Three-layer hollow blade structure and manufacturing method thereof

A technology for hollow blades, manufacturing methods, applied in the direction of supporting elements of blades, engine elements, machines/engines, etc., which can solve the problems of overall performance reduction and achieve an effect that is conducive to thinning

Active Publication Date: 2018-11-27
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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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

Method used

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  • Three-layer hollow blade structure and manufacturing method thereof
  • Three-layer hollow blade structure and manufacturing method thereof
  • Three-layer hollow blade structure and manufacturing method thereof

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Embodiment Construction

[0032] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The detailed description and accompanying drawings of the following embodiments are used to illustrate the principles of the present invention, but cannot be used to limit the scope of the present invention, that is, the present invention is not limited to the described embodiments, without departing from the spirit of the present invention Any modification, substitution and improvement of parts, components and connection methods are covered under.

[0033] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0034] Figure 1(a) and Figure 1(b) are schematic diagrams of the interaction force between the s...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00F01D5/14F01D5/18B23P15/04
CPCB23P15/00B23P15/04F01D5/14F01D5/147F01D5/18
Inventor 杜立华李志强韩晓宁邵杰韩秀全黄京东
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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