Design method of ceramic-based turbine rotor blade prefabricated body

Abstract

A design method for a ceramic-based turbine rotor blade preform, including a modular component design of the turbine blade preform and a method for laying up SiC fiber cloth in each modular component. The modular components of the turbine rotor blade preform include: the main body splitting component, the upper outer sealing component and the lower outer sealing component of the CMC turbine rotor blade prefab. The modular layup design method of the CMC turbine blade prefab can extract the airfoil profile parameters for the turbine blade with spatial twist and complex shape, and then realize the structural design of the turbine blade prefab. The SiC fiber layup structure in each modular component can be unfolded on a two-dimensional plane, which is conducive to the cutting and forming of SiC fiber cloth in practice, thereby realizing a simple, accurate and reliable near-net-shape operation of CMC turbine blade preforms .

Description

technical field [0001] The invention belongs to the design field of ceramic matrix composite (CMC, ceramic matrix composite) aero-engine turbine blade preforms, and in particular relates to a modular laying of complex-shaped turbine rotor blade preforms by using silicon carbide (SiC) fiber cloth layer design method. Background technique [0002] CMC has the characteristics of light weight, high modulus, high tensile strength, good vibration absorption and good temperature resistance, and its density is only 1 / 4~1 / 3 of nickel-based alloys. will decrease, even higher than at room temperature (see Wen Shengqiong and He Aijie, Application of CMC in Aero-Engine Hot-End Components. Aviation Manufacturing Technology, 2009(S1): pp. 4-7.). At present, the most widely used CMC is mainly carbon fiber toughened silicon carbide (C f / SiC) and silicon carbide fiber toughened silicon carbide (SiC) f / SiC), these two materials have excellent properties such as high temperature strength, ...

AI Technical Summary

Problems solved by technology

[0005] Most of the layered composite materials involved in the field of aero-engines focus on the description of the laminated structure and the realization of the manufacturing process (see Chinese patent CN107074668A "Manufacturing method of ceramic matrix composite materials"), and at the beginning of the design, combined with the prefabricated body Extensive research on structural optimization and layup design is lacking

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