Two-dimensional blade profile optimization method for compressor considering low Reynolds number working performance

Abstract

The invention relates to a two-dimensional blade profile optimization method for a compressor considering a low Reynolds number working performance; the optimization method is characterized by comprising the following steps of: step 1: analyzing the meridional flow performance of a prototype multistage axial flow compressor at different rotating speeds; step 2: determining a key two-dimensional blade profile section to be optimized; step 3: performing parametric fitting to the key two-dimensional blade profile in step 2; step 4: analyzing the aerodynamic performance of the two-dimensional blade profile, and analyzing the aerodynamic performance of the parameterized two-dimensional blade profile to obtain the variable attack angle performance of the blade profile under a low Reynolds numberworking condition and the variable attack angle performance under a high Reynolds number working condition; and step 5: optimizing the modeling parameters of the two-dimensional blade profile, adjusting the two-dimensional modeling parameters according to the variable attack angle performance parameters of the two-dimensional blade profile obtained in step 4 at different Reynolds numbers, using agenetic algorithm to circularly iterate steps 3 and 4 until a two-dimensional blade profile design reducing loss and increasing stall margin is obtained, and then obtaining a new two-dimensional blade profile. According to the invention, the performance optimization of the two-dimensional blade profile of the axial flow compressor at different Reynolds numbers and different attack angles is realized; the designed working performance of the compressor is improved while the aerodynamic performance of the compressor at the low rotation speed working condition is improved; and the flow efficiencyis improved while the normal starting and stable working of the compressor are ensured.

Description

technical field [0001] The invention relates to an optimal design method of a two-dimensional airfoil, in particular to a two-dimensional airfoil optimal design method of a compressor that takes into account the low Reynolds number performance. The invention belongs to the field of axial flow impeller machinery. Background technique [0002] The aerodynamic performance of the axial flow compressor not only refers to the aerodynamic performance of the compressor at the design speed, such as pressure ratio, efficiency, surge margin, etc.; it also includes the aerodynamic performance of the compressor during the starting process. During the starting process, the operating speed of the compressor is lower than the design speed, and there are often stall clusters in the main flow channel, and the surge margin is low. How to ensure the surge margin of the compressor at low speed and ensure the normal operation of the compressor? Getting started is crucial. [0003] The two-dimen...

AI Technical Summary

Problems solved by technology

When the inlet Reynolds number of the diffuser cascade decreases, the usual two-dimensional airfoil will show performance changes such as increased loss and decreased stall margin, which will affect the aerodynamic performance of the compressor at low speed

But at present, most of the two-dimensional airfoil optimization methods only focus on the aerodynamic performance of the airfoil under the design condition (that is, the high Reynolds number condition), while ignoring the performance requirements of the two-dimensional airfoil under the low Reynolds number.

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