Engine performance simulation method and integrated simulation platform

Abstract

The invention relates to the technical field of engine performance testing, and discloses an engine performance simulation method and an integrated simulation platform, and the method comprises the steps: constructing the integrated simulation platform comprising a complete machine 0D model and a birotor turbine 3D integrated model, operating the complete machine 0D model under a simulation condition to obtain the performance parameters and boundary conditions of a birotor turbine, setting boundary conditions of the double-rotor turbine 3D integrated model on the basis, adjusting the boundary conditions to obtain performance parameters of the double-rotor turbine 3D integrated model, judging whether simulation conditions are met or not according to the performance parameters of the two models, if not, adjusting the complete machine 0D model until the simulation conditions are met, and executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step of executing the step. And determining overall performance parameters of the engine and performance parameters of the double-rotor turbine. According to the method, the influence of the pneumatic strong coupling effect between the parts and the runner loss between the parts on the performance of the whole machine can be more accurately considered, and the prediction precision of the part characteristics and the performance of the whole machine is improved.

Description

Technical Field

[0001] This invention relates to the field of engine performance testing technology, specifically to an engine performance simulation method and integrated simulation platform. Background Technology

[0002] Current aero-engine performance simulation mainly uses zero-dimensional (0D) simulation methods. The core of these methods is to solve nonlinear residual equations by combining independent characteristic diagrams of each component (derived from component 3D simulation or bench tests) with common working conditions such as continuous flow and power balance, thereby obtaining the performance of components and the entire engine.

[0003] This method can meet basic requirements in traditional, simple-configuration engines, but its limitations have become increasingly apparent with the development of aero-engines. On the one hand, traditional 0D simulation independently characterizes the characteristics of upstream and downstream components, ignoring the impact of aerodynamic coupling between components on component characteristics and overall engine matching characteristics. On the other hand, the total pressure loss in the transition section between components is calculated using simple formulas such as the converted flow rate at the upstream component outlet or the square of the Mach number, resulting in inaccurate evaluation results. Therefore, in traditional whole-engine 0D simulation methods, the coupling relationships between components and between components and the whole engine are weak, leading to insufficient accuracy in performance prediction. Modern aero-engines have more complex structures and component geometries, and greater aerodynamic loads, resulting in significantly enhanced aerodynamic coupling between components. Traditional 0D simulation is insufficient to meet the high-precision performance simulation requirements of advanced aero-engines, leading to increased design process risks, longer development cycles, and higher costs. Summary of the Invention

[0004] This invention provides an engine performance simulation method and integrated simulation platform to solve the problems of weak coupling between components and between components and the whole engine in existing engine performance simulation methods, as well as inaccurate assessment of transition section losses.

[0005] In a first aspect, the present invention provides an engine performance simulation method applied to an integrated simulation platform. The integrated simulation platform deploys a complete engine 0D model and a dual-rotor turbine 3D integrated model. The method includes: determining the simulation conditions of the integrated simulation platform, and the corresponding engine operating conditions and control laws; running the complete engine 0D model based on the operating conditions and control laws to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine; setting the second boundary conditions of the dual-rotor turbine 3D integrated model as the first boundary conditions, and adjusting the second boundary conditions based on the first performance parameters to obtain the second performance parameters of the dual-rotor turbine 3D integrated model; determining whether the simulation conditions are met based on the first and second performance parameters; if not, adjusting the complete engine 0D model; returning to the step of running the complete engine 0D model based on the operating conditions and control laws until the simulation conditions are met; and determining the engine's complete engine performance parameters and dual-rotor turbine performance parameters based on the adjusted complete engine 0D model and the adjusted dual-rotor turbine 3D integrated model.

[0006] The engine performance simulation method provided by this invention constructs an integrated simulation platform based on a whole engine 0D model and a dual-rotor turbine 3D integrated model. Under the simulation conditions defined by the integrated simulation platform, the whole engine 0D model is run to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. The second boundary conditions of the dual-rotor turbine 3D integrated model are set as the first boundary conditions, and the second boundary conditions are adjusted based on the first performance parameters to obtain the second performance parameters of the dual-rotor turbine 3D integrated model. Then, it is determined whether the simulation conditions are met. If not, the whole engine 0D model is adjusted, and the process returns to the step of running the whole engine 0D model until the simulation conditions are met. Finally, the whole engine performance parameters and dual-rotor turbine performance parameters are determined. This invention aerodynamically couples the integrated 3D model of components with the 0D simulation model of the whole machine to conduct mixed-dimensional simulation of the whole machine. This allows for a more accurate consideration of the impact of strong aerodynamic coupling between components and flow channel losses between components on the overall performance. During performance simulation, it strengthens the aerodynamic coupling between upstream and downstream components, as well as between components and the whole machine, thereby achieving a refined description of component characteristics, improving the prediction accuracy of component characteristics and overall machine performance, reducing the number of iterations between design and testing, and lowering the R&D cost, cycle, and risk of the engine.

[0007] In one optional implementation, both the first and second boundary conditions include outlet static pressure, and both the first and second performance parameters include the total expansion ratio of the dual-rotor turbine. The second boundary conditions are adjusted based on the first performance parameter to obtain the second performance parameter of the integrated 3D model of the dual-rotor turbine. This includes: running the integrated 3D model of the dual-rotor turbine to obtain its second performance parameter; calculating the relative error between the first total expansion ratio of the overall OD model and the second total expansion ratio of the integrated 3D model of the dual-rotor turbine, and determining whether the relative error is lower than an error threshold; if the relative error is not less than the error threshold, adjusting the outlet static pressure of the integrated 3D model of the dual-rotor turbine according to the first and second total expansion ratios; and returning to running the integrated 3D model of the dual-rotor turbine based on the adjusted outlet static pressure to obtain the second performance parameter of the integrated 3D model of the dual-rotor turbine, until the relative error is less than the error threshold, at which point the second performance parameter is determined.

[0008] This invention adjusts the outlet static pressure of the integrated 3D model of the dual-rotor turbine after setting the boundary conditions of the integrated 3D model of the dual-rotor turbine based on the boundary conditions of the 0D model of the whole machine. This can forcibly constrain the consistency of the total expansion ratio of the dual-rotor turbine between the 0D and 3D models, break through the coupling logic between the whole machine and the components, enable the 3D model to accurately respond to the matching state of the whole machine, and ensure the successful coupling between the 0D model of the whole machine and the integrated 3D model of the dual-rotor turbine.

[0009] In one optional implementation, the outlet static pressure of the dual-rotor turbine 3D integrated model is adjusted according to a first total expansion ratio and a second total expansion ratio, including: calculating the difference between the first total expansion ratio and the second total expansion ratio, calculating the product of the difference and a correction coefficient, and adding the outlet static pressure to the product to obtain the adjusted outlet static pressure.

[0010] This invention directly reflects the coupling deviation between the two rotor turbines by using the difference in the total expansion ratio between the 0D model and the 3D integrated model of the whole machine turbine. It can directly convert the deviation into the adjustment amount of the outlet static pressure through the correction coefficient, realize the direct correlation between the deviation and the correction, and thus optimize the outlet static pressure. This allows the 3D model to realistically reproduce the aerodynamic environment of the flow channel between turbine stages, avoiding the coarse treatment of the transition section loss in traditional 0D simulation that only relies on a simple square relationship. This indirectly improves the accuracy of the transition section loss assessment and provides key support for the refined description of component characteristics.

[0011] In one optional implementation, the simulation conditions include at least: the maximum number of external iterations, the longest simulation time, and the convergence criterion. Determining whether the simulation conditions are met based on a first performance parameter and a second performance parameter includes: determining whether the convergence criterion is met based on the first performance parameter and the second performance parameter; determining whether the current number of external iterations is greater than the maximum number of external iterations, and determining whether the current simulation time is greater than the longest simulation time; if at least one of the following is met: the convergence criterion is met, the current number of external iterations is greater than the maximum number of external iterations, or the current simulation time is greater than the longest simulation time, then the simulation conditions are met; otherwise, the simulation conditions are not met.

[0012] This invention, by setting a maximum number of external iterations and a maximum simulation time, can prevent the integrated simulation platform from becoming uncontrollable, ensuring that the simulation process is predictable and controllable, and improving the stability of the overall simulation process. Based on this, it determines whether the convergence criteria are met by judging the performance parameters between the whole machine 0D model and the dual-rotor turbine 3D integrated model, and whether the coupling deviation between the two meets the requirements. Thus, through gradual iterative adjustments, the coupling degree between the two is gradually strengthened.

[0013] In one optional implementation, both the first performance parameter and the second performance parameter include: the first converted flow rate, the first expansion ratio, and the first isentropic efficiency of the gas turbine; the second converted flow rate, the second expansion ratio, and the second isentropic efficiency of the power turbine; and the total pressure recovery coefficient of the inter-stage transition section. Determining whether the convergence criterion is met based on the first and second performance parameters includes: calculating the performance residuals between each corresponding first and second performance parameter, whereby the performance residuals include: the residuals of the first converted flow rate, the first expansion ratio, and the first isentropic efficiency of the gas turbine; the residuals of the second converted flow rate, the second expansion ratio, and the second isentropic efficiency of the power turbine; and the residual of the total pressure recovery coefficient of the inter-stage transition section. Each performance residual is compared with the convergence residual; if each performance residual is lower than the convergence residual, the convergence criterion is met; otherwise, the convergence criterion is not met.

[0014] This invention calculates the residuals corresponding to the seven core performance parameters of a dual-rotor turbine simulation, which can simultaneously cover the core performance indicators of a single turbine component and the key parameters of inter-component coupling, achieving full-dimensional coverage of the performance of a single component and the collaborative characteristics between components, and ensuring the collaborative stability of the hybrid-dimensional simulation.

[0015] In one optional implementation, the whole machine 0D model is adjusted, including: determining the total residual based on each performance residual, and determining the correction factor for the current internal iteration step within the constraints with the goal of minimizing the total residual. The correction factors include: a first converted flow rate correction factor, a first expansion ratio correction factor, and a first isentropic efficiency correction factor for the gas turbine; a second converted flow rate correction factor and a second isentropic efficiency correction factor for the power turbine; and a total pressure recovery coefficient correction factor for the transition section. The characteristic map of the corresponding first performance parameter is then corrected according to each correction factor, and the whole machine 0D model is run based on the corrected characteristic map to obtain the corrected first performance parameters. The parameters include the corrected first converted flow rate, the corrected first expansion ratio, the corrected first isentropic efficiency, the corrected second converted flow rate, the corrected second expansion ratio, the corrected second isentropic efficiency, and the corrected transition section total pressure recovery coefficient. The corrected second expansion ratio is determined based on the corrected first expansion ratio, the corrected transition section total pressure recovery coefficient, and the total expansion ratio of the dual-rotor turbine. The performance residuals between the corrected first performance parameters and each corresponding second performance parameter are calculated, and the process returns to the step of determining the total residual based on each performance residual, and determining the correction factor of the current internal iteration step within the constraints with the goal of minimizing the total residual, until the current internal iteration number reaches the maximum internal iteration number.

[0016] This invention addresses the performance parameter differences between the dual-rotor turbine and the integrated 3D model of the whole machine's 0D model. It constructs correction factors for the converted flow rate, expansion ratio, efficiency, and total pressure recovery coefficient. Based on these correction factors, the characteristic diagram of the 0D model is adjusted, integrating the component characteristics of the 0D model with the aerodynamic coupling effect captured by the 3D model. This corrects the gas turbine characteristic diagram, power turbine characteristic diagram, and total pressure recovery coefficient of the transition section in the whole machine's 0D model, ensuring that the optimization direction of the 0D model gradually aligns with the deviation from the actual operating conditions fed back by the 3D model.

[0017] In one optional implementation, determining a correction factor within a constraint range with the goal of minimizing the total residual includes: determining the lower limit of the constraint range based on the correction factor determined in the previous internal iteration step and a first preset change amount, and determining the upper limit of the constraint range based on the correction factor determined in the previous internal iteration step and a second preset change amount; constructing an objective function with the goal of minimizing the total residual, and solving the objective function using a preset algorithm based on the constraint range to obtain the correction factor for the current internal iteration step.

[0018] In order to ensure that the performance residuals of the dual-rotor turbine meet the convergence criteria, this invention transforms the solution of the correction factor into an iterative optimization problem. The optimization variable is the correction factor, and the optimization objective is to minimize the total residual of the dual-rotor turbine performance. This invention can constrain the variation range of the correction factor while ensuring the matching of performance parameters between the 0D model and the 3D model, thereby controlling the residual oscillation amplitude and ensuring stable convergence of the simulation.

[0019] Secondly, the present invention provides an integrated simulation platform, which is equipped with a control module, a complete engine 0D model, and a dual-rotor turbine 3D integrated model. The gas turbine in the complete engine 0D model is represented by a gas turbine characteristic diagram, and the power turbine is represented by a power turbine characteristic diagram. The total pressure loss of the turbine stage transition section between the gas turbine and the power turbine is represented by the total pressure recovery coefficient of the transition section. The dual-rotor turbine 3D integrated model is constructed based on the gas turbine and the power turbine, including: an inlet section, a first adjustable guide vane and a first moving blade corresponding to the gas turbine, a second adjustable guide vane and a second moving blade corresponding to the power turbine, and an outlet section. The control module is connected to the complete engine 0D model and the dual-rotor turbine 3D integrated model and is used to execute the engine performance simulation method of the first aspect or any corresponding embodiment described above.

[0020] The integrated simulation platform provided by this invention deploys a complete 0D model and a dual-rotor turbine 3D integrated model. It characterizes the dual-rotor turbine characteristics in the complete 0D model using gas turbine characteristic diagrams, power turbine characteristic diagrams, and the total pressure recovery coefficient of the transition section. The dual-rotor turbine 3D integrated model is constructed using the inlet section, the first adjustable guide vane and first moving blade corresponding to the gas turbine, the second adjustable guide vane and second moving blade corresponding to the power turbine, and the outlet section. This allows for bidirectional data transfer between the complete 0D model and the dual-rotor turbine 3D integrated model without altering the original architecture of the complete 0D model. This couples the complete 0D model with the dual-rotor turbine 3D integrated model, strengthening the aerodynamic coupling between components and the complete machine. It establishes a mixed-dimensional simulation model of the complete machine, accurately assessing the strong aerodynamic coupling between the dual rotor turbines, interstage transition losses, changes in working fluid thermophysical parameters, and the impact of blade cooling on the overall machine performance, thereby improving the prediction accuracy of component and overall machine performance.

[0021] In one optional implementation, the boundary conditions of the inlet and outlet sections in the integrated 3D model of the dual-rotor turbine are set based on the boundary conditions obtained from the whole machine 0D model. The boundary conditions include: total inlet pressure, total inlet temperature, axial intake conditions, and static outlet pressure.

[0022] This invention establishes a 3D integrated model of upstream and downstream components, the gas turbine and the power turbine, and sets boundary conditions for the inlet and outlet sections of the dual-rotor turbine 3D integrated model based on the whole machine 0D model. This can enhance the aerodynamic coupling between components, thereby more accurately considering the strong aerodynamic coupling effect and interstage transition losses, and achieving a refined description of component characteristics.

[0023] In one optional implementation, the rotational speeds of the first and second moving blades are determined according to the engine's operating conditions, the variable geometry angles of the first and second adjustable guide vanes are determined according to the engine's control laws, and the thermophysical parameters of the gas turbine and the power turbine, as well as the blade cooling parameters, are determined based on simulation of the whole machine's 0D model.

[0024] This invention ensures that the parameter settings conform to the actual operating logic of the engine by setting the rotor speed according to the operating conditions, the guide vane angle according to the control law, and the thermophysical parameters and blade cooling parameters according to the 0D model. This enhances the accuracy of the boundary conditions of the 3D integrated model, supports the refined description of component characteristics, promotes the synergistic coupling between the 0D model and the 3D model, opens up the data transmission closed loop, and realizes the coupling closed loop. Attached Figure Description

[0025] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure of the integrated simulation platform according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the overall 0D model of the integrated simulation platform according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of a dual-rotor turbine 3D integrated model of the integrated simulation platform according to an embodiment of the present invention; Figure 4 This is a detailed structural diagram of the integrated simulation platform according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the first process of an engine performance simulation method according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the overall process of an engine performance simulation method according to an embodiment of the present invention; Figure 7 This is a second flowchart illustrating an engine performance simulation method according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the third process of an engine performance simulation method according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the hardware structure of the terminal device according to an embodiment of the present invention. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] It is understood that before using the technical solutions disclosed in the various embodiments of the present invention, users should be informed of the types, scope of use, and usage scenarios of the personal information involved in the present invention and their authorization should be obtained in accordance with relevant laws and regulations through appropriate means.

[0029] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0030] As an optional application scenario of this invention, such as Figure 1 As shown, an integrated simulation platform 100 is pre-constructed, in which a control module 101, a whole-machine 0D model 102, and a dual-rotor turbine 3D integrated model 103 are deployed. The gas turbine in the whole-machine 0D model 102 is represented by a gas turbine characteristic diagram, and the power turbine is represented by a power turbine characteristic diagram. The total pressure loss of the turbine stage transition section between the gas turbine and the power turbine is represented by the total pressure recovery coefficient of the transition section. The dual-rotor turbine 3D integrated model 103 is constructed based on the gas turbine and the power turbine, including: inlet section, the first adjustable guide vane S1 and the first moving blade R1 corresponding to the gas turbine, the second adjustable guide vane S2 and the second moving blade R2 corresponding to the power turbine, and outlet section. The control module is connected to the whole-machine 0D model and the dual-rotor turbine 3D integrated model.

[0031] Specifically, in this embodiment of the invention, a typical turboshaft engine is used as an example, and its overall OD model 102 is as follows: Figure 2As shown, a turboshaft engine consists of major components such as an axial-centrifugal combined compressor, a combustion chamber, a gas turbine, a power turbine, and exhaust pipes. The turboshaft engine contains two rotors: a gas generator rotor and a power turbine rotor. The axial-centrifugal combined compressor and gas turbine are located on the gas generator rotor. The power turbine is located on the power turbine rotor, which is used to output shaft power. The gas generator rotor and the power turbine rotor rotate at different speeds.

[0032] In traditional whole-machine 0D simulation methods, the characteristics of the above-mentioned components are characterized by independent component characteristic maps, which are usually derived from component 3D simulation or component bench tests. Figure 2 The diagram shows typical characteristic diagrams of the axial-centrifugal combined compressor, gas turbine, and power turbine. Based on the known characteristic diagrams of each component, the performance of each component and the overall engine performance are obtained by solving a set of nonlinear residual equations generated by the common operating conditions of components such as continuous flow, power balance, and uniform speed. The upstream and downstream components of the overall engine 0D model 102 are characterized using independent characteristic diagrams, and the total pressure loss in the transition section between components is represented by a simple relationship between the converted flow rate or the square of the Mach number at the outlet of the upstream component.

[0033] This approach has two problems: 1) It considers the characteristics of upstream and downstream components independently, neglecting the impact of aerodynamic coupling between them on component characteristics and overall engine performance; 2) The loss assessment of the transition section between components is inaccurate. Furthermore, for traditional simple-configuration aero-engines, due to the weak coupling between components and between components and the entire engine, whole-engine 0D simulation methods can usually achieve good accuracy in predicting overall engine performance. However, with the development of aero-engines, engine structures and component geometries have become more complex, component aerodynamic loads have increased, and the aerodynamic coupling between components has become more significant. Traditional whole-engine 0D simulation methods are no longer sufficient to meet the high-precision performance simulation requirements of advanced aero-engines.

[0034] Therefore, without changing the original architecture of the overall machine 0D model 102, this embodiment of the invention constructs a dual-rotor turbine 3D integrated model 103, as follows: Figure 3As shown, the gas turbine consists of a first adjustable guide vane S1 and a first moving vane R1, while the power turbine consists of a second adjustable guide vane S2 and a second moving vane R2. The upstream of the first adjustable guide vane S1 is the inlet section of the dual-rotor turbine 3D integrated model 103, where inlet boundary conditions need to be set, typically including inlet total pressure, inlet total temperature, and axial intake conditions. The downstream of the second moving vane R2 is the outlet section of the dual-rotor turbine 3D integrated model 103, where outlet boundary conditions need to be set, typically including outlet static pressure. The boundary conditions of the inlet and outlet sections in the dual-rotor turbine 3D integrated model are based on the boundary conditions obtained from the overall engine 0D model. Since the gas turbine and power turbine are located on different rotors, the rotational speeds of the first moving vane R1 and the second moving vane R2 need to be set separately according to the engine's operating conditions. The variable geometry angles of the first adjustable guide vane S1 and the second adjustable guide vane S2 are determined by the engine control laws. When the gas turbine and / or power turbine are air-cooled turbines, cooling flow parameters such as cooling flow rate and cooling pressure of the guide vanes and moving blades need to be set separately, which can be obtained from the whole machine 0D model simulation. The thermal properties of the gas flowing through the gas turbine and power turbine and the blade cooling parameters, such as specific heat at constant pressure and specific heat ratio, can be obtained from the whole machine 0D model simulation.

[0035] After the dual-rotor turbine 3D integrated model 103 is built, the resulting integrated simulation platform 100 is as follows: Figure 4 As shown, in this embodiment of the invention, the control module 101 is used to perform mixed-dimensional simulation on the whole machine 0D model 102 and the dual rotor turbine 3D integrated model 103, and to perform aerodynamic coupling on the whole machine 0D model 102 and the dual rotor turbine 3D integrated model 103, so as to simulate and test the performance of the aero-engine.

[0036] The integrated simulation platform provided by this invention deploys a complete 0D model and a dual-rotor turbine 3D integrated model. It characterizes the dual-rotor turbine characteristics in the complete 0D model using gas turbine characteristic diagrams, power turbine characteristic diagrams, and the total pressure recovery coefficient of the transition section. The dual-rotor turbine 3D integrated model is constructed using the inlet section, the first adjustable guide vane and first moving blade corresponding to the gas turbine, the second adjustable guide vane and second moving blade corresponding to the power turbine, and the outlet section. This allows for bidirectional data transfer between the complete 0D model and the dual-rotor turbine 3D integrated model without altering the original architecture of the complete 0D model. This couples the complete 0D model with the dual-rotor turbine 3D integrated model, strengthening the aerodynamic coupling between components and the complete machine. It establishes a mixed-dimensional simulation model of the complete machine, accurately assessing the strong aerodynamic coupling between the dual rotor turbines, interstage transition losses, changes in working fluid thermophysical parameters, and the impact of blade cooling on the overall machine performance, thereby improving the prediction accuracy of component and overall machine performance.

[0037] This invention provides an engine performance simulation method that, by conducting a hybrid-dimensional simulation of the entire engine, accurately considers the impact of strong aerodynamic coupling between the dual rotor turbines and the transition losses between turbine stages on the overall engine performance, thereby improving the accuracy of overall engine performance prediction.

[0038] According to an embodiment of the present invention, an embodiment of an engine performance simulation method is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0039] This embodiment provides an engine performance simulation method that can be used in the aforementioned integrated simulation platform. Figure 5 This is a flowchart of an engine performance simulation method according to an embodiment of the present invention, such as... Figure 5 As shown, the process includes the following steps: Step S501: Determine the simulation conditions of the integrated simulation platform, the corresponding engine operating conditions and control laws, and run the whole machine 0D model based on the operating conditions and control laws to obtain the first performance parameters and first boundary conditions of the dual rotor turbine.

[0040] Specifically, in this embodiment of the invention, in order to ensure that the integrated simulation platform can achieve fully automatic control of the simulation process, complete the calling and execution of models, and the data interaction and collaborative simulation between models, after preparing the whole machine 0D model and the dual rotor turbine 3D integrated model as a component model, when initializing the integrated simulation platform, simulation parameters such as the maximum number of external iterations, the longest simulation time, and the convergence criterion need to be set. The maximum number of external iterations, the longest simulation time, and the convergence criterion are used as simulation conditions of the integrated simulation platform.

[0041] In addition, such as Figure 6 As shown, after initializing the integrated simulation platform, in order to aerodynamically couple the 0D model of the whole engine and the 3D integrated model of the dual-rotor turbine, it is necessary to determine the engine's operating conditions and control laws, so as to perform mixed-dimensional simulation of the 0D model of the whole engine and the 3D integrated model of the dual-rotor turbine in the same scenario. The operating conditions include flight altitude, flight Mach number, ISA temperature deviation, etc.; the control laws are given the physical speed of the gas generator rotor, variable geometry, etc.

[0042] Based on the established simulation conditions, operating conditions, and control laws, such as Figure 6 As shown, a 0D model of the entire machine is run based on operating conditions and control laws to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. The performance parameters of the dual-rotor turbine include: gas turbine converted flow rate. Gas turbine expansion ratio entropy efficiency of gas turbine Power turbine conversion flow rate Power Turbine Expansion Ratio Entropy efficiency of power turbine Total pressure recovery coefficient of the turbine stage transition section and the total expansion ratio of the twin-rotor turbine .

[0043] In some alternative implementations, the boundary conditions for the dual-rotor turbine include: the total pressure at the gas turbine inlet. Total temperature at the gas turbine inlet Gas turbine inlet oil-gas ratio Physical speed of gas generator rotor Physical speed of the power turbine rotor Variable geometry of gas turbine guide vanes Variable geometry of power turbine guide vanes Gas turbine guide vane cooling flow rate Gas turbine guide vane cooling flow pressure Gas turbine blade cooling flow rate Gas turbine blade cooling flow pressure Cooling flow rate of power turbine guide vanes , power turbine guide vane cooling flow pressure Cooling flow rate of power turbine blades Power turbine blade cooling flow pressure This is just an example and is not intended to be limiting.

[0044] Step S502: Set the second boundary condition of the dual-rotor turbine 3D integrated model as the first boundary condition, and adjust the second boundary condition based on the first performance parameter to obtain the second performance parameter of the dual-rotor turbine 3D integrated model.

[0045] Specifically, in embodiments of the present invention, such as Figure 4 As shown, the dual-rotor turbine 3D integrated model serves as a component 3D integrated model. The whole machine 0D model can provide boundary conditions for it under whole machine matching. That is, the boundary conditions of the dual-rotor turbine 3D integrated model are set to the corresponding values ​​of the boundary conditions obtained from the whole machine 0D model. The boundary conditions are set as follows: , , , , ; , , , ; , , , ; , ; Since the overall 0D model mainly involves total parameters, while the outlet boundary condition of the dual-rotor turbine 3D integrated model is a static parameter, i.e., the outlet static pressure, an internal iteration of the dual-rotor turbine 3D integrated model is added during the simulation. For example, this internal iteration can be implemented using a user-defined function in the commercial software ANSYS CFX to dynamically adjust the outlet static pressure of the dual-rotor turbine 3D integrated model. To ensure the overall expansion ratio between the integrated 3D model of the dual-rotor turbine and the 0D model of the whole machine. They are approximately equal.

[0046] Step S503: Determine whether the simulation conditions are met based on the first performance parameter and the second performance parameter. If not, adjust the whole machine 0D model.

[0047] Specifically, in this embodiment of the invention, the outlet static pressure of the integrated 3D model of the dual-rotor turbine is iteratively adjusted to ensure the overall expansion ratio between the integrated 3D model of the dual-rotor turbine and the 0D model of the whole machine. After approximating equality, such as Figure 6 As shown, the performance parameters of the adjusted dual-rotor turbine are obtained. Specifically, in calculating the performance of the dual-rotor turbine, a mass flow rate averaging method is used to perform parameter averaging and mathematical operations on the inlet and outlet cross-sections of the gas turbine to obtain the gas turbine performance, including: gas turbine converted flow rate, gas turbine expansion ratio, and gas turbine isentropic efficiency. Similarly, parameter averaging and mathematical operations are performed on the inlet and outlet cross-sections of the power turbine to obtain the power turbine performance, including: power turbine converted flow rate, power turbine expansion ratio, and power turbine isentropic efficiency. Finally, parameter averaging and mathematical operations are performed on the gas turbine outlet cross-section and the power turbine inlet cross-section to obtain the total pressure recovery coefficient of the interstage transition section. The inlet section of the gas turbine and the outlet section of the power turbine are subjected to parameter averaging and mathematical calculations to obtain the overall performance of the dual-rotor turbine: the overall expansion ratio of the dual-rotor turbine. .

[0048] Based on this, according to the performance residual between the performance parameters under the dual-rotor turbine 3D integrated model and the performance parameters under the whole machine 0D model, it is determined whether the pre-set convergence criteria are met based on the performance residual. If not, the gas turbine characteristic diagram, power turbine characteristic diagram and transition section total pressure recovery coefficient of the whole machine 0D model are corrected.

[0049] Step S504: Return to the step of running the whole machine 0D model based on the operating conditions and control laws until the simulation conditions are met. Determine the engine's overall performance parameters and the dual rotor turbine performance parameters based on the adjusted whole machine 0D model and the adjusted dual rotor turbine 3D integrated model.

[0050] Specifically, in this embodiment of the invention, after correcting the overall machine 0D model, the adjusted overall machine 0D model is rerun to obtain the performance parameters and boundary conditions of the dual-rotor turbine under the adjusted overall machine 0D model. Based on the boundary conditions of the overall machine 0D model, the boundary conditions of the dual-rotor turbine 3D integrated model are adjusted, and the dual-rotor turbine 3D integrated model undergoes internal iteration to obtain the performance parameters under the dual-rotor turbine 3D integrated model. The performance residual between the performance parameters under the dual-rotor turbine 3D integrated model and the performance parameters under the overall machine 0D model is used to determine whether the convergence criterion is met. During the iterative adjustment process, the component 3D integrated model provides more refined and accurate component characteristics to the overall machine 0D model, such as... Figure 4 As shown, this strengthens the aerodynamic coupling between components and the whole machine in the 0D model. Based on this, conducting mixed-dimensional simulation of the whole machine can more accurately consider the strong aerodynamic coupling between components, flow channel losses between components, changes in the thermophysical properties of the working fluid, and the impact of blade cooling on the overall performance, thereby improving the prediction accuracy of component and overall machine performance.

[0051] Once the convergence criteria are met, the engine's overall performance parameters and the dual-rotor turbine's performance parameters are determined based on the final adjusted 0D model and the adjusted integrated 3D model of the dual-rotor turbine. Specifically, the dual-rotor turbine performance parameters are determined based on the integrated 3D model of the dual-rotor turbine, while the overall engine performance parameters are determined based on the 0D model of the engine.

[0052] The engine performance simulation method provided by this invention constructs an integrated simulation platform based on a whole engine 0D model and a dual-rotor turbine 3D integrated model. Under the simulation conditions defined by the integrated simulation platform, the whole engine 0D model is run to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. The second boundary conditions of the dual-rotor turbine 3D integrated model are set as the first boundary conditions, and the second boundary conditions are adjusted based on the first performance parameters to obtain the second performance parameters of the dual-rotor turbine 3D integrated model. Then, it is determined whether the simulation conditions are met. If not, the whole engine 0D model is adjusted, and the process returns to the step of running the whole engine 0D model until the simulation conditions are met. Finally, the whole engine performance parameters and dual-rotor turbine performance parameters are determined. This invention aerodynamically couples the integrated 3D model of components with the 0D simulation model of the whole machine to conduct mixed-dimensional simulation of the whole machine. This allows for a more accurate consideration of the impact of strong aerodynamic coupling between components and flow channel losses between components on the overall performance. During performance simulation, it strengthens the aerodynamic coupling between upstream and downstream components, as well as between components and the whole machine, enabling a refined description of component characteristics, improving the prediction accuracy of component characteristics and overall machine performance, reducing the number of iterations between design and testing, and lowering the R&D cost, cycle, and risk of engines. This is of great significance for improving the development capability and level of next-generation high-performance aero-engines.

[0053] This embodiment provides an engine performance simulation method that can be used in the aforementioned integrated simulation platform. Figure 7 This is a flowchart of an engine performance simulation method according to an embodiment of the present invention, such as... Figure 7 As shown, the process includes the following steps: Step S701: Determine the simulation conditions of the integrated simulation platform, and the corresponding engine's operating conditions and control laws. Based on the operating conditions and control laws, run the whole engine 0D model to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. For details, please refer to [link to relevant documentation]. Figure 5 Step S501 of the illustrated embodiment will not be described again here.

[0054] Step S702: Set the second boundary condition of the dual-rotor turbine 3D integrated model as the first boundary condition, and adjust the second boundary condition based on the first performance parameter to obtain the second performance parameter of the dual-rotor turbine 3D integrated model.

[0055] Specifically, step S702 includes: Step S7021: Run the dual-rotor turbine 3D integrated model to obtain the second performance parameters of the dual-rotor turbine 3D integrated model.

[0056] Specifically, in this embodiment of the invention, the control module invokes the dual-rotor turbine 3D integrated model, causing the model to run according to set boundary conditions and obtain corresponding performance parameters, including: gas turbine converted flow rate. Gas turbine expansion ratio entropy efficiency of gas turbine Power turbine conversion flow rate Power Turbine Expansion Ratio Entropy efficiency of power turbine Total pressure recovery coefficient of the turbine stage transition section and the total expansion ratio of the twin-rotor turbine .

[0057] Step S7022: Calculate the relative error between the first total expansion ratio of the whole machine 0D model and the second total expansion ratio of the dual rotor turbine 3D integrated model, and determine whether the relative error is lower than the error threshold.

[0058] Specifically, in this embodiment of the invention, the total expansion ratio under the whole machine 0D model is calculated based on the whole machine 0D model. Total expansion ratio under the integrated 3D model of dual rotor turbine The relative error between them is determined, and it is judged whether the relative error is less than a preset error threshold. The calculation and comparison of relative errors are shown below:

[0059] Step S7023: If the relative error is not less than the error threshold, the outlet static pressure of the dual-rotor turbine 3D integrated model is adjusted according to the first total expansion ratio and the second total expansion ratio.

[0060] Specifically, in this embodiment of the invention, if the relative error is greater than the error threshold... The outlet static pressure of the dual-rotor turbine 3D integrated model is then... Iterative adjustments are performed. This embodiment of the invention iteratively adjusts the outlet static pressure. At that time, calculate the total expansion ratio of the whole machine 0D model in the current internal iteration step. Total expansion ratio under the integrated 3D model of dual rotor turbine The difference is calculated and compared with a pre-set correction factor. The product of the two, and the output static pressure of the current internal iteration step. Adding the product together, we obtain the outlet static pressure for the next iteration. The iterative formula is shown below, but is not limited to this:

[0061] Among them, the correction coefficient It can be set to -10, but is not limited to this value.

[0062] Step S7024 involves returning to the operating dual-rotor turbine 3D integrated model based on the adjusted outlet static pressure to obtain the second performance parameters of the dual-rotor turbine 3D integrated model. This process continues until the relative error is less than the error threshold, at which point the second performance parameters are determined.

[0063] Specifically, in this embodiment of the invention, based on the adjusted outlet static pressure Moving to the next iteration, the internal iteration of the dual-rotor turbine 3D integrated model ensures its overall expansion ratio with the complete machine 0D model. Approximately equal, at this point the performance parameters of the dual-rotor turbine 3D integrated model are obtained.

[0064] Step S703: Based on the first and second performance parameters, determine whether the simulation conditions are met. If not, adjust the overall 0D model. For details, please refer to [link to relevant documentation]. Figure 5 Step S503 of the illustrated embodiment will not be described again here.

[0065] Step S704: Return to the step of running the whole engine 0D model based on operating conditions and control laws until the simulation conditions are met. Determine the engine's overall performance parameters and the dual-rotor turbine performance parameters based on the adjusted whole engine 0D model and the adjusted dual-rotor turbine 3D integrated model. For details, please refer to [link to relevant documentation]. Figure 5 Step S504 of the illustrated embodiment will not be described again here.

[0066] The engine performance simulation method provided by this invention constructs an integrated simulation platform based on a whole engine 0D model and a dual-rotor turbine 3D integrated model. Under the simulation conditions defined by the integrated simulation platform, the whole engine 0D model is run to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. The second boundary conditions of the dual-rotor turbine 3D integrated model are set as the first boundary conditions, and the second boundary conditions are adjusted based on the first performance parameters to obtain the second performance parameters of the dual-rotor turbine 3D integrated model. Then, it is determined whether the simulation conditions are met. If not, the whole engine 0D model is adjusted, and the process returns to the step of running the whole engine 0D model until the simulation conditions are met. Finally, the whole engine performance parameters and dual-rotor turbine performance parameters are determined. This invention aerodynamically couples the integrated 3D model of components with the 0D simulation model of the whole machine to conduct mixed-dimensional simulation of the whole machine. This allows for a more accurate consideration of the impact of strong aerodynamic coupling between components and flow channel losses between components on the overall performance. During performance simulation, it strengthens the aerodynamic coupling between upstream and downstream components, as well as between components and the whole machine, thereby achieving a refined description of component characteristics, improving the prediction accuracy of component characteristics and overall machine performance, reducing the number of iterations between design and testing, and lowering the R&D cost, cycle, and risk of the engine.

[0067] This embodiment provides an engine performance simulation method that can be used in the aforementioned integrated simulation platform. Figure 8 This is a flowchart of an engine performance simulation method according to an embodiment of the present invention, such as... Figure 8 As shown, the process includes the following steps: Step S801: Determine the simulation conditions of the integrated simulation platform, and the corresponding engine's operating conditions and control laws. Based on the operating conditions and control laws, run the whole engine 0D model to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. For details, please refer to [link to relevant documentation]. Figure 7 Step S701 of the illustrated embodiment will not be described again here.

[0068] Step S802: Set the second boundary condition of the integrated 3D model of the dual-rotor turbine to the first boundary condition, and adjust the second boundary condition based on the first performance parameters to obtain the second performance parameters of the integrated 3D model of the dual-rotor turbine. For details, please refer to [link to relevant documentation]. Figure 7 Step S702 of the illustrated embodiment will not be described again here.

[0069] Step S803: Determine whether the simulation conditions are met based on the first performance parameter and the second performance parameter. If not, adjust the whole machine 0D model.

[0070] Specifically, step S803 includes: Step S8031: Determine whether the convergence criterion is met based on the first performance parameter and the second performance parameter.

[0071] Specifically, in this embodiment of the invention, the performance parameters corresponding to the integrated 3D model of the dual-rotor turbine contain the same parameter types as the performance parameters corresponding to the overall 0D model, including: gas turbine converted flow rate. Gas turbine expansion ratio entropy efficiency of gas turbine Power turbine conversion flow rate Power Turbine Expansion Ratio Entropy efficiency of power turbine Total pressure recovery coefficient of the turbine stage transition section and the total expansion ratio of the twin-rotor turbine .

[0072] In some optional implementations, step S8031 above includes: Step a1: Calculate the performance residuals between the corresponding first and second performance parameters.

[0073] Step a2: Compare each performance residual with the convergence residual. If each performance residual is lower than the convergence residual, the convergence criterion is met; otherwise, the convergence criterion is not met.

[0074] Specifically, in this embodiment of the invention, the performance residuals between each relative performance parameter are calculated to obtain seven performance residuals: gas turbine converted flow rate residual, gas turbine expansion ratio residual, gas turbine isentropic efficiency residual, power turbine converted flow rate residual, power turbine expansion ratio residual, power turbine isentropic efficiency residual, and turbine stage transition section total pressure recovery coefficient residual. The calculation formulas are as follows:

[0075] in, These are the various performance parameters of the integrated 3D model of the dual-rotor turbine. These are the various performance parameters of the complete machine 0D model. This represents the performance residuals corresponding to each performance parameter. Each performance residual is then... With convergence residuals Compare and determine the residuals of each performance component. Are they all lower than the convergence residuals? :

[0076] in, The value can be 0.0005. This represents the first of the seven performance parameters of a dual-rotor turbine. i indivual.

[0077] When the performance residual of the twin-rotor turbine All are lower than the convergence residuals If the convergence criterion is met, then the iteration continues; otherwise, iteration continues.

[0078] Step S8032: Determine whether the current number of external iterations is greater than the maximum number of external iterations, and determine whether the current simulation time is greater than the longest simulation time.

[0079] Specifically, in this embodiment of the invention, when determining whether the convergence criterion is met, it is determined whether the current number of external iterations is greater than the preset maximum number of external iterations, and whether the current simulation time is greater than the preset maximum simulation time, thereby avoiding simulation runaway.

[0080] Step S8033: If at least one of the following conditions is met: the convergence criterion is satisfied, the current number of external iterations is greater than the maximum number of external iterations, or the current simulation time is greater than the maximum simulation time, then the simulation conditions are satisfied; otherwise, the simulation conditions are not satisfied.

[0081] Specifically, in this embodiment of the invention, if at least one of the following is satisfied: the convergence criterion is met, the current number of external iterations is greater than the maximum number of external iterations, or the current simulation time is greater than the longest simulation time, then the simulation conditions are met, and the integrated simulation platform automatically ends the iteration adjustment. At this time, the whole machine 0D model and the dual rotor turbine 3D integrated model reach the coupling condition, or the coupling cannot be satisfied after iteration, and the model needs to be checked, etc.

[0082] Step S8034: Determine the total residual based on each performance residual, and determine the correction factor for the current internal iteration step within the constraints with the goal of minimizing the total residual.

[0083] Specifically, in this embodiment of the invention, the total residual of the dual-rotor turbine performance parameters in the current internal iteration step is determined based on the performance residual between the overall 0D model and the integrated 3D model of the dual-rotor turbine. Based on the total residual Determine the correction factor for the current internal iteration step. Therefore, based on the correction factor The gas turbine characteristic diagram, power turbine characteristic diagram, and total pressure recovery coefficient of the transition section in the whole machine 0D model are corrected.

[0084] In some optional implementations, step S8034 above includes: Step b1: Determine the lower limit of the constraint range based on the correction factor and the first preset change amount determined in the previous internal iteration step, and determine the upper limit of the constraint range based on the correction factor and the second preset change amount determined in the previous internal iteration step.

[0085] Step b2: Construct an objective function with the goal of minimizing the total residual, and solve the objective function using a preset algorithm based on the constraint range to obtain the correction factor for the current internal iteration step.

[0086] Specifically, in this embodiment of the invention, in order to ensure that the residuals of the dual-rotor turbine performance parameters all meet the convergence criterion, the solution of the correction factors is transformed into an optimization problem, wherein the optimization variables are six correction factors: gas turbine converted flow correction factor. Gas turbine expansion ratio correction factor Gas turbine isentropic efficiency correction factor Power Turbine Flow Correction Factor Power turbine isentropic efficiency correction factor and the total pressure recovery coefficient correction factor of the transition section The optimization objective is to optimize the total residual of the dual-rotor turbine performance. Minimize; optimization methods can include genetic algorithms, gradient descent, particle swarm optimization, simulated annealing, etc.

[0087] In some alternative implementations, the total residual can be represented by the square root of the sum of the squares of the seven dual-rotor turbine performance residuals, or by other forms such as root mean square (RMS). Total residual in RMS form For example, the expression is as follows:

[0088] To control the residual oscillation amplitude and ensure stable convergence of the simulation, taking the correction factor of the gas turbine as an example, the constraint ranges of each optimization variable are set as follows:

[0089]

[0090]

[0091]

[0092] in, to This represents the preset change amount corresponding to each correction factor. These can be the same or different, and the value can be selected as 0.15. (Subscript) and These represent the parameters of the current internal iteration step and the parameters of the previous internal iteration step, respectively. Therefore, the lower limit of the constraint range is determined based on the correction factor and the first preset change amount determined in the previous internal iteration step, and the upper limit of the constraint range is determined based on the correction factor and the second preset change amount determined in the previous internal iteration step. At that time, each correction factor equals 1.

[0093] Step S8035: Correct the characteristic map of the corresponding first performance parameter according to each correction factor, and run the whole machine 0D model based on the corrected characteristic map to obtain the corrected first performance parameter.

[0094] Specifically, in the embodiments of the present invention, when determining various performance parameters Correction factor Then, based on each correction factor For performance parameters To make corrections, taking the correction of a gas turbine as an example, the correction formulas for each performance parameter are as follows:

[0095]

[0096]

[0097]

[0098] In this context, the subscripts mod and org represent the parameters before and after the correction, respectively.

[0099] Furthermore, the aforementioned performance parameters include seven items, while the correction factors determined in this embodiment of the invention include six items; therefore, the power turbine expansion ratio... No correction factor is used. This is because the iterative adjustment of the integrated 3D model of the dual-rotor turbine has already ensured... ,and Therefore, no power turbine expansion ratio correction factor was introduced, and the gas turbine expansion ratio was obtained directly after correction. Then, directly based on the gas turbine expansion ratio Total pressure recovery coefficient of the turbine stage transition section and the total expansion ratio of the twin-rotor turbine Determine the expansion ratio of the power turbine This is equivalent to the expansion ratio of the power turbine. Corrections have been made. Similarly, a power turbine expansion ratio correction factor can be used instead of a gas turbine expansion ratio correction factor.

[0100] By correcting the gas turbine converted flow rate, gas turbine expansion ratio, gas turbine isentropic efficiency, power turbine converted flow rate, power turbine expansion ratio, power turbine isentropic efficiency, and the total pressure recovery coefficient of the transition section between turbine stages, it is equivalent to adjusting the gas turbine characteristic diagram, power turbine characteristic diagram, and total pressure recovery coefficient of the transition section in the whole machine 0D model.

[0101] Step S8036: Calculate the performance residuals between the corrected first performance parameter and each corresponding second performance parameter, and return to the step of determining the total residual based on each performance residual, and determining the correction factor of the current internal iteration step within the constraint range with the goal of minimizing the total residual, until the current internal iteration number reaches the maximum internal iteration number.

[0102] Specifically, in this embodiment of the invention, the solver for the correction factor optimization problem is the whole-machine 0D model. That is, the optimization solution of the correction factor is an internal iterative process, continuously correcting the gas turbine characteristic diagram, power turbine characteristic diagram, and total pressure recovery coefficient of the transition section of the whole-machine 0D model, and continuously executing the corrected whole-machine 0D model. This continuously reduces the performance residual of the dual-rotor turbine performance parameters between the whole-machine 0D model and the integrated 3D model of the dual-rotor turbine. Since the integrated 3D model of the dual-rotor turbine is not introduced in the internal iteration, the iteration rate is relatively fast. However, the internal iteration only adjusts the whole-machine 0D model, which usually cannot reach the convergence criterion; therefore, a maximum number of internal iterations is set.

[0103] In any current internal iteration step, the total residual is determined based on each performance residual. With the goal of minimizing the total residual, a correction factor for the current internal iteration step is determined within constraints. Based on this correction factor, the gas turbine characteristic diagram, power turbine characteristic diagram, and transition section total pressure recovery coefficient of the whole machine 0D model are corrected. Then, the whole machine 0D model is run based on the corrected characteristic diagram to obtain the corrected first performance parameter. The performance residual between the corrected first performance parameter and each corresponding second performance parameter is calculated. The process then proceeds to the next internal iteration step, which is then used as the current internal iteration step, and the correction factor is readjusted. This embodiment of the invention, through internal iterative optimization of the correction factor, can gradually reduce the total residual of performance parameters between the whole machine 0D model and the dual-rotor turbine 3D integrated model to a certain extent. Based on this, the process proceeds to the next external iteration step, and within the external iteration, it re-enters the internal iterative adjustment of the dual-rotor turbine 3D integrated model.

[0104] Step S804: Return to the step of running the whole engine 0D model based on operating conditions and control laws until the simulation conditions are met. Determine the engine's overall performance parameters and the dual-rotor turbine performance parameters based on the adjusted whole engine 0D model and the adjusted dual-rotor turbine 3D integrated model. For details, please refer to... Figure 7 Step S703 of the illustrated embodiment will not be described again here.

[0105] The engine performance simulation method provided by this invention constructs an integrated simulation platform based on a whole engine 0D model and a dual-rotor turbine 3D integrated model. Under the simulation conditions defined by the integrated simulation platform, the whole engine 0D model is run to obtain the first performance parameters and first boundary conditions of the dual-rotor turbine. The second boundary conditions of the dual-rotor turbine 3D integrated model are set as the first boundary conditions, and the second boundary conditions are adjusted based on the first performance parameters to obtain the second performance parameters of the dual-rotor turbine 3D integrated model. Then, it is determined whether the simulation conditions are met. If not, the whole engine 0D model is adjusted, and the process returns to the step of running the whole engine 0D model until the simulation conditions are met. Finally, the whole engine performance parameters and dual-rotor turbine performance parameters are determined. This invention aerodynamically couples the integrated 3D model of components with the 0D simulation model of the whole machine to conduct mixed-dimensional simulation of the whole machine. This allows for a more accurate consideration of the impact of strong aerodynamic coupling between components and flow channel losses between components on the overall performance. During performance simulation, it strengthens the aerodynamic coupling between upstream and downstream components, as well as between components and the whole machine, thereby achieving a refined description of component characteristics, improving the prediction accuracy of component characteristics and overall machine performance, reducing the number of iterations between design and testing, and lowering the R&D cost, cycle, and risk of the engine.

[0106] Figure 9 This is a schematic diagram of the structure of a terminal device with an integrated simulation platform deployed, provided as an embodiment of the present invention.

[0107] The following is a detailed reference. Figure 9 The diagram illustrates a structural schematic suitable for implementing a terminal device according to an embodiment of the present invention. The terminal device may include a processor (e.g., a central processing unit, a graphics processing unit, etc.) 901, which can perform various appropriate actions and processes based on a program stored in a read-only memory (ROM) 902 or a program loaded from memory 908 into random access memory (RAM) 903. The RAM 903 also stores various programs and data required for the operation of the terminal device. The processor 901, ROM 902, and RAM 903 are interconnected via a bus 904. An input / output (I / O) interface 905 is also connected to the bus 904.

[0108] Typically, the following devices can be connected to I / O interface 905: input devices 906 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 907 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; memory devices 908 including, for example, magnetic tapes, hard disks, etc.; and communication devices 909. Communication device 909 allows the terminal device to exchange data via wireless or wired communication with other devices. Although Figure 9 Terminal devices with various means are shown, but it should be understood that it is not required to implement or have all the means shown, and more or fewer means may be implemented or have instead.

[0109] In particular, according to embodiments of the present invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of the present invention include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device 909, or installed from a memory 908, or installed from a ROM 902. When the computer program is executed by the processor 901, it performs the functions defined in the engine performance simulation method of the embodiments of the present invention.

[0110] Figure 9 The terminal device shown is merely an example and should not impose any limitations on the functionality and scope of use of the embodiments of the present invention.

[0111] This invention also provides a computer-readable storage medium. The methods described above according to embodiments of the invention can be implemented in hardware or firmware, or implemented as computer code that can be recorded on a storage medium, or implemented as computer code downloaded via a network and originally stored on a remote storage medium or a non-transitory machine-readable storage medium and then stored on a local storage medium. Thus, the methods described herein can be processed by software stored on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. The storage medium can be a magnetic disk, optical disk, read-only memory, random access memory, flash memory, hard disk, or solid-state drive, etc.; further, the storage medium can also include combinations of the above types of memory. It is understood that computers, processors, microprocessor controllers, or programmable hardware include storage components capable of storing or receiving software or computer code. When the software or computer code is accessed and executed by the computer, processor, or hardware, the engine performance simulation method shown in the above embodiments is implemented.

[0112] A portion of this invention can be applied as a computer program product, such as computer program instructions, which, when executed by a computer, can invoke or provide the methods and / or technical solutions according to the invention through the operation of the computer. Those skilled in the art will understand that the forms in which computer program instructions exist in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways in which computer program instructions are executed by a computer include, but are not limited to: the computer directly executing the instructions, or the computer compiling the instructions and then executing the corresponding compiled program, or the computer reading and executing the instructions, or the computer reading and installing the instructions and then executing the corresponding installed program. Here, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible to a computer.

[0113] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. An engine performance simulation method, characterized in that, The method is applied to an integrated simulation platform, which deploys a complete 0D model of the machine and a dual-rotor turbine 3D integrated model. The simulation conditions of the integrated simulation platform, the corresponding engine operating conditions and control laws are determined, and the whole machine 0D model is run based on the operating conditions and control laws to obtain the first performance parameters and first boundary conditions of the dual rotor turbine. The second boundary condition of the integrated 3D model of the dual rotor turbine is set as the first boundary condition, and the second boundary condition is adjusted based on the first performance parameter to obtain the second performance parameter of the integrated 3D model of the dual rotor turbine. Based on the first performance parameter and the second performance parameter, determine whether the simulation conditions are met. If not, adjust the whole machine 0D model. Return to the step of running the whole machine 0D model based on the operating conditions and the control law until the simulation conditions are met. Determine the whole machine performance parameters and the dual rotor turbine performance parameters based on the adjusted whole machine 0D model and the adjusted dual rotor turbine 3D integrated model.

2. The method according to claim 1, characterized in that, Both the first boundary condition and the second boundary condition include outlet static pressure, and both the first performance parameter and the second performance parameter include the total expansion ratio of the dual-rotor turbine. The adjustment of the second boundary conditions based on the first performance parameters to obtain the second performance parameters of the integrated 3D model of the dual-rotor turbine includes: Run the integrated 3D model of the dual-rotor turbine to obtain the second performance parameters of the integrated 3D model of the dual-rotor turbine; Calculate the relative error between the first total expansion ratio of the whole machine 0D model and the second total expansion ratio of the dual rotor turbine 3D integrated model, and determine whether the relative error is lower than the error threshold; If the relative error is not less than the error threshold, the outlet static pressure of the dual-rotor turbine 3D integrated model is adjusted according to the first total expansion ratio and the second total expansion ratio. Based on the adjusted outlet static pressure, the process of returning to the running dual-rotor turbine 3D integrated model to obtain the second performance parameter of the dual-rotor turbine 3D integrated model continues until the relative error is less than the error threshold, at which point the second performance parameter is determined.

3. The method according to claim 2, characterized in that, The adjustment of the outlet static pressure of the integrated 3D model of the dual-rotor turbine based on the first total expansion ratio and the second total expansion ratio includes: Calculate the difference between the first total expansion ratio and the second total expansion ratio, calculate the product of the difference and the correction coefficient, and add the outlet static pressure to the product to obtain the adjusted outlet static pressure.

4. The method according to claim 1, characterized in that, The simulation conditions include at least: maximum number of external iterations, longest simulation time, and convergence criterion. The determination of whether the simulation conditions are met based on the first performance parameter and the second performance parameter includes: Determine whether the convergence criterion is met based on the first performance parameter and the second performance parameter; Determine whether the current number of external iterations is greater than the maximum number of external iterations, and determine whether the current simulation time is greater than the maximum simulation time; If at least one of the following conditions is met: the convergence criterion is satisfied, the current number of external iterations is greater than the maximum number of external iterations, or the current simulation time is greater than the longest simulation time, then the simulation conditions are satisfied; otherwise, the simulation conditions are not satisfied.

5. The method according to claim 4, characterized in that, Both the first performance parameter and the second performance parameter include: the first converted flow rate, the first expansion ratio and the first isentropic efficiency of the gas turbine, the second converted flow rate, the second expansion ratio and the second isentropic efficiency of the power turbine, and the total pressure recovery coefficient of the turbine stage transition section; The step of determining whether the convergence criterion is met based on the first performance parameter and the second performance parameter includes: Calculate the performance residuals between each corresponding first performance parameter and second performance parameter. The performance residuals include: the first converted flow rate residual, the first expansion ratio residual, and the first isentropic efficiency residual of the gas turbine; the second converted flow rate residual, the second expansion ratio residual, and the second isentropic efficiency residual of the power turbine; and the total pressure recovery coefficient residual of the turbine stage transition section. Each performance residual is compared with the convergence residual. If each performance residual is lower than the convergence residual, the convergence criterion is satisfied; otherwise, the convergence criterion is not satisfied.

6. The method according to claim 5, characterized in that, The adjustment of the overall 0D model includes: The total residual is determined based on each of the aforementioned performance residuals, and with the goal of minimizing the total residual, the correction factor for the current internal iteration step is determined within the constraints. The correction factor includes: the first converted flow rate correction factor, the first expansion ratio correction factor, and the first isentropic efficiency correction factor for the gas turbine; the second converted flow rate correction factor and the second isentropic efficiency correction factor for the power turbine; and the total pressure recovery coefficient correction factor for the transition section. The characteristic diagrams of the corresponding first performance parameters are corrected according to each of the correction factors, and the whole machine 0D model is run based on the corrected characteristic diagrams to obtain the corrected first performance parameters. The corrected first performance parameters include the corrected first converted flow rate, the corrected first expansion ratio, the corrected first isentropic efficiency, the corrected second converted flow rate, the corrected second expansion ratio, the corrected second isentropic efficiency, and the corrected transition section total pressure recovery coefficient. The corrected second expansion ratio is determined based on the corrected first expansion ratio, the corrected transition section total pressure recovery coefficient, and the total expansion ratio of the dual rotor turbine. Calculate the performance residuals between the corrected first performance parameter and each corresponding second performance parameter, and return to the step of determining the total residual based on each performance residual, and determining the correction factor of the current internal iteration step within the constraints with the goal of minimizing the total residual, until the current internal iteration number reaches the maximum internal iteration number.

7. The method according to claim 6, characterized in that, The step of determining the correction factor within the constraints with the objective of minimizing the total residual includes: The lower limit of the constraint range is determined based on the correction factor and the first preset change amount determined in the previous internal iteration step, and the upper limit of the constraint range is determined based on the correction factor and the second preset change amount determined in the previous internal iteration step. An objective function is constructed with the goal of minimizing the total residual. Based on the constraint range, a preset algorithm is used to solve the objective function to obtain the correction factor for the current internal iteration step.

8. An integrated simulation platform, characterized in that, The integrated simulation platform is equipped with a control module, a complete 0D model of the machine, and a dual-rotor turbine 3D integrated model. The gas turbine in the whole machine 0D model is represented by a gas turbine characteristic diagram, the power turbine is represented by a power turbine characteristic diagram, and the total pressure loss of the turbine stage transition section between the gas turbine and the power turbine is represented by the total pressure recovery coefficient of the transition section. The integrated 3D model of the dual-rotor turbine is constructed based on the gas turbine and the power turbine, and includes: inlet section, first adjustable guide vane and first moving vane corresponding to the gas turbine, second adjustable guide vane and second moving vane corresponding to the power turbine, and outlet section; The control module is connected to the overall 0D model and the integrated 3D model of the dual-rotor turbine, and is used to execute the engine performance simulation method according to any one of claims 1 to 7.

9. The integrated simulation platform according to claim 8, characterized in that, Based on the boundary conditions obtained from the overall 0D model, the boundary conditions of the inlet and outlet sections in the integrated 3D model of the dual rotor turbine are set. The boundary conditions include: total inlet pressure, total inlet temperature, axial intake conditions, and static outlet pressure.

10. The integrated simulation platform according to claim 8, characterized in that, The rotational speeds of the first and second moving blades are determined according to the engine's operating conditions. The variable geometry angles of the first and second adjustable guide vanes are determined according to the engine's control laws. The thermal properties and blade cooling parameters of the gas turbine and the power turbine are determined based on simulation of the whole machine's 0D model.

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