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Brazing repair method for failures of aeroengine cobalt-based superalloy parts

A technology of aero-engines and high-temperature alloys, applied in welding equipment, metal processing equipment, manufacturing tools, etc., can solve problems such as blade thermal fatigue cracks, blade scrapping, etc., and achieve the effects of improved pass rate, easy integration, and cost reduction

Active Publication Date: 2017-03-15
国营川西机器厂
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The vane of the high-pressure turbine guide of a certain type of aero-engine is made of cobalt-based superalloy. The guide vane has been working in an environment above 900 °C for a long time. Thermal strain, resulting in blades prone to thermal fatigue cracks and causing a large number of blades to be scrapped
The material of the guide vane is K640 cast cobalt-based superalloy, which has good weldability; because the guide vane has a large number of penetrating cracks and large gap cracks after an overhaul period, it cannot be repaired by ordinary fusion welding technology, resulting in the scrapped
There is no public report on the repair method of the cobalt-based superalloy parts at home and abroad, so a repair method for this type of superalloy parts is needed

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] A method for brazing and repairing failures of cobalt-based superalloy parts of an aero-engine, comprising the following steps:

[0027] S1. Grinding: Use an alloy grinding head to grind the part fault at a speed of 1500rpm, remove all the oxides at the defect and polish it into a "V"-shaped groove, and reserve a 0.2mm matrix for penetrating crack defects;

[0028] S2. Cleaning: Clean the polished place with acetone until the polished place is free of oil, dirt and excess, and the cleaning time is 60 minutes;

[0029] S3. Positioning of the positioning piece: Fix the positioning piece on the side of the penetrating crack or the part where the brazing material is easy to leak by spot welding, so as to prevent the part from filling the parts that do not need to be brazed when the brazing material melts;

[0030] S4. Alloy powder filling: Fill with alloy powder mixed with binder from -100 to +325 mesh (can pass through 100 mesh sieve, but cannot pass through 325 mesh sieve...

Embodiment 2

[0038] A method for brazing and repairing failures of cobalt-based superalloy parts of an aero-engine, comprising the following steps:

[0039] S1. Grinding: Use an alloy grinding head to grind the part fault at a speed of 1200rpm, remove all the oxides at the defect and grind it into a "V"-shaped groove, and reserve a 0.2mm matrix for penetrating crack defects;

[0040] S2. Cleaning: Clean the polished place with acetone until the polished place is free of oil, dirt and excess, and the cleaning time is 45 minutes;

[0041] S3. Positioning of the positioning piece: Fix the positioning piece on the side of the penetrating crack or the part where the brazing material is easy to leak by spot welding, so as to prevent the part from filling the parts that do not need to be brazed when the brazing material melts;

[0042] S4. Alloy powder filling: Fill the gap between the grinding areas with alloy powder mixed with binder of -100~+325 mesh. The material of the alloy powder is the sa...

Embodiment 3

[0050] A method for brazing and repairing failures of cobalt-based superalloy parts of an aero-engine, comprising the following steps:

[0051] S1. Grinding: Use an alloy grinding head to grind the part fault at a speed of 1000rpm, remove all oxides at the defect and grind it into a "V"-shaped groove, and reserve a 0.2mm matrix for penetrating crack defects;

[0052] S2. Cleaning: Clean the polished place with acetone until there is no oil, dirt and excess in the polished place, and the cleaning time is 30 minutes;

[0053] S3. Positioning of the positioning piece: Fix the positioning piece on the side of the penetrating crack or the part where the brazing material is easy to leak by spot welding, so as to prevent the part from filling the parts that do not need to be brazed when the brazing material melts;

[0054] S4. Alloy powder filling: Fill the gap between the grinding areas with alloy powder mixed with binder of -100~+325 mesh. The material of the alloy powder is the sa...

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PUM

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Abstract

The invention relates to a brazing repair method for failures of aeroengine cobalt-based superalloy parts. The method comprises the following steps: S1, polishing; S2, cleaning; S3, making positioning pieces positioned; S4, filling alloy powder: filling gaps among polishing zones by using the alloy powder which is minus 100 to 325 meshes and mixed with adhesives, wherein the materials of the alloy powder are the same as or similar to the materials of the cobalt-based superalloy parts, and the filling heights exceed 1-5mm of the surfaces of the cobalt-based superalloy parts; S5, filling solders; S6, drying; S7, carrying out vacuum brazing: firstly, rising temperature to 600 to 800 DEG C, carrying out heat preservation for 10-30min, then adjusting the temperature to 1100 to 1180 DEG C, carrying out heat preservation for 1-2h, performing brazing, cooling to the temperature of 800 to 900 DEG C along with a furnace, then filling 800 to 1500-mbar argon and cooling to the temperature of 50 to 100 DEG C, and discharging from the furnace; S8, machining profiles; S9, carrying out post-welding inspection. The brazing repair method for the failures of the aeroengine cobalt-based superalloy parts disclosed by the invention has the advantages of solving the problems of incapability of repairing the parts by using the conventional fusion welding, having a good repairing effect and making the parts being capable of reused to reduce the cost.

Description

technical field [0001] The invention relates to the field of aero-engine maintenance, in particular to a fault brazing repair method for cobalt-based high-temperature alloy components of an aero-engine. Background technique [0002] Cobalt-based superalloy is a kind of higher melting point than nickel-based alloy, better thermal corrosion resistance, thermal fatigue performance, creep resistance and welding performance, so it is especially suitable for application in higher thrust-to-weight ratio aeroengines, such as Turbine guide, turbine blade, etc. [0003] The vane of the high-pressure turbine guide of a certain type of aero-engine is made of cobalt-based superalloy. The guide vane works in an environment above 900 °C for a long time. Due to the effects of high temperature, high pressure, gas corrosion, etc. Thermal strain causes the blades to easily produce thermal fatigue cracks and make a large number of blades scrapped. The material of the guide vane is K640 cast c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/04B23K1/008B23K1/20
CPCB23K1/0008B23K1/008B23K1/20B23K1/206B23P6/045
Inventor 郭连平侯廷红张剑铭付俊波何勇张铀
Owner 国营川西机器厂
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