Three-dimensional matching iteration method for aero-engine

Abstract

The invention belongs to the technical field of three-dimensional simulation, and particularly relates to a three-dimensional matching iteration method for an aero-engine which is characterized in that on the basis of existing three-dimensional simulation software of all parts of the engine, steady-state calculation results of all the parts are recycled, a balance equation deviation function is constructed and solved, and boundary conditions of all the parts are updated; the invention aims to solve the technical problems of low matching iterative calculation precision, low efficiency, poor convergence and the like in the technical scheme of three-dimensional steady-state simulation of the whole machine, and provides an effective new method which can truly and effectively reflect the three-dimensional flow field of the engine and is suitable for engineering application.

Description

technical field [0001] The present application belongs to the technical field of three-dimensional simulation, and in particular relates to an iterative method for three-dimensional matching of an aero-engine. Background technique [0002] In the design of aeroengines, simulation technology can effectively promote the advance research of engines, verify the design results, reduce design defects and design process repetition. The 3D simulation of the whole machine more accurately simulates the real working environment of each component of the engine. Compared with the zero-dimensional simulation of the whole machine, the three-dimensional simulation can obtain the internal flow field distribution of each component, the interface of the components is a surface field distribution instead of an average value, the distortion of the flow field information is small, and the boundary conditions are closer to the real flow conditions, thereby improving Machine simulation accuracy. ...

AI Technical Summary

Problems solved by technology

However, the flow conditions of each component are different. For example, the main combustion chamber of the engine is generally a constant-pressure combustion, which can be regarded as an incompressible fluid; the compression and expansion of the gas by the fan / compressor and the high / low pressure turbine mainly involve compressible fluid. solution, so the same computational model and turbulence model are not applicable

[0006] (2) Low computational efficiency

For example, in the three-dimensional calculation of the whole machine, the flow of the main combustion chamber components is the most complicated, requiring denser meshes and smaller iteration steps. The calculation efficiency of other components is low and takes up a lot of computing resources

[0007] (3) Computational convergence difference

However, the component boundary conditions are the average value of the overall calculation, and the influence between the components is not considered. The characteristic correction iteration between the overall and the components takes a long time, and the calculation efficiency and accuracy are not applicable in the design.

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