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Clamp for near net shaping of ceramic matrix composite material turbine guide vane of aeroengine

A turbine guider and aero-engine technology, which is applied in the field of aero-engine parts manufacturing, can solve the problems of ceramic matrix composite material turbine guider blade preparation failure, difficulty in ensuring the shape and size of ceramic matrix composite material blades, and protrusions, etc., to achieve improved Effects on preparation quality and production efficiency

Active Publication Date: 2017-10-20
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During the preparation process of the CVI deposition interface layer of the blade preform and the initial stage of matrix densification, because the blade preform is not tooled, it is difficult to guarantee the shape and size of the ceramic matrix composite blade, and defects such as warping, twisting, and protrusions will occur , resulting in the failure of the preparation of ceramic matrix composite turbine guide blades

Method used

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  • Clamp for near net shaping of ceramic matrix composite material turbine guide vane of aeroengine
  • Clamp for near net shaping of ceramic matrix composite material turbine guide vane of aeroengine
  • Clamp for near net shaping of ceramic matrix composite material turbine guide vane of aeroengine

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Embodiment Construction

[0023] The present invention will be further described below in conjunction with accompanying drawing, protection scope of the present invention is not limited to the following:

[0024] Such as Figure 3~11 Shown, a kind of fixture for near-net shape of turbine guider blade of aeroengine ceramic matrix composite material, it comprises large edge plate module 4, small edge plate module 5, blade back airfoil module 6 and blade pot airfoil module 7, so The top of the large edge plate module 4 is provided with a cavity A8 that matches the large edge plate 3 of the blade prefabricated body. The large edge plate module 4 is also provided with a blade back positioning block 9 and a blade back positioning block respectively located on the left and right sides of the cavity A8. The pot positioning block 10, the leaf back positioning block 9 is located on the front side of the leaf pot positioning block 10, the bottom of the small edge plate module 5 is provided with a cavity B11 match...

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Abstract

The invention discloses a clamp for near net shaping of a ceramic matrix composite material turbine guide vane of an aeroengine. A cavity A (8) matched with a vane perform large marginal plate (3) is formed in the top of a marginal plate module (4); a cavity B (11) matched with a small marginal plate (2) is formed in the bottom of a small marginal plate module (5); a curved surface (12) matched with a vane back airfoil profile (21) is arranged on the rear side of a vane back airfoil profile module (6); and a protrusion (14) matched with a vane basin airfoil profile (22) is arranged on the front side of a vane basin airfoil profile module (7). The clamp disclosed by the invention has the beneficial effects that no or less allowance processing of the working surface of a finished vane and quick disassembly and assembly are ensured, near net shaping of the ceramic matrix composite material turbine guide vane is effectively realized, and the manufacturing cost is low.

Description

technical field [0001] The invention relates to the technical field of aero-engine component manufacturing, in particular to a near-net-shaping fixture for an aero-engine ceramic-matrix composite material turbine guide vane. Background technique [0002] As one of the most critical parts of the aero-engine, the ceramic matrix composite turbine guide vane, because the working environment of the turbine guide vane is very harsh, the highest temperature, strong thermal corrosion, and the most severe thermal shock, and the ceramic matrix composite material is With excellent properties such as low density, high specific strength, high specific stiffness, and good high temperature resistance, it is most likely to replace the high temperature material of the turbine guide blade used by the nickel-based superalloy at a higher temperature as a ceramic matrix composite material. Ceramic matrix composites generally refer to carbon fiber reinforced carbon matrix (C / C) composite material...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80
CPCC04B35/80
Inventor 张铀张良成赖智卢才军郭双全刘俊伶叶勇松彭中亚黄璇璇姚改成何勇徐春
Owner PLA NO 5719 FACTORY
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