Parameterization modeling method for turbine blade root extension segment profile

Abstract

The invention provides a parameterization modeling method of a turbine blade root extension segment profile. The method comprises the steps of firstly, dividing a blade body profile curved surface of a blade and a tenon profile curved surface, then dividing the divided front edge and rear edge curved surfaces of a blade body and the front edge and rear edge curved surfaces of a tenon, constructing a blade basin control curved surface and a blade back control curved surface, and finally constructing and sewing the blade basin and blade back control curved surfaces, the blade body profile curved surface and the tenon profile curved surface into a root extension profile extended curved surface. Through the use of the method, at least G1 continuation is achieved at the connection positions among the root extended profile, a blade body profile and a tenon profile, and G2 continuation can be achieved at the interior, thus being capable of generating a segment of a smoothier root extended profile. Furthermore, four B sample strip control curved surfaces generated through reverse calculation of a transition section is changed through changing the proportion of the front edge and rear edge curved surfaces so as to control section curves and ridge lines of the blade basin curved surface and the blade back curved surface of the root extended profile, thus adjusting the whole root extended profile so as to obtain a satisfactory shape.

Description

technical field [0001] The invention relates to the technical field of turbine blade internal profile design, in particular to a parametric modeling method for the internal profile of a root section of a turbine blade. Background technique [0002] Aeroengine blades are the key components of aeroengines, which have the characteristics of complex structure, many varieties, large quantities, great influence on engine performance, and long design and manufacturing cycle. Among the aeroengine blades, the turbine blade with air-cooling structure is the most complex. In addition to the complex inner cavity structure, there is also a root section (middle blade root) structure with a complex shape between the blade body and the tenon. In the design of the root section structure, factors such as the airflow rate, strength, turbine disk and tenon structure, and blade weight should be considered comprehensively, which is a very complicated and tedious design process. [0003] Relevant...

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Problems solved by technology

[0004] The existing design method of the extension section is mainly designed for a specific model. The inner shape of the root is directly interpolated by two closed curves, a section line on the inner shape of the blade body and a top section line of the inner shape of the tenon, to generate a closed curved surface. The shape characteristics of the tenon and tenon are quite

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