CN-122021464-A - Engine performance simulation method and integrated simulation platform

CN122021464ACN 122021464 ACN122021464 ACN 122021464ACN-122021464-A

Abstract

The invention relates to the technical field of engine performance test and discloses an engine performance simulation method and an integrated simulation platform, wherein the method comprises the steps of constructing the integrated simulation platform comprising a complete machine 0D model and a double-rotor turbine 3D integrated model, operating the complete machine 0D model under simulation conditions to obtain performance parameters and boundary conditions of the double-rotor turbine, setting the boundary conditions of the double-rotor turbine 3D integrated model according to the performance parameters and adjusting the boundary conditions to obtain the performance parameters of the double-rotor turbine 3D integrated model, judging whether the simulation conditions are met according to the performance parameters of the two models, and if the simulation conditions are not met, adjusting the complete machine 0D model until the simulation conditions are met, and determining the complete machine performance parameters and the double-rotor turbine performance parameters of an engine. The invention can more accurately consider the influence of pneumatic strong coupling action among components and flow channel loss among components on the performance of the whole machine, and improves the component characteristics and the prediction precision of the performance of the whole machine.

Inventors

ZOU WANGZHI
JIN HAILIANG
XIAO WEI
ZHOU CHUN
Bao Qiaoqiao

Assignees

中国航发湖南动力机械研究所

Dates

Publication Date: 20260512
Application Date: 20260410

Claims (10)

1. An engine performance simulation method is characterized by being applied to an integrated simulation platform, wherein the integrated simulation platform is provided with a complete machine 0D model and a double-rotor turbine 3D integrated model, and the method comprises the following steps: determining simulation conditions of the integrated simulation platform, and operation conditions and control rules of the corresponding engine, and operating the complete machine 0D model based on the operation conditions and the control rules to obtain first performance parameters and first boundary conditions of the double-rotor turbine; setting a second boundary condition of the dual-rotor turbine 3D integrated model as the first boundary condition, and adjusting the second boundary condition based on the first performance parameter to obtain a second performance parameter of the dual-rotor turbine 3D integrated model; judging whether the simulation condition is met or not based on the first performance parameter and the second performance parameter, and if not, adjusting the whole machine 0D model; Returning to the step of operating the complete machine 0D model based on the operating condition and the control rule until the simulation condition is met, and determining the complete machine performance parameter and the double-rotor turbine performance parameter of the engine according to the adjusted complete machine 0D model and the adjusted double-rotor turbine 3D integrated model.
2. The method of claim 1, wherein the first boundary condition and the second boundary condition each comprise an outlet static pressure, and the first performance parameter and the second performance parameter each comprise a total expansion ratio of a dual rotor turbine; The adjusting the second boundary condition based on the first performance parameter to obtain a second performance parameter of the dual-rotor turbine 3D integrated model includes: operating the dual-rotor turbine 3D integrated model to obtain a second performance parameter of the dual-rotor turbine 3D integrated model; calculating a relative error between a first total expansion ratio of the whole machine 0D model and a second total expansion ratio of the double-rotor turbine 3D integrated model, and judging whether the relative error is lower than an error threshold value or not; If the relative error is not smaller 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; And returning to the operation of the dual-rotor turbine 3D integrated model based on the regulated outlet static pressure, and obtaining a second performance parameter of the dual-rotor turbine 3D integrated model until the relative error is smaller than the error threshold value, and determining the second performance parameter.
3. The method of claim 2, wherein said adjusting the outlet static pressure of the dual rotor turbine 3D integrated model based on the first and second total expansion ratios comprises: And calculating a difference value of the first total expansion ratio and the second total expansion ratio, calculating a product of the difference value and a correction coefficient, and adding the outlet static pressure to the product to obtain an adjusted outlet static pressure.
4. The method of claim 1, wherein the simulation conditions include at least a maximum number of external iterations, a maximum simulation time, and a convergence criterion, and wherein determining whether the simulation conditions are met based on the first performance parameter and the second performance parameter comprises: Judging whether the convergence criterion is met or not according to the first performance parameter and the second performance parameter; Judging whether the current external iteration times are larger than the maximum external iteration times or not, and judging whether the current simulation time is larger than the maximum simulation time or not; And if at least one of the convergence criterion is judged to be met, the current external iteration number is judged to be larger than the maximum external iteration number, and the current simulation time is judged to be larger than the longest simulation time is judged to be met, the simulation condition is judged to be met, otherwise, the simulation condition is judged not to be met.
5. The method of claim 4, wherein the first performance parameter and the second performance parameter each comprise a first scaled flow, a first expansion ratio, and a first isentropic efficiency of the gas turbine, a second scaled flow, a second expansion ratio, and a second isentropic efficiency of the power turbine, and a turbine interstage transition piece total pressure recovery coefficient; The determining whether the convergence criterion is satisfied according to the first performance parameter and the second performance parameter includes: Calculating performance residual errors between the corresponding first performance parameters and the corresponding second performance parameters, wherein the performance residual errors comprise a first converted flow residual error, a first expansion ratio residual error and a first isentropic efficiency residual error of the gas turbine, a second converted flow residual error, a second expansion ratio residual error and a second isentropic efficiency residual error of the power turbine, and a total pressure recovery coefficient residual error of a turbine interstage transition section; And respectively comparing each performance residual with a convergence residual, if each performance residual is lower than the convergence residual, judging that the convergence standard is met, otherwise, judging that the convergence standard is not met.
6. The method of claim 5, wherein said adapting the complete machine 0D model comprises: Determining total residual errors according to the performance residual errors, and determining correction factors of the current internal iteration step in a constraint range with the aim of minimizing the total residual errors, wherein the correction factors comprise a first conversion flow correction factor, a first expansion ratio correction factor and a first isentropic efficiency correction factor of the gas turbine, a second conversion flow correction factor and a second isentropic efficiency correction factor of the power turbine and a transition section total pressure recovery coefficient correction factor; Respectively correcting a characteristic diagram of a corresponding first performance parameter according to each correction factor, and operating the whole machine 0D model based on the corrected characteristic diagram to obtain a corrected first performance parameter, wherein the corrected first performance parameter comprises corrected first converted flow, corrected first expansion ratio, corrected first isentropic efficiency, corrected second converted flow, corrected second expansion ratio, corrected second isentropic efficiency and corrected total pressure recovery coefficient of a transition section, and the corrected second expansion ratio is determined according to the corrected first expansion ratio, the corrected total pressure recovery coefficient of the transition section and the total expansion ratio of the double-rotor turbine; Calculating performance residual errors between the corrected first performance parameters and the corresponding second performance parameters, returning to a step of determining total residual errors according to the performance residual errors, and determining correction factors of the current internal iteration step in a constraint range with the aim of minimizing the total residual errors until the current internal iteration number reaches the maximum internal iteration number.
7. The method of claim 6, wherein said determining a correction factor within a constraint range with the goal of minimizing a total residual comprises: Determining the lower limit of the constraint range according to the correction factor and the first preset variation determined in the previous internal iteration step, and determining the upper limit of the constraint range according to the correction factor and the second preset variation determined in the previous internal iteration step; And constructing an objective function by taking the minimum total residual error as a target, and solving the objective function by adopting a preset algorithm based on the constraint range to obtain a correction factor of the current internal iteration step.
8. An integrated simulation platform is characterized in that a control module, a complete machine 0D model and a double-rotor turbine 3D integrated model are deployed on the integrated simulation platform; the gas turbine of the whole machine 0D model is characterized by adopting a gas turbine characteristic diagram, the power turbine is characterized by adopting a power turbine characteristic diagram, and the total pressure loss of a turbine interstage transition section between the gas turbine and the power turbine is characterized by adopting a transition section total pressure recovery coefficient; The dual-rotor turbine 3D integrated model is constructed based on the gas turbine and the power turbine and comprises an inlet section, a first adjustable guide vane and a first movable vane corresponding to the gas turbine, a second adjustable guide vane and a second movable vane corresponding to the power turbine and an outlet section; The control module is connected with the complete machine 0D model and the dual rotor turbine 3D integrated model for executing the engine performance simulation method of any one of claims 1 to 7.
9. The integrated simulation platform of claim 8, wherein boundary conditions of an inlet section and an outlet section in the dual-rotor turbine 3D integrated model are set based on boundary conditions obtained by the complete machine 0D model, wherein the boundary conditions comprise an inlet total pressure, an inlet total temperature, an axial air inlet condition and an outlet static pressure.
10. The integrated simulation platform of claim 8, wherein rotational speeds of the first and second buckets are determined according to an operating condition of an engine, variable geometry angles of the first and second adjustable vanes are determined according to a control law of the engine, and thermophysical parameters and blade cooling parameters of the gas turbine and the power turbine are determined based on the complete machine 0D model simulation.

Description

Engine performance simulation method and integrated simulation platform Technical Field The invention relates to the technical field of engine performance test, in particular to an engine performance simulation method and an integrated simulation platform. Background The existing aeroengine performance simulation is mainly based on a zero-dimensional (0D) simulation method, and the core is to solve a nonlinear residual equation set by combining the common working conditions of continuous flow, power balance and the like through independent characteristic diagrams (derived from three-dimensional simulation or bench test of the components) of each component, so as to obtain the performances of the components and the whole machine. The method can meet basic requirements in the traditional engine with simple configuration, but with the development of the aeroengine, the limitation of the method is more remarkable, on one hand, the traditional 0D simulation independently characterizes the characteristics of the upstream and downstream components, ignores the influence of the pneumatic coupling effect between the components on the characteristics of the components and the matching characteristics of the whole machine, and on the other hand, the total pressure loss of the transition section between the components is calculated only through simple relational expressions such as the conversion flow of an outlet of the upstream component or the square of Mach number, and the evaluation result is inaccurate. Therefore, in the conventional complete machine 0D simulation method, coupling relations between components and the complete machine are weak, resulting in insufficient performance prediction accuracy. The modern aero-engine has more complex structure and component geometric characteristics, larger pneumatic load and obviously enhanced pneumatic coupling effect among components, and the traditional 0D simulation is difficult to meet the requirement of high-precision performance simulation of the advanced aero-engine, so that the risk of the design process is increased, the research and development period is prolonged and the cost is increased. Disclosure of Invention The invention provides an engine performance simulation method and an integrated simulation platform, which are used for solving the problems of weak coupling relation among components, between the components and the whole engine and inaccurate evaluation of transition section loss in the existing engine performance simulation method. The invention provides an engine performance simulation method, which is applied to an integrated simulation platform, wherein the integrated simulation platform is provided with a complete machine 0D model and a double-rotor turbine 3D integrated model, and the method comprises the steps of determining simulation conditions of the integrated simulation platform, operation conditions and control rules of a corresponding engine, operating the complete machine 0D model based on the operation conditions and the control rules to obtain first performance parameters and first boundary conditions of a double-rotor turbine, setting second boundary conditions of the double-rotor turbine 3D integrated model as the first boundary conditions, adjusting the second boundary conditions based on the first performance parameters to obtain second performance parameters of the double-rotor turbine 3D integrated model, judging whether the simulation conditions are met or not based on the first performance parameters and the second performance parameters, adjusting the complete machine 0D model if the simulation conditions are not met, returning to the step of operating the complete machine 0D model based on the operation conditions and the control rules until the simulation conditions are met, and determining the performance parameters of the complete machine and the double-rotor turbine according to the adjusted complete machine 0D model and the adjusted double-rotor turbine 3D integrated model. According to the engine performance simulation method provided by the invention, an integrated simulation platform is constructed based on the whole machine 0D model and the double-rotor turbine 3D integrated model, the whole machine 0D model is operated under the simulation conditions limited by the integrated simulation platform to obtain the first performance parameters and the first boundary conditions of the double-rotor turbine, the second boundary conditions of the double-rotor turbine 3D integrated model are set as the first boundary conditions, the second boundary conditions are adjusted based on the first performance parameters to obtain the second performance parameters of the double-rotor turbine 3D integrated model, whether the simulation conditions are met or not is judged, if the simulation conditions are not met, the whole machine 0D model is adjusted, and the whole machine 0D model is operated in a returning mode until the simulati