Root extending segment appearance parameterization design method of turbine air-cooling moving blade

Abstract

The invention provides a root extending segment appearance parameterization design method of a turbine air-cooling moving blade. A root extending segment appearance section line set capable of being parameterized is built, an auxiliary geometry body is acquired, a bridging curve is built, the free-form surface of the root extension segment appearance is acquired through the covering method, other planes of the root extending segment appearance are acquired through the boundary control method, a formed sealed root extending segment appearance curve body is converted to an entity, and a final root extending segment appearance entity is acquired. Through the method, the complex root extending segment appearance modeling problem is converted to a plurality of problems of surface modeling, the auxiliary geology body is built, and the continuity of the root extending segment appearance curve and a tenon appearance curve on the boundary G1 is achieved accordingly; because root extending segment appearance section lines capable of being parameterized are built, the root extending segment appearance is more scientific and reasonable in design, and the method can be better applied to the engineering design field.

Description

technical field [0001] The invention relates to the field of shape design of a root section of a turbine air-cooled moving blade, in particular to a parametric design method for the shape of a root section of a turbine air-cooled moving 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 moving blades with air-cooling structure are the most complex. In addition to the complex inner cavity structure, there is also a section of root structure between the edge plate and the tenon. It is a very complicated and cumbersome process to comprehensively consider factors such as inner cavity air flow, strength, turbine disk and tenon structure, and blade weight in the design of the root section structure. [0003] Relevant domestic personn...

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Problems solved by technology

[0005] The purpose of the present invention is to propose a parametric design method for the shape of the root extension section of the turbine air-cooled moving blade in view of the current situation of insufficient research on the shape of the root extension of the existing blade. Curve operations such as edges and other curves are used to construct parametric root profile section line groups, and then stretched to obtain the auxiliary geometry required in the process of constructing the root profile, and then create a bridge curve group, a

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