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Aero-engine stator assembly vacuum electron beam welding technology

A vacuum electron beam and aero-engine technology, applied in electron beam welding equipment, welding equipment, manufacturing tools, etc., can solve problems such as excessive welding deformation of stator components, and meet the requirements of post-weld performance stability, uniform heat input, Controlling the effect of weld distortion

Active Publication Date: 2015-04-01
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0005] Aiming at the problems existing in the prior art, the present invention provides a vacuum electron beam welding process for the stator assembly of an aero-engine, which can meet the performance stability requirements of the stator assembly after welding, and can effectively solve the problem of excessive welding deformation of the stator assembly

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  • Aero-engine stator assembly vacuum electron beam welding technology

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Embodiment Construction

[0025] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0026] The stator assembly used for welding is made of TC4 titanium alloy material, and its weld seam is a weld seam of unequal thickness. is 16°, the number of welds is 138, and the welding machine used is a vacuum electron beam welding machine.

[0027] A vacuum electron beam welding process for the stator assembly of an aero-engine comprises the following steps:

[0028] Step 1: Select the deformation allowance of the stator assembly parts before welding

[0029] ① In order to reduce the axial and radial deformation of the mounting edge during welding and improve the rigidity of the mounting edge, a margin of 2mm is left in the axial and radial directions of the mounting edge;

[0030] ②Because the stator assembly has welds of unequal thickness, in order to reduce the thickness difference and ensure the flatness of the weld, a ma...

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Abstract

The invention discloses an aero-engine stator assembly vacuum electron beam welding technology and belongs to the technical field of aero-engine part manufacturing. Formerly, an aero-engine stator assembly is welded through a brazing method, the brazing intensity is lower than the base metal intensity, the stator assembly performance stability is directly influenced, and a traditional welding method is excessively large in welding deformation. Compared with the prior art, after a large amount of soldering tests, the aero-engine stator assembly vacuum electron beam welding technology has the advantages that welding of the aero-engine stator assembly can be completely satisfied, brand new welding parameters are provided, the welding parameters are obtained after a large amount of welding parameter tests, welding of different thickness weld joints can be satisfied maximally, and thermal input is guaranteed uniform, the welding deformation is effectively controlled, and the requirement for stable postwelding performance of the stator assembly is satisfied due to sequence welding of the two weld joints at symmetrical positions.

Description

technical field [0001] The invention belongs to the technical field of aero-engine component manufacturing, in particular to a vacuum electron beam welding process for an aero-engine stator assembly. Background technique [0002] In the past, the aero-engine stator assembly was welded by brazing, and the strength of the brazing seam was lower than that of the base metal, which would directly affect the performance stability of the stator assembly. However, if the traditional welding method was used for welding, there would be welding problems. The problem of excessive deformation, in order to achieve the stability of the performance of the stator assembly after welding, and to avoid the problem of excessive welding deformation, relevant technical personnel try to use the existing vacuum electron beam welding process to meet the welding requirements of the stator assembly. . [0003] However, the applicable part of the existing vacuum electron beam welding process method is ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23K15/00
CPCB23K15/0033B23K15/04
Inventor 葛沁杨涧石李文学曲伸李英
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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