Computing method of revolution section profile of turbomachinery blade

Abstract

The invention discloses a computing method of a revolution section profile of a turbomachinery blade, which mainly comprises the following steps: reading in each section profile data of the blade; taking out a point at the corresponding position on each section profile and recombining the points to form a space curve l; projecting the curve to an XZ plane and a YZ plane to obtain a curve lXZ and a curve lYZ; presetting a function relational expression R=f(X) of the intersecting line of a revolution surface and a meridian plane; presetting an initial radius Rinitial to solve the coordinates of the intersecting point A of a cylindrical revolution surface the axes of which is the X-axis and the radius of which is the initial radius Rinitial and the space curve l; substituting the coordinate AX of the point A at the X-axis into the function relational expression R=f(X) of the intersecting line of the revolution surface and the meridian plane to obtain the magnitude of the radius RA which corresponds to the coordinate AX on the revolution surface; and then judging whether the point A is the intersecting point according to the absolute value of RA-Rinitial. Each solved intersecting point forms the revolution section profile of the blade. The computing method has the advantages of convenience, rapidness, high computing precision and the like.

Description

technical field [0001] The invention relates to a turbomachinery blade, in particular to a calculation method for a rotary section profile of a turbomachinery blade. Background technique [0002] S 1 and S 2 Flow surface theory is an important means of turbomachinery design, and is widely used in the design fields of gas turbines, axial flow and centrifugal compressors, steam turbines, centripetal turbines, blowers, fans, water turbines, etc. When performing calculations, S is often estimated based on the shape of the meridian flow channel of the turbomachinery 1 Surface shape, S 1 In principle, the flow surface is not a regular surface of revolution, but when the height of the blade is small relative to the radius of gyration, the surface of revolution can be used to replace S 1 Therefore, the shape of the rotary surface can be determined according to the shape of the flow channel on the meridian surface of the turbomachinery. Usually, the shape line of turbomachinery ...

AI Technical Summary

Problems solved by technology

Usually, the shape line of turbomachinery blades is given in the form of the coordinates of the section points used for processing. These sections are usually contour sections or rotary sections, but it is difficult to ensure that the coordinate points on the section to be calculated are exactly The section coordinate point given by the profile line, in this case, it is necessary to interpolate according to the known point coordinates to obtain the required blade rotation section profile line

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