Three-layer hollow blade structure and manufacturing method thereof

Abstract

The invention relates to a three-layer hollow blade structure and a manufacturing method thereof. The method comprises the steps of machining multiple bosses on the inner surfaces of skin at the two sides through a mechanical machining or chemical processing method; coating the parts, except the bosses, on the inner surfaces of the skin with a diffusion bonding separating agent; machining inclinedcutting core plates with the variable cross-section thickness through a mechanical machining or chemical processing method; machining air inlet grooves in the thickness reducing ends of the inclinedcutting core plates; clamping the middle core plates between the skin at the two sides with the bosses, and conducting welding and edge sealing on the peripheries of a formed three-layer laminating structure; putting the three-layer laminating structure subjected to combined edge sealing into a hot isobaric furnace for diffusion bonding after vacuum encapsulation, so that the middle core plates and the skin at the two sides are connected at the bosses; filling the three-layer laminating structure after diffusion bonding with inert gas for super-plastic forming through the air inlet grooves inthe core plates, so that the core plates bulge with a non-diffusion-bonding area, except the bosses, of the skin and fit the molded surface of a super-plastic forming die.

Description

technical field [0001] The invention relates to the technical field of manufacturing aeroengine blades, in particular to a three-layer hollow blade structure and a manufacturing method thereof. Background technique [0002] Super plastic forming / diffusion bonding (SPF / DB) technology is known as a pioneering technology in the modern aviation industry, which largely increases the utilization of aerospace materials and improves the reliability of structures and maintainability. As an advanced manufacturing technology, the SPF / DB combination process breaks through the traditional sheet metal forming method, which can save cost and weight, and realize near-no margin forming. It has obvious advantages in manufacturing complex shapes and multi-layer structures. [0003] Aeroengine blades are thin-walled and easily deformable parts, and the manufacturing process of the blade profile has a direct impact on engine performance. In the existing technology, the three-layer hollow blade...

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Problems solved by technology

[0005] The embodiment of the present invention provides a three-layer hollow blade structure and its manufacturing method. By partially thickening the inner surface of the skin and adopting a core plate with a variable cross-section and thick bottom, groove defects are avoided, and at the same time, problems caused by thinning the core plate are solved. The problem of overall performance degradation when

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