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Vacuum electronic beam welding method for titanium-alloy rotor component

A vacuum electron beam and electron beam welding technology, which is applied in the direction of electron beam welding equipment, welding equipment, welding/welding/cutting items, etc., can solve the problem of high coaxiality requirements, weld seam porosity easily exceeds the standard, and the number of weld seams is large, etc. question

Active Publication Date: 2014-09-24
HARBIN DONGAN ENGINE GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the product has the characteristics of poor overall rigidity, high coaxiality requirements, strict assembly clearance, and a large number of welds, it is difficult to guarantee the overall coaxiality of the product after welding, and the pores of the welded seam are easy to exceed the standard

Method used

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  • Vacuum electronic beam welding method for titanium-alloy rotor component
  • Vacuum electronic beam welding method for titanium-alloy rotor component
  • Vacuum electronic beam welding method for titanium-alloy rotor component

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0057] The compressor rotor of an aero engine is made of TC11 titanium alloy. This part is made up of six-stage compressor disks connected by five welds. The weld depth of weld I is required to be 7mm, and the weld of weld II to weld V The seam depth is required to be 5mm. And it is required that the coaxiality of the six-stage compressor disc after welding is ≤0.20mm, and the penetration depth is guaranteed, and the defects such as pores are excluded to the bottom of the liner. The inspection standard for pore defects is: CT inspection of the weld area , The entire weld is not allowed to have cracks, incomplete penetration, and no fusion, except for the liner area, no air holes are allowed, the size of a single air hole in the liner area is ≤1.5mm; the minimum distance between the air holes is 2D, where D It is the size of the largest pore; there are no more than 3 pores and unfused joints on a 100mm long weld; if any of the above indicators is not met, the welding is deemed t...

Embodiment approach

[0058] The specific implementation is as follows:

[0059] 1. Perform conventional pickling and dehydrogenation treatment on the compressor disk before electron beam welding, and perform electron beam welding within 24 hours;

[0060] 2. Load the compressor discs at all levels step by step, and the maximum gap between the welds after assembly is 0.05mm;

[0061] 3. Electron beam welding is used for tack welding at Ⅰ~Ⅴ. The process parameters of tack welding are shown in the following table:

[0062]

[0063] 4. Use electron beam welding to perform electron beam welding on the Ⅰ~Ⅴ positions. See Table 2 for sealing and welding parameters. The welding sequence is: firstly seal each weld in the order of weld Ⅰ→Ⅱ→Ⅲ→Ⅳ→Ⅴ; then perform formal welding in the order of weld Ⅱ→Ⅳ→Ⅰ→Ⅲ→Ⅴ, welding parameters As shown in the table below:

[0064]

[0065] 5. Perform conventional stress relief heat treatment after welding to eliminate stress;

[0066] 6. Perform CT inspection on the weld area. There ar...

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Abstract

The invention relates to a vacuum electronic beam welding method for a titanium-alloy rotor component. Five welding seams of a rotor of a gas compressor are welded by an electronic beam welding process. The vacuum electronic beam welding method has the advantages that reasonable welding sequence and welding parameters are adopted for controlling the welding deformation and the quality of the welding seams, the technical difficulties of poor whole rigidity, larger welding amount and difficult control for welding deformation and the like of a product are overcome, the quality of the welding seams is ensured, and the design requirement is met.

Description

Technical field [0001] The invention relates to a welding method, in particular to a vacuum electron beam welding method of a titanium alloy rotor assembly. Background technique [0002] The lightweight requirements of aviation products are getting higher and higher, and the application of titanium alloy components is becoming more and more extensive. For example, the compressor rotor component of an aero engine is TC11 titanium alloy, which is used to connect the stator blades at all levels, and its structure is as figure 1 Shown. This part is made up of a six-stage compressor plate connected by five welds. The weld depth of weld I is 7mm, and the weld depth of weld II to weld V is 5mm. Since the welding torch and the processing tool cannot enter, if the penetration welding method of electron beam welding is adopted, it is impossible to repair the defects after welding on the back of the weld and clean the metal splash in the inner cavity. Therefore, each weld has a liner 8 s...

Claims

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Application Information

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IPC IPC(8): B23K15/06B23K103/14
CPCB23K15/06B23K2103/14
Inventor 郑欣陈健宋健陈玉宝张福霞安晶王振明李佳
Owner HARBIN DONGAN ENGINE GRP
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