compressor outlet and the combustion chamber inlet, is the updated value of the mass flow rate at the combustion chamber outlet for the n+1th iteration, α 2 Relaxation factors for solving quantity deviations to control combustion chamber outlet and turbine inlet flow rates;

[0019] Get the target values ​​for updating the compressor outlet and combustion chamber outlet solution at the n+1th iteration step.

[0020] Furthermore, a preferred embodiment is proposed, wherein step S3 further comprises converting the target total pressure and flow rate into static pressure:

[0021]

[0022] in, is the mass flow rate, K is the coefficient constant, P * is the total pressure, T * is the total temperature, Ma is the Mach number, P is the static pressure, and k is the adiabatic index.

[0023] Based on the same inventive concept, the present invention also proposes a three-dimensional performance joint simulation system for an aircraft engine core machine under the whole machine matching constraint, the system comprising:

[0024] An initial value determination unit, used to determine the initial values ​​of the compressor, combustion chamber and turbine boundary conditions according to the overall matching value;

[0025] An updating unit, used to calculate the deviation of the solution quantity of adjacent components, and update the back pressure of the compressor outlet and the combustion chamber outlet in the next iteration step according to the deviation;

[0026] A boundary condition iteration unit, used for updating the boundary conditions of the compressor outlet and the combustion chamber outlet according to a relaxation iteration method;

[0027] The simulation unit is used to calculate the compressor outlet flow rate. After the calculation is completed, the total temperature of the compressor outlet flow rate is extracted and transferred to the combustion chamber inlet. After the combustion chamber calculation is completed, the total outlet pressure and total temperature are extracted and transferred to the turbine inlet. After the turbine calculation is completed, the deviation of the solution of adjacent components is calculated to determine whether the deviation meets the given value. If so, the iteration ends. If not, the boundary conditions of the compressor outlet and the combustion chamber outlet continue to be updated according to the relaxation iteration method until the deviation meets the given value and the simulation is completed.

[0028] Based on the same inventive concept, the present invention provides a computer device, including a memory and a processor, wherein the memory stores a computer program. When the processor runs the computer program stored in the memory, the processor executes the method for joint simulation of the three-dimensional performance of an aircraft engine core machine under the whole machine matching constraints described in any one of the above items.

[0029] Based on the same inventive concept, the present invention provides a computer-readable storage medium, characterized in that a computer program is stored on the computer-readable storage medium, and when the computer program is run by a processor, the steps of the method for joint simulation of the three-dimensional performance of an aircraft engine core machine under the whole machine matching constraints as described in any of the above items are executed.

[0030] The present invention is beneficial in that:

[0031] (1) It has a wide range of applications and can be used for the three-dimensional performance joint simulation of engine cores / whole machines with different configurations. It only needs to replace the component models, or add the components of the fan, low-pressure compressor, and low-pressure turbine, and rewrite the relaxation iterative method. In addition, different types of domestic or commercial software can be used for overall performance simulation and component three-dimensional simulation. The data input and output rules used by the software need to be modified into the relaxation iterative method.

[0032] (2) Considering the mutual influence between components, compared with the single-component three-dimensional simulation, this method takes into account the flow continuity between the upstream and downstream adjacent components through the bidirectional transmission of data, making it closer to the actual flow situation.

[0033] (3) It has good convergence. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is a flow chart of the method for joint simulation of three-dimensional performance of aero-engine core under the whole-machine matching constraint described in the first embodiment;

[0035] Figure 2 This is a schematic diagram of a core machine simulation framework for the whole machine matching constraints described in Implementation 11;

[0036] Figure 3 This is a schematic diagram for describing the three-dimensional joint simulation problem according to the eleventh embodiment, wherein: Figure 3 (a) is a schematic diagram of the calculation of a single component of the core engine. Figure 3 (b) is a schematic diagram of the core machine serial simulation;

[0037] Figure 4 A schematic diagram of the total parameter flow of the three-dimensional joint simulation according to the eleventh embodiment;

[0038] Figure 5 for Figure 2 Schematic diagram of the zero-dimensional overall simulation. DETAILED DESCRIPTION

[0039] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may 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 prevent unnecessary details from obstructing the description of the present application.

[0040] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0041] It should also be understood that the terms used in this application specification are only for the purpose of describing specific embodiments and are not intended to limit the application. As used in this application specification and the appended claims, the singular forms "a", "an" and "the" are intended to include plural forms unless the context clearly indicates otherwise.

[0042] The specific implementation mode of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention.

[0043] Implementation method 1, see Figure 1 The method for joint simulation of three-dimensional performance of aero-engine core machine under the whole machine matching constraint described in this embodiment includes:

[0044] S1: Determine the initial values ​​of the compressor, combustion chamber and turbine boundary conditions based on the overall matching value;

[0045] S2: Calculate the deviation of the solution quantity of adjacent components, and update the back pressure of the compressor outlet and the combustion chamber outlet of the next iteration according to the deviation;

[0046] S3: Update the compressor outlet and combustion chamber outlet boundary conditions according to the relaxation iteration method;

[0047] S4: Calculate the compressor outlet flow rate. After the calculation is completed, extract the total temperature of the compressor outlet flow rate and transfer it to the combustion chamber inlet. After the combustion chamber calculation is completed, extract the total outlet pressure and total temperature and transfer them to the turbine inlet. After the turbine calculation is completed, calculate the deviation of the solution of adjacent components to determine whether the deviation meets the given value. If so, the iteration ends. If not, continue to update the boundary conditions of the compressor outlet and combustion chamber outlet according to the relaxation iteration method until the deviation meets the given value and the simulation is completed.

[0048] In this embodiment, the initial values ​​of the boundary conditions of the compressor, combustion chamber and turbine are determined according to the matching value of the whole machine, which helps to improve the accuracy of the initial solution and thus accelerate the convergence process. By calculating the deviation of the solution amount of adjacent components, the system can dynamically update the back pressure of the compressor outlet and the combustion chamber outlet according to the deviation size. This feedback mechanism helps to optimize the matching and balance of the flow field and reduce unnecessary consumption of computing resources. The boundary conditions of the compressor outlet and the combustion chamber outlet are updated using the relaxation iteration method. This method can gradually adjust the boundary conditions in each iteration to make it closer to the real physical flow state, thereby improving convergence and stability. After the calculation of each component is completed, the flow field parameters are effectively transferred by transferring the total temperature of the compressor outlet flow to the combustion chamber inlet and the total pressure and temperature of the combustion chamber outlet to the turbine inlet, which is conducive to maintaining the consistency of the flow field between the components and reducing unnecessary numerical coupling errors. By judging whether the deviation of the solution amount of adjacent components meets the given value to control the end of the iteration, this adaptive convergence judgment mechanism can effectively reduce the instability and calculation amount in the calculation process while ensuring the accuracy of the results.

[0049] The method described in this embodiment effectively overcomes various difficulties in existing simulation methods by introducing whole-machine matching constraints, iterative update mechanisms, and optimized boundary condition processing methods. Compared with traditional overall modeling or simple boundary transfer, this method has significant progress in improving simulation efficiency and accuracy:

[0050] By dynamically adjusting boundary conditions and accurately matching the flow field, unnecessary calculations and iterations are reduced;

[0051] The introduction of relaxation iteration method and dynamic update mechanism effectively improves the convergence speed and stability;

[0052] Through the effective transmission of flow and thermal parameters, the consistency and accuracy of the flow field between components are guaranteed.

[0053] Embodiment 2: This embodiment further limits the method for joint simulation of three-dimensional performance of aero-engine core under the whole-machine matching constraint described in Embodiment 1, and S1 includes:

[0054]

[0055]

[0056] in, is the total pressure at the compressor outlet of the nth iteration, is the total pressure at the compressor inlet of the nth iteration, is the total temperature of the compressor inlet at the nth iteration, is the mass flow rate at the combustion chamber outlet of the nth iteration, is the mass flow rate at the combustion chamber inlet of the nth iteration, is the fuel mass flow rate added, is the turbine inlet mass flow rate at the nth iteration, is the total pressure at the turbine inlet of the nth iteration, is the total temperature of turbine inlet at the nth iteration, P turb,out,n is the turbine outlet static pressure at the nth iteration.

[0057] This embodiment is explained in conjunction with the first embodiment. This embodiment uses the overall matching value to determine the initial values ​​of the boundary conditions of the compressor, combustion chamber and turbine. These initial values ​​are based on the parameters such as the compressor outlet total pressure, compressor inlet total pressure, compressor inlet total temperature, etc. of the nth iteration. In this way, it can be ensured that the initial boundary conditions are closer to the actual flow state, thereby accelerating the convergence speed and improving the accuracy of the simulation.

[0058] According to the deviation of the solution of adjacent components, the back pressure of the compressor outlet and the combustion chamber outlet of the next iteration step is dynamically adjusted. This iterative update mechanism can respond to the changes of flow field parameters in real time, effectively control and optimize the matching of the flow field, avoid unnecessary large adjustments, and improve the stability and convergence of the algorithm.

[0059] After the calculation of each component is completed, the key parameters of the flow field (such as total pressure, total temperature, etc.) are effectively transferred to the next component using parameter transfer mechanisms such as fuel mass flow, thereby ensuring the consistency and accuracy of the overall flow field. This optimized coupling method can reduce the accumulation of numerical errors and improve the credibility of the overall simulation results.

[0060] Implementation method 3: This implementation method further limits the method for joint simulation of three-dimensional performance of aero-engine core machine under the whole machine matching constraint described in implementation method 1. The calculation of the deviation of the solution amount of adjacent components in step S2 includes:

[0061]

[0062] Among them, P comp,out,n+1 is the static pressure at the compressor outlet of the n+1th iteration, ε 1 is the total pressure deviation between the compressor outlet and the combustion chamber inlet, P comb,out,n+1 is the static pressure at the combustion chamber outlet at the n+1th iteration, ε 2is the mass flow rate deviation between the combustion chamber outlet and the turbine inlet.

[0063] Based on the nth iteration, by calculating the total pressure deviation between the compressor outlet and the combustion chamber inlet and the mass flow deviation between the combustion chamber outlet and the turbine inlet, the flow field matching between adjacent components can be accurately captured. This precise deviation calculation helps to more accurately determine the boundary conditions of the next iteration step, thereby improving the accuracy and credibility of the overall simulation.

[0064] By calculating and updating the compressor outlet static pressure and the combustion chamber outlet static pressure in real time, this method can achieve dynamic flow field adjustment and optimization. This dynamic adjustment is based on the quantity deviation of the current iteration step, which can effectively adjust the boundary conditions of the next step, making the simulation process more stable and efficient.

[0065] Embodiment 4: This embodiment further limits the method for joint simulation of three-dimensional performance of aero-engine core machine under the whole machine matching constraint described in embodiment 1, and step S3 includes:

[0066] The convergence and convergence speed of the iteration are controlled by the relaxation factor:

[0067]

[0068] in, is the compressor outlet total pressure updated in the n+1th iteration, α 1 To control the relaxation factor of the deviation of the total pressure solution at the compressor outlet and the combustion chamber inlet, is the updated value of the mass flow rate at the combustion chamber outlet for the n+1th iteration, α 2 Relaxation factors for solving quantity deviations to control combustion chamber outlet and turbine inlet flow rates;

[0069] Get the target values ​​for updating the compressor outlet and combustion chamber outlet solution at the n+1th iteration step.

[0070] The present embodiment uses a relaxation factor to adjust the target values ​​of the compressor outlet total pressure and the combustor outlet mass flow rate updated in each iteration. This control capability can help ensure that the system can more accurately achieve the desired performance indicators during the iteration process, thereby improving the precision and accuracy of the overall simulation.

[0071] Furthermore, adjusting the relaxation factor can also affect the convergence speed of the iteration. By reasonably selecting and adjusting the relaxation factor, the system can reach a stable solution faster, thereby saving computing resources and time costs. Especially in complex simulation processes, optimizing the convergence speed is crucial to improving simulation efficiency.

[0072] Stability during the iteration process is the key to any simulation method. By adjusting the relaxation factor, the stability of the solution can be effectively controlled to avoid too fast changes or unstable oscillations, thereby ensuring that the system remains stable and reliable during the solution process.

[0073] Embodiment 5: This embodiment further limits the method for joint simulation of three-dimensional performance of aero-engine core under the whole-machine matching constraint described in Embodiment 1. Step S3 further includes converting the target total pressure and flow rate into static pressure:

[0074]

[0075] in, is the mass flow rate, K is the coefficient constant, P * is the total pressure, T * is the total temperature, Ma is the Mach number, P is the static pressure, and k is the adiabatic index.

[0076] Since the boundary conditions at the target values ​​of the compressor outlet and combustion chamber outlet solution update in the n+1th iteration step are usually in the form of static pressure, the target total pressure and flow rate need to be converted into static pressure. Converting the target total pressure and flow rate into static pressure helps to maintain the consistency and accuracy of physical quantities during the simulation process. Static pressure is an important physical quantity in the flow field and can directly reflect the static pressure state of the fluid. Therefore, converting the target total pressure and flow rate into static pressure uniformly helps to ensure that the simulation results are physically reasonable and explainable.

[0077] Furthermore, in numerical calculations, static pressure is usually easier to handle and calculate than total pressure. By converting the target total pressure and flow rate into static pressure, the solution process can be simplified, the complexity and time consumption of numerical calculations can be reduced, and the efficiency and speed of simulation can be improved.

[0078] Embodiment 6: The three-dimensional performance joint simulation system of an aircraft engine core machine under the whole machine matching constraint described in this embodiment comprises:

[0079] An initial value determination unit, used to determine the initial values ​​of the compressor, combustion chamber and turbine boundary conditions according to the overall matching value;

[0080] An updating unit, used to calculate the deviation of the solution quantity of adjacent components, and update the back pressure of the compressor outlet and the combustion chamber outlet in the next iteration step according to the deviation;

[0081] A boundary condition iteration unit, used for updating the boundary conditions of the compressor outlet and the combustion chamber outlet according to a relaxation iteration method;

[0082] The simulation unit is used to calculate the compressor outlet flow rate. After the calculation is completed, the total temperature of the compressor outlet flow rate is extracted and transferred to the combustion chamber inlet. After the combustion chamber calculation is completed, the total outlet pressure and total temperature are extracted and transferred to the turbine inlet. After the turbine calculation is completed, the deviation of the solution of adjacent components is calculated to determine whether the deviation meets the given value. If so, the iteration ends. If not, the boundary conditions of the compressor outlet and the combustion chamber outlet continue to be updated according to the relaxation iteration method until the deviation meets the given value and the simulation is completed.

[0083] Embodiment 7. A computer device described in this embodiment includes a memory and a processor, wherein the memory stores a computer program. When the processor runs the computer program stored in the memory, the processor executes the method for joint simulation of the three-dimensional performance of an aircraft engine core machine under the whole machine matching constraints described in any one of claims 1-5.

[0084] Embodiment 8. A computer-readable storage medium described in this embodiment stores a computer program, and when the computer program is executed by a processor, the steps of the method for joint simulation of three-dimensional performance of an aircraft engine core machine under the whole machine matching constraint as described in any one of embodiments 1 to 5.

[0085] Implementation method 9: See Figures 2 to 5 This embodiment is described. This embodiment provides a specific example of the method for joint simulation of three-dimensional performance of aircraft engine core under the whole machine matching constraint described in the first embodiment, and is also used to explain the second to sixth embodiments. Specifically:

[0086] like Figure 2 and Figure 5 As shown, the simulation method described in this embodiment is based on the currently more mature domestic overall performance simulation software and domestic Taihang CAE three-dimensional numerical simulation software, and establishes a joint simulation architecture including the overall performance program and the component three-dimensional simulation program. A relaxation iterative method considering aerodynamic and thermodynamic conservation is adopted to realize the three-dimensional performance joint simulation of the aircraft engine core machine considering the mutual influence between components under the constraint of whole machine matching.

[0087] The three-dimensional joint simulation of the core engine simulates a certain steady-state common working point under the overall matching of the aircraft engine. At present, there are relatively mature simulation methods for each component of the core engine, and good accuracy and robustness can be guaranteed when simulating each component separately. However, since each component is relatively independent at the level of the numerical model after segmentation, it is undoubtedly necessary to repeatedly adjust the additional numerical boundaries if you want to simulate a certain common working point, and this adjustment method is often decoupled. In summary, the problem to be solved by the three-dimensional joint simulation is how to give full play to the accuracy and robustness advantages of single-component simulation when each component is relatively independent, and at the same time use the common working equation of the whole machine matching to constrain the simulation of each component, so that it can simulate a certain steady-state common working point under the test conditions / overall matching as much as possible. To achieve the matching of each component under the three-dimensional joint simulation, two main problems need to be solved: ① How to ensure power balance; ② How to achieve the conservation of aerodynamic parameters.

[0088] For question ①, in the test process / overall matching, the fuel supply to the combustion chamber is adjusted to stabilize each component at a certain operating speed, thereby obtaining a steady-state common operating point under the fuel supply. Figure 3 It can be seen that the relationship between the working speed and the oil supply is constrained by the common working equation of each component. From the perspective of the equation, the working speed is the solution value of the common working equation with a certain oil supply as input. For the serial co-simulation of components, the oil supply and the working speed should be used as the input of the simulation setting at the same time, that is, the relationship between the two is adaptive when given artificially. Therefore, for the three-dimensional co-simulation of the core engine, the oil supply and the working speed need to be used as invariants or iterations at the same time. Since the power balance equation itself is difficult to be used as a constraint condition for the serial co-simulation of components, if both are used as iterations, the robustness of the algorithm will undoubtedly be greatly reduced, and it is difficult to control the direction of algorithm convergence. Therefore, for the three-dimensional co-simulation, the necessary condition to ensure power balance is that the parameters of the simulation input oil supply and working speed are consistent with the common working equation. Based on the above considerations, solving the common working point problem of the core engine under a certain oil supply through the three-dimensional co-simulation of components is converted into iterating the boundary conditions of each component under a given oil supply and working speed to satisfy ① the total parameter error of the physical interface of each component.

[0089] In view of the above situation, this embodiment proposes a three-dimensional performance joint simulation method for an aircraft engine core machine under the constraint of whole machine matching, and the process is as follows: first, the initial value of the boundary condition of each component in the first step is determined according to the overall matching value, and the deviation of the solution quantity of adjacent components is calculated after the calculation is completed, and the back pressure of the compressor outlet and the combustion chamber outlet of the next iteration step is updated according to the deviation. In the nth step, the compressor is first calculated, and the total temperature of the compressor outlet flow is extracted and transferred to the combustion chamber inlet after the calculation is completed. After the combustion chamber calculation is completed, the outlet total pressure and total temperature are extracted and transferred to the turbine inlet. After the turbine calculation is completed, the deviation of the solution quantity of adjacent components is calculated to determine whether the deviation meets the given value. If so, the iteration ends. If not, the boundary conditions of the compressor outlet and the combustion chamber outlet continue to be updated according to the relaxation iteration method until the deviation meets the given value.

[0090] For the numerical simulation of core engine components, different boundary condition combinations are often required to solve the problem due to the different physical characteristics of different components. The compressor usually uses the inlet total pressure and total temperature, and the outlet back pressure; the combustion chamber usually uses the inlet flow total temperature and the outlet back pressure; the turbine usually uses the inlet total pressure and total temperature, and the outlet back pressure. Under the above boundary condition combination, the most direct way to ensure aerodynamic thermodynamic conservation is to extract the total parameters of the upstream component outlet and transfer them to the total parameter combination required for the downstream component inlet, that is, in each round of calculation, the total flow temperature at the compressor outlet is transferred to the combustion chamber inlet, and the total pressure and total temperature at the combustion chamber outlet is transferred to the turbine inlet.

[0091] In addition to the above parameters, the solution quantities of adjacent components do not necessarily satisfy the continuity conditions. Figure 4 Under the boundary condition combination shown, the solution quantities on the boundaries of each component are the compressor outlet total pressure, the combustion chamber inlet total pressure, and the turbine inlet flow rate. The relationship between the solution quantity and the boundary conditions is shown in formula (1-3).

[0092]

[0093] From the above analysis, it can be seen that the transfer quantities that meet the continuity condition of the three-dimensional joint simulation are the total temperature of the compressor outlet and the combustion chamber inlet flow rate and the total pressure and temperature of the combustion chamber outlet and the turbine inlet. The solution quantities that do not meet the continuity condition are the total pressure of the compressor outlet and the combustion chamber inlet and the flow rate of the combustion chamber outlet and the turbine inlet. In the iterative solution, the deviation of these solution quantities is directly related to the component outlet conditions, that is, the iteration quantity. Therefore, the core of serial collaborative simulation is to seek an iteration mechanism under which the change of the iteration quantity can affect the direction and size of the deviation between the solution quantities and ultimately make the deviation less than the given value, as shown in formula (5-6).

[0094]

[0095] In the above formula, mechanism g is the iterative update strategy to be sought. Mathematically, mechanism g can be analyzed in many ways, such as arithmetic mean or harmonic mean based on deviation. The difference between various methods lies in the different control of the convergence and convergence speed of the iteration. In order to use a unified parameter to control the convergence and convergence speed of the iteration at the same time, this study developed a more universal relaxation iteration method, the connotation of which is to relax the deviation of the solution of the previous iteration step to set the target value of the solution of the next iteration step, and comprehensively control the convergence and convergence speed of the iteration through the size of the relaxation factor. The specific expression is shown in formula (7-8).

[0096]

[0097] In the above formula, α 1 is the relaxation factor for controlling the deviation of the total pressure solution at the compressor outlet and the combustion chamber inlet, α 2 It is the relaxation factor for controlling the deviation of the solution of the combustion chamber outlet and turbine inlet flow, and its value is between 0 and 1. It should be noted that the subscript "target" in formula (7-8) means the expected value of the n+1th iteration step, which must have a deviation from the actual solution value of the corresponding quantity of the n+1th step. This deviation actually determines ε 1 , ε 2 size.

[0098] Formula (7-8) determines the target value of the updated solution at the compressor outlet and the combustion chamber outlet in the n+1th iteration step. Since the boundary conditions at these two places in numerical calculations are usually in the form of static pressure, it is necessary to convert the target total pressure and flow rate into static pressure. The conversion mainly uses the aerodynamic function of formula (9-10).

[0099]

[0100] For the compressor outlet, the static pressure can be obtained by knowing the total pressure and Mach number through equation (10), and the Mach number can be obtained by inversely solving the q function through equation (9). At this time, the outlet flow rate and total temperature are also required. The outlet flow rate and total temperature can be obtained in two ways: the first way is to obtain it based on the total temperature of the compressor outlet flow at the nth iteration step; the second way is to obtain it based on the estimated total temperature of the compressor outlet flow at the matching point. The first way will introduce two additional variables related to the cycle, which may cause iterative divergence when the component characteristics are close to the unstable boundary. The second way is more recommended, which can ensure that the flow rate and total temperature required to update the static pressure do not change with the iteration process, and can enhance the convergence of the iteration. The combustion chamber outlet is similar to the compressor outlet, that is, the total pressure and total temperature are additionally obtained under the condition of known target flow to solve the static pressure, which will not be repeated here.

[0101] The proposed implementation mode has a wide range of applications and can be used for the three-dimensional performance joint simulation of engine core machines / whole machines with different configurations. It only needs to replace the component models, and the components of the fan, low-pressure compressor, and low-pressure turbine can also be added, and the relaxation iterative method can be rewritten. In addition, different types of domestic or commercial software can be used for overall performance simulation and component three-dimensional simulation, and the data input and output rules used by the software need to be modified into the relaxation iterative method.

[0102] Considering the mutual influence between components, compared with the single-component 3D simulation, this method considers the flow continuity between the upstream and downstream adjacent components through the bidirectional transmission of data, making it closer to the actual flow situation. And it has better convergence.

[0103] Although preferred embodiments of the present disclosure have been described, those skilled in the art may make additional changes and modifications to these embodiments once they are aware of the basic creative concepts. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present disclosure. Obviously, those skilled in the art may make various changes and modifications 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.

[0104] Those skilled in the art will appreciate that the embodiments of the present disclosure may be provided as methods, systems or computer program products. Therefore, the present disclosure may take the form of a complete hardware embodiment, a complete software embodiment or an embodiment combining software and hardware. Moreover, the present disclosure may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0105] The present disclosure is described with reference to flowcharts and / or block diagrams of methods, devices (systems) and computer program products according to embodiments of the present disclosure. It should be understood that each process and / or block in the flowchart and / or block diagram and the combination of processes and / or blocks in the flowchart and / or block diagram can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1These computer program instructions can also be stored in a computer-readable memory that can guide a computer or other programmable data processing device to work in a specific way, so that the instructions stored in the computer-readable memory produce a product including an instruction device, which implements the functions specified in the process. Figure 1 A process or multiple processes and / or boxes Figure 1 These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to produce a computer-implemented process, so that the instructions executed on the computer or other programmable device provide for implementing the process in the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0106] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present disclosure rather than to limit its protection scope. Although the present disclosure has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that after reading the present disclosure, those skilled in the art can still make various changes, modifications or equivalent substitutions to the specific implementation methods of the invention, but these changes, modifications or equivalent substitutions are all within the protection scope of the disclosed claims to be approved.

Claims

1. A three-dimensional performance joint simulation method for aero-engine core machine under the constraint of whole machine matching, characterized in that: The method comprises: S1: Determine the initial values ​​of the compressor, combustion chamber and turbine boundary conditions based on the overall matching value; S2: Calculate the deviation of the solution quantity of adjacent components, and update the back pressure of the compressor outlet and the combustion chamber outlet of the next iteration according to the deviation; S3: Update the compressor outlet and combustion chamber outlet boundary conditions according to the relaxation iteration method; S4: Calculate the compressor outlet flow rate, extract the total temperature of the compressor outlet flow rate after the calculation is completed and transfer it to the combustion chamber inlet, extract the total pressure and temperature of the combustion chamber outlet after the calculation is completed and transfer it to the turbine inlet, calculate the deviation of the solution of adjacent components after the turbine calculation is completed, and judge whether the deviation meets the given value. If so, the iteration ends, otherwise, continue to update the boundary conditions of the compressor outlet and the combustion chamber outlet according to the relaxation iteration method until the deviation meets the given value and the simulation is completed; The S1 includes: in, is the total pressure at the compressor outlet of the nth iteration, is the total pressure at the compressor inlet of the nth iteration, is the total temperature of the compressor inlet at the nth iteration, is the mass flow rate at the combustion chamber outlet of the nth iteration, is the mass flow rate at the combustion chamber inlet of the nth iteration, is the fuel mass flow rate added, is the turbine inlet mass flow rate at the nth iteration, is the total pressure at the turbine inlet of the nth iteration, is the total temperature of turbine inlet at the nth iteration, P turb,out,n is the turbine outlet static pressure at the nth iteration, Calculating the deviation of the solution amount of adjacent components in step S2 includes: Among them, P comp,out,n+1 is the static pressure at the compressor outlet of the n+1th iteration, ε1 is the deviation of the total pressure between the compressor outlet and the combustion chamber inlet, P comb,out,n+1 is the combustion chamber outlet static pressure at the n+1th iteration, ε2 is the deviation of the mass flow rate between the combustion chamber outlet and the turbine inlet; The step S3 comprises: The convergence and convergence speed of the iteration are controlled by the relaxation factor: in, is the compressor outlet total pressure value updated in the n+1th iteration, α1 is the relaxation factor for controlling the deviation of the total pressure solution at the compressor outlet and the combustion chamber inlet, is the updated value of the mass flow rate at the combustion chamber outlet in the n+1th iteration, and α2 is the relaxation factor for controlling the deviation of the solution of the combustion chamber outlet and the turbine inlet flow rate; Get the target values ​​for updating the compressor outlet and combustion chamber outlet solution at the n+1th iteration step.

2. A three-dimensional performance joint simulation system for aero-engine core engine under the constraints of complete engine matching, characterized in that: The system comprises: An initial value determination unit is used to determine the initial values ​​of the compressor, combustion chamber and turbine boundary conditions according to the overall matching value; including: in, is the total pressure at the compressor outlet of the nth iteration, is the total pressure at the compressor inlet of the nth iteration, is the total temperature of the compressor inlet at the nth iteration, is the mass flow rate at the combustion chamber outlet of the nth iteration, is the mass flow rate at the combustion chamber inlet of the nth iteration, is the fuel mass flow rate added, is the turbine inlet mass flow rate at the nth iteration, is the total pressure at the turbine inlet of the nth iteration, is the total temperature of turbine inlet at the nth iteration, P turb,out,n is the turbine outlet static pressure at the nth iteration; The updating unit is used to calculate the deviation of the solution quantity of adjacent components and update the back pressure of the compressor outlet and the combustion chamber outlet in the next iteration according to the deviation; the calculation of the deviation of the solution quantity of adjacent components includes: Among them, P comp,out,n+1 is the static pressure at the compressor outlet of the n+1th iteration, ε1 is the deviation of the total pressure between the compressor outlet and the combustion chamber inlet, P comb,out,n+1 is the combustion chamber outlet static pressure at the n+1th iteration, ε2 is the deviation of the mass flow rate between the combustion chamber outlet and the turbine inlet; Boundary condition iteration unit, used to update the compressor outlet and combustion chamber outlet boundary conditions according to the relaxation iteration method; including: The convergence and convergence speed of the iteration are controlled by the relaxation factor: in, is the compressor outlet total pressure value updated in the n+1th iteration, α1 is the relaxation factor for controlling the deviation of the total pressure solution at the compressor outlet and the combustion chamber inlet, is the updated value of the mass flow rate at the combustion chamber outlet in the n+1th iteration, and α2 is the relaxation factor for controlling the deviation of the solution of the combustion chamber outlet and the turbine inlet flow rate; Obtain the target values ​​for updating the solution quantities of the compressor outlet and the combustion chamber outlet in the n+1th iteration step; The simulation unit is used to calculate the compressor outlet flow rate. After the calculation is completed, the total temperature of the compressor outlet flow rate is extracted and transferred to the combustion chamber inlet. After the combustion chamber calculation is completed, the total outlet pressure and total temperature are extracted and transferred to the turbine inlet. After the turbine calculation is completed, the deviation of the solution of adjacent components is calculated to determine whether the deviation meets the given value. If so, the iteration ends. If not, the boundary conditions of the compressor outlet and the combustion chamber outlet continue to be updated according to the relaxation iteration method until the deviation meets the given value and the simulation is completed.

3. A computer device comprising a memory and a processor, characterized in that: A computer program is stored in the memory. When the processor runs the computer program stored in the memory, the processor executes the method for joint simulation of three-dimensional performance of an aircraft engine core machine under the whole machine matching constraint according to any one of claims 1-2.

4. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, which, when executed by a processor, executes the steps of the method for joint simulation of three-dimensional performance of an aircraft engine core machine under whole-machine matching constraints as described in any one of claims 1-2.

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