An unsteady flow visualization method for an aero-engine compressor

Abstract

The invention discloses an aero-engine compressor unsteady flow visualization method which comprises the following steps: taking a single-channel grid as an input/output full-ring grid, and marking acompressor blade row where each grid block is located; Distributing all the grid blocks to different processes, independently outputting the flow field on the distributed grid blocks by each process when the flow field is stored, and establishing a folder for each leaf row; sequentially reading the flow field data of each blade row, and calculating flow field parameters; and outputting a flow field visualization file according to the interface standard of the visualization software Tecplot. The system has the capability of visualizing unsteady mass flow field data of the multi-stage compressoron a single machine; the multi-stage compressor has the capability of extracting and independently processing any blade row in the multi-stage compressor; the method has the capability of automatically extracting the two-dimensional tangent plane and the capability of reducing the size of the flow field file by about one order of magnitude.

Description

technical field [0001] The invention relates to an unsteady flow visualization method of an aero-engine compressor, which belongs to the technical field of aero-vehicles. Background technique [0002] In the design and modification process of aero-engine compressors, multiple compressor geometric shapes are available for selection. At this time, it is necessary to evaluate the global aerodynamic performance and internal flow details of different shapes to provide reference for model selection. The internal flow details of the compressor are extremely rich, among which the tip leakage flow, corner flow, unsteady interference between blade rows, blade pressure distribution, shock wave / boundary layer interference on the blade directly affect the local performance of the compressor blade, And indirectly affect the overall aerodynamic performance of the compressor. Through the visualization of compressor flow details, these flow details can be evaluated intuitively. [0003] At...

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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