Aero-engine turbine rear case support plate long crack A-TIG welding restoration method

An aero-engine and repair method technology, which is applied in welding equipment, arc welding equipment, manufacturing tools, etc., can solve the problems of decreased mechanical properties of weld seams, large welding residual stress, and out-of-tolerance runout of end faces, etc., and achieves the reduction of welding heat affected area. Small size, small cross-sectional area of ​​weld seam, and small deformation of end face

Active Publication Date: 2019-10-15
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The inner ring is circular, and there are rectifying support plates outside the load-bearing support plate. Under the action of comprehensive stress such as vibration stress and thermal stress during work, a large number of long cracks appear at the welds between the support plate and the inner and outer rings and are scrapped. The repair method is TIG welding. Due to the large number and long cracks, the installation surface is seriously deformed after repair, and the runout of the end face is out of tolerance, resulting in repair failure.
[0003] Traditional TIG welding technology, in order to solve the problem of poor fusion of the side wall, it is necessary to open a V-shaped groove with a large angle, many welding passes, wide welding heat-affected zone, large welding residual stress, and large welding deformation
At the same time, due to the large welding heat input, the weld structure is coarse, which reduces the mechanical properties of the weld.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] Example 1: An A-TIG repair method for long cracks in aeroengine turbine rear casing support plate. Three support plates have cracks. The crack lengths are 10mm, 12mm, and 12mm respectively. It includes the following steps:

[0026] S1. Flux preparation: scrape off the outer coating of Inconel718 electrode and mix it with acetone evenly;

[0027] S2. Use a pneumatic sanding pen and A1.5 type sanding head to polish away the oxide scale and dirt inside the crack to form an "I" groove, clean it with acetone, and dry it naturally;

[0028] S3. Apply the mixed flux of S1 to the cracked surface;

[0029] S4. Argon arc welding where the flux is applied to S2, the welding current of argon arc welding is 3-A, the argon flow is 16 L / min on the front and 12 L / min on the back;

[0030] S5. The fitter polishes to make the weld and the base smoothly transition;

[0031] S6, stress relief heat treatment, the heat treatment specification is 762℃ / (2h﹢10min), AC+625℃ / (4h-10min), AC;

[0032] S7. Runo...

Embodiment 2

[0033] Example 2: An A-TIG repair method for long cracks in aeroengine turbine rear casing support plate, four support plates have cracks, and the crack lengths are 10mm, 11mm, 11mm, and 13mm respectively. It includes the following steps:

[0034] S1. Flux preparation: scrape off the outer coating of Inconel718 electrode and mix it with absolute ethanol;

[0035] S2. Use a pneumatic grinding pen and A1.5 type grinding head to polish away the oxide scale and dirt inside the crack and form an "I" groove, clean it with acetone, and dry it naturally;

[0036] S3. Apply the mixed flux of S1 to the cracked surface;

[0037] S4. Argon arc welding where flux is applied to S2, the welding current of argon arc welding is 25A, the argon flow is 13 L / min on the front and 10 L / min on the back;

[0038] S5. The fitter polishes to make the weld and the base smoothly transition;

[0039] S6, stress relief heat treatment, the heat treatment specification is 765℃ / (2h﹢10min), AC+624℃ / (4h﹢10min), AC;

[0040...

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Abstract

The invention relates to an aero-engine turbine rear case support plate long crack A-TIG welding restoration method. The method includes the following steps: S1, grinding and cleaning; S2, coating a crack with soldering flux; S3, argon arc welding; S4, benchwork grinding; S5, stress relief heat treatment; and S6, inspection. The idea of performing active TIG welding (A-TIG) to restore the long crack of a rear case support plate of an aero-engine turbine is put forwards in the method, the heat input of a welded joint is low, welding heat affected zones are reduced, and the mechanical property of the welded joint is improved. The deformation amount of an intermediate case is greatly reduced compared with that in a TIG welding method. The engine maintenance cost is greatly reduced and the engine maintenance period is shortened.

Description

Technical field [0001] The invention relates to the technical field of aeroengine maintenance, in particular to an A-TIG welding repair method for long cracks in aeroengine turbine rear casing support plate. Background technique [0002] The aero engine turbine rear casing is the main load-bearing component at the rear of the engine. The inner and outer rings of the rear casing are welded to form a frame with 8 support plates. The outer ring is polygonal and is connected to the outer culvert load-bearing ring through 8 tie rods. The inner ring is circular, and there are rectifying support plates outside the load-bearing support plates. Under the action of vibration stress, thermal stress and other comprehensive stresses during operation, a large number of long cracks appear at the welding seams of the support plate and the inner and outer rings and are scrapped. The repair method of TIG welding, due to the large number of cracks and long, the installation surface deformed serious...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/04B23K9/167B23K9/235
CPCB23P6/045B23K9/235B23K9/167
Inventor 刘瑞陈海生彭东段俊菲孙治国罗光荣
Owner PLA NO 5719 FACTORY
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