Compressor and blade, two-dimensional blade design method of blade, computer equipment

Abstract

Provide a compressor and blades, a two-dimensional airfoil design method, computer equipment, and a two-dimensional airfoil design method for a compressor. The compressor is an axial flow compressor. In the design steps of the two-dimensional airfoil design method, along the The thickness distribution in the normal direction of the mid-arc line is superimposed to generate the suction surface and the pressure surface. The construction of any one of the suction surface thickness curve and the pressure surface thickness curve includes defining five position points, a curve connecting the five position points, and the suction surface thickness curve. The first derivative is continuous with the pressure surface thickness curve at five points and the second derivative is continuous at the maximum thickness point. According to the existing constraints, the four-segment curve is calculated and determined to obtain the suction surface thickness curve or the pressure surface thickness curve; A curve, keeping the first derivative of each thickness curve continuous at the front connection point and the middle arc of the two-dimensional airfoil unchanged, the first curve of the suction surface thickness and pressure surface thickness curve is adjusted to an asymmetric curve to improve the angle of attack characteristics.

Description

technical field [0001] The invention relates to a compressor, a blade, and a two-dimensional blade design method for the blade, and also relates to computer equipment for the auxiliary design method. Background technique [0002] Axial flow compressor is a multi-stage compression equipment in which the flow direction of the air flow is consistent or nearly consistent with the direction of the rotating axis of the working wheel. It is composed of a series of stators and rotors arranged alternately, and is often used in aero-engines or gas turbines. The blade of the axial flow compressor is an important part of the airflow channel of the compressor to realize the conversion of the airflow function and change the direction of the airflow. The leaf shape (Cascade) of the blade is the basic unit of the blade, and the blade is formed by stacking the leaf shape along the stacking line. [0003] Aeroengine blades have the characteristics of complex blade surface, large blade body t...

AI Technical Summary

Problems solved by technology

In order to improve the characteristics of the angle of attack, it is usually necessary to update the center arc and the thickness distribution curve. There are many adjustment parameters, and the adjustment of the center arc will cause obvious changes in the geometry of the entire airfoil.

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