Rapid prototyping and investment casting combined dewaxing method facing turbine blade

Abstract

The invention relates to a rapid prototyping and investment casting combined dewaxing method facing a turbine blade. The method includes the steps that an internal structure of a mould core is designed according to the appearance of the turbine blade, closed small gas chambers are established in the internal structure of the mould core through the characteristic that the expansion coefficient of air is different from the expansion coefficient of a rapid prototyping material, the small gas chambers are connected with external large gas chambers through supporting rib plates, the structure design is completed, and a digital file is generated at the same time; operation is conducted on a three-dimensional model of the mould core of the turbine blade, a mould core entity of a resin material is printed through a laser rapid prototyping machine, and surface treatment is conducted at the same time for standby application; slurry dipping, sand spreading and drying hardening treatment are conducted on the mould core structure subjected to rapid prototyping, and a mould shell is obtained; and the obtained mould shell is heated, the large gas chambers communicate with the outside world at a sprue gate, and the mould shell meeting the requirement is rapidly obtained with high quality. By means of the scheme mentioned above, the problem that the ceramic mould shell expansion breakage rate in dewaxing is too high when an additive manufacturing material is used as a wax mould is effectively solved.

Description

technical field [0001] The invention relates to the field of investment casting, in particular to a melting and loss investment method combining rapid prototyping and investment casting for turbine blades. Background technique [0002] With the improvement of computer-aided design technology for turbine blades, the design technologies of curved, wide, swept, twisted and thin blades are becoming mature. The early blades were narrow chords, and there were damping shoulders (vibration-absorbing bosses) protruding to both sides at 1 / 3 of the blade body from the blade tip. The shoulders pressed against each other to form a reinforcing ring between the blades. In terms of performance and technology, solid blades with shoulders do not meet the performance requirements of larger thrust engines on blades. One of the reasons is that the airflow will be separated when it flows through the shoulder, which reduces the airflow efficiency and the weight of the solid blade is too large; th...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a combination of rapid prototyping for turbine blades and investment casting method for melting and loss, which can effective...

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