A visualization method for unsteady flow of aero-engine compressor

Abstract

The invention discloses a method for visualizing the unsteady flow of an aero-engine compressor, comprising the following steps: taking a single-channel grid as an input and output full-ring grid, and marking the compressor blade row where each grid block is located; The grid blocks are distributed to different processes. When the flow field is stored, each process outputs the flow field on the grid block it has obtained separately, and creates a folder for each leaf row; reads the data of each leaf row in turn. Flow field data, calculate flow field parameters; output flow field visualization file according to the interface standard of visualization software Tecplot. The invention has the ability to visualize the unsteady mass flow field data of the multi-stage compressor on a single machine; the invention has the ability to extract and independently process any blade row in the multi-stage compressor; the invention has the ability to automatically extract the two-dimensional section. capability and the ability to reduce flow field file size by about an order of magnitude.

Description

technical field [0001] The invention relates to a method for visualizing unsteady flow of an aero-engine compressor, which belongs to the technical field of aeronautical aircraft. Background technique [0002] In the design and modification process of aero-engine compressors, multiple compressor geometries will be introduced for selection. At this time, it is necessary to evaluate the global aerodynamic performance and internal flow details of different shapes to provide a reference for selection. The details of the internal flow of the compressor are extremely rich, among which the leakage flow at the tip, the flow in the corner area, the unsteady interference between the blade rows, the pressure distribution of the blade, the shock wave / boundary layer interference on the blade, etc. directly affect the local performance of the compressor blade. And indirectly affect the overall aerodynamic performance of the compressor. Through visualization of compressor flow details, th...

AI Technical Summary

Problems solved by technology

[0005] 1) The PIV method, also known as the particle image velocimetry method, mainly measures the velocity distribution information of the spatial flow field, but cannot obtain information such as the density and pressure of the air inside the compressor, and for the relatively closed internal space of the compressor, the dense blade distribution, High-speed blade rotation and other conditions greatly affect the effect of PIV, and the equipment is expensive and the cost is high;

[0006] 2) The porous probe is inserted into the compressor, which can measure the velocity, direction, total pressure and static pressure of the flow field inside the compressor, but cannot test the information of the flow area of ​​the rotor, and other components are added to the compressor. Objects will affect the authenticity of the flow field, and the design and processing of the seven-hole probe is difficult

[0008] 1) The global flow information file is too large to be displayed on a single machine

Due to the large number of stages in the whole compressor, the total size of the coordinate information and basic flow information files of the unsteady flow of the whole ring at a certain moment is nearly 100G, which is far beyond the memory size of ordinary stand-alone machines, and cannot be displayed on a stand-alone machine , only by processing and outputting pictures or data on a supercomputer, the operation is complicated, the operation efficiency is low, it is not intuitive enough, and it is not flexible enough;

[0009] 2) It is impossible to output the coordinate information and flow information of the interested compressor blade row separately, and it is also impossible to output the coordinate information and flow information of some section planes of a certain blade row or several blade rows separately, and it is also impossible to output only the interested flow variable;

[0010] 3) Lack of a solution to reduce the size of the global flow information file

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