CAD (Computer-Aided Design) aided design method of controllable diffused blade profile with curvature continuity

Abstract

The invention relates to a CAD (Computer-Aided Design) aided design method of a controllable diffused blade profile with curvature continuity, which belongs to the field of design of a compressor blade. The method is characterized by comprising the steps of respectively solving a leading edge point by using the point of tangency of a pressure surface, a suction surface and a small circuit at the leading edge; fitting with a cubic spline to solve the curvature of each data point on the suction face and the pressure surface; solving a side profile of the suction face and a side profile of the pressure surface of the leading edge with curvature continuity by a cubic Bezier curve; giving the curvature distribution of the suction face by a B spline curve to solve a control point of the B spline curve, so that the deviation between the profile of the suction face with curvature continuity and the original profile of the suction face corresponding to curve distribution is minimum; and solving the position of the small circle at a tail edge of the optimized blade profile. Compared with the original controllable diffused blade profile, the range of the angle of attack is expanded by 2.5 degrees, and the pitot loss in a low loss area is reduced.

Description

technical field [0001] The invention relates to an optimal design method for compressor blades. Background technique [0002] Compressor is one of the important components of aero-engine and gas turbine, and the airfoil design is the key link of compressor design. Early compressor airfoils used series airfoils (such as NACA-64 series, C-4 series, etc.). In the 1950s and 1960s, the controllable diffusion airfoil began to be widely used in compressors. Compared with the traditional series of airfoils, it can better control the diffusion, suppress the separation of the boundary layer, and reduce the excitation at high Mach numbers. Wave loss, so it can reduce the surface loss, expand the angle of attack range, and it is easy to match in a multi-stage environment. With the increasing load of the compressor stages, the development of high-load, high-efficiency, and high-reliability compressors puts forward higher requirements for the loss of the airfoil and the range of the ang...

AI Technical Summary

Problems solved by technology

Song Yin et al.’s paper “Design of Compressor Blade Leading Edge with Continuous Curvature and Its Influence on Aerodynamic Performance” proposed to use cubic Bezier curves to define the suction side and pressure side of the leading edge, but did not disclose the design parameters or How to select control points of Bezier curve

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