Aviation blade forming tool and process based on carbon-ceramic material

A technology for aviation blades and forming tooling, applied in the field of aviation blade molds, can solve the problems of difficult processing of air film grooves, eccentric mold positioning, etc., and achieve the effect of easy processing and accurate positioning

Active Publication Date: 2021-04-02
XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a carbon-ceramic material-based aviation blade molding tooling and process, which solves the problems of eccentric mold positioning and difficult processing of air film grooves in the molding process when using existing molding molds

Method used

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  • Aviation blade forming tool and process based on carbon-ceramic material
  • Aviation blade forming tool and process based on carbon-ceramic material
  • Aviation blade forming tool and process based on carbon-ceramic material

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Embodiment Construction

[0063] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0064] like figure 1 As shown, it is a schematic diagram of the structure of the blade to be processed in this embodiment, and it can be seen that a plurality of air film holes 01 are opened thereon. figure 2 It is a schematic diagram of the fiber fabric structure, and a plurality of air film holes are correspondingly opened on it. Because the opening size of the air film hole is generally less than 10*10mm, the depth is about 30mm, and the profile is a curved surface, it cannot be processed by a tool holder. Therefore the present invention designs a kind of forming tooling, utilizes forming tooling in the process of wrapping the fiber fabric with the surface of the inner mold, processes the air film groove at the corresponding part of the fiber fabric, and the air film hole is naturally formed during the blade forming process.

[0065] to c...

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Abstract

The invention provides an aviation blade forming tool and a process based on a carbon-ceramic material, and solves the problems of mold positioning eccentricity and difficulty in air film groove machining after forming in the forming process by adopting an existing forming mold. A forming tool comprises an inner die, an outer die, a clamping plate assembly and a limiting tool. The clamping plate assembly is used for being matched with the inner die and the outer die to achieve positioning of the inner die and the outer die. The limiting tool is used for machining an air film groove in the corresponding portion of the fiber fabric in the process that the fiber fabric is wrapped by the molded surface of the inner die. In the machining process, the relative positions of the air film grooves and the relative positions of the air film grooves and the fiber fabric are accurately positioned through the limiting tool, and blade scrapping caused by errors caused by manual measurement is prevented; the relative positions of the inner die and the outer die are fixed through the clamping plate assembly, and the situation that due to relative sliding of the inner laminated and the outer die inthe forming process, the fiber fabric profile (wall thickness and curvature) is changed, and later blade machining operability and blade performance are affected is prevented.

Description

technical field [0001] The invention relates to an aviation blade mold made of carbon ceramic material and a method for preparing blade structural components using the mold. Background technique [0002] The blade is an important part of the aero-engine, and it is an important part of the aero-engine that is subjected to severe working stress, high temperature and high pressure. Its development technology and manufacturing level have an important impact on the performance of the engine. [0003] SiC / SiC composite material and C / SiC composite material are a new type of thermal structure / function integrated strategic material with low density, high temperature resistance, high specific strength, high specific modulus, oxidation resistance, ablation resistance, and insensitivity to cracks , No catastrophic damage and other characteristics, widely used in key fields such as aviation, aerospace, nuclear power, photovoltaics, etc. [0004] The fibers in carbon-ceramic structural ...

Claims

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Application Information

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IPC IPC(8): C04B35/571C04B35/622C04B35/80
CPCC04B35/571C04B35/622
Inventor 康志杰苏海龙李仁意张少博马文科陈静
Owner XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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