Multi-point synchronous hot-torsion forming device and forming method for hollow blade

A hollow blade and blade technology, which is applied to the field of multi-point synchronous hot torsion forming devices for hollow blades, can solve the problems of lack of auxiliary limit of clamps and uneven deformation of the blade body, and shorten the finishing forming time and the high temperature residence time of the blade. The effect of improving part quality and saving mold manufacturing costs

Active Publication Date: 2018-02-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a hollow blade multi-point synchronous thermal torsion forming device and forming method to solve the lack of fixtures in the conventional chuck torsion, mold push-bending forming and multi-section synchronous torsion. Auxiliary limit and uneven deformation

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  • Multi-point synchronous hot-torsion forming device and forming method for hollow blade
  • Multi-point synchronous hot-torsion forming device and forming method for hollow blade
  • Multi-point synchronous hot-torsion forming device and forming method for hollow blade

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Embodiment Construction

[0036] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

[0037] refer to figure 1 As shown, a hollow blade multi-point synchronous thermal torsion forming device of the present invention includes: a blade tenon clamping device, a multi-point push rod punch device and a heating device; wherein,

[0038] like Figure 4a , Figure 4b As shown, the blade tenon clamping device includes: blade+x side tenon clamping device pressure plate 14, blade tenon clamping device fixed base 15, blade-x side tenon clamping device pressure plate 18, pressure plate nut A34, pressure plate spacer A35, Pressure plate screw A36, pressure plate bottom fixing nut A37, pressure plate nut B38, pressure plate spacer B39, pressure plate screw B40, pressure plate bottom fixin...

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Abstract

The invention discloses a multi-point synchronous hot-torsion forming device and forming method for a hollow blade. The multi-point synchronous hot-torsion forming device comprises a blade tenon clamping device, a multi-point pushing rod punch device and a heating device. According to the multi-point synchronous hot-torsion forming device and forming method for the hollow blade, precise control over torsional deformation of a blade body can be achieved through multi-point synchronous loading heat torsion, and meanwhile the mold manufacturing cost can be greatly reduced by applying a flexible tool composed of height-adjustable basic bodies which are arranged in a dot-matrix mode.

Description

technical field [0001] The invention belongs to the technical field of hollow blade torsion forming, and specifically refers to a hollow blade multi-point synchronous thermal torsion forming device and forming method. Background technique [0002] Aeroengine hollow blades are usually composed of skins on both sides and a reinforced structure in the middle, which can greatly improve the performance of the engine compared with solid structure blades. At the same time, according to the aerodynamic requirements of the engine blade, the blade body is usually designed as a variable cross-section structure with a large twist angle. [0003] Titanium alloy hollow blade forming usually includes several processes of diffusion bonding, twisting and finishing forming. At present, the common torsion forming process of equal-thickness solid blades is to clamp the blades by torsion fixtures, fix the blades with tenons, and realize the torsional deformation of the blade body through the ro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21D11/14B21D11/22B21D37/16B21D53/84
CPCB21D11/14B21D11/22B21D37/16B21D53/84
Inventor 陈明和王宁谢兰生叶建华巩云峰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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