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

A curvature-continuous, design-aided technology, which is applied to components of pumping devices for elastic fluids, mechanical equipment, non-variable-capacity pumps, etc., can solve problems such as the selection method of Bezier curve control points for which no design parameters are disclosed.

Active Publication Date: 2013-03-27
TSINGHUA UNIV
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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

Method used

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

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Embodiment Construction

[0092] Thinking of the present invention is as follows:

[0093] 1. Calculate the leading edge point according to the tangent point between the suction surface and the small leading edge circle, and the tangent point between the pressure surface and the small leading edge circle,

[0094] 2. Carry out cubic spline fitting on the suction surface and the pressure surface, and calculate the slope of the curve at each type of value point,

[0095] 3. Use the cubic Bezier curve to give the continuous curvature of the leading edge suction side profile line and the leading edge pressure side profile line, and its control points are obtained by the given initial value selection and iterative method,

[0096] 5. Use the B-spline curve to give the curvature distribution of the suction surface, and find the control points of the B-spline curve, so that the curvature continuous suction surface corresponding to the curvature distribution curve has the smallest deviation from the original s...

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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...

Claims

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Application Information

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IPC IPC(8): F04D29/38
Inventor 宋寅顾春伟
Owner TSINGHUA UNIV
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