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Vacuum brazing method for patch repairing of stator blade of aero-engine turbine

A technology for aero-engines and turbine stators, applied in welding equipment, metal processing equipment, manufacturing tools, etc., can solve the problems of failure repair that cannot be ablated, ablation, scrapped blades, etc., and achieve small solder, good repair effect, and energy saving cost effect

Pending Publication Date: 2019-01-11
PLA NO 5719 FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to high temperature, high pressure gas corrosion and cold and heat fatigue during the working process of the turbine stator blades, failures such as ablation and other failures often occur in the parts of high thermal stress, resulting in the scrapping of the blades
[0003] However, ablation failures cannot be repaired using traditional brazing or welding methods
At present, there are no public reports at home and abroad that can repair the ablation failure of aeroengine turbine stator blades

Method used

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  • Vacuum brazing method for patch repairing of stator blade of aero-engine turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] A vacuum brazing method for repairing an aero-engine turbine stator blade patch, comprising the following steps;

[0031] S1. Removing the thermal barrier coating: remove the thermal barrier coating according to the thermal barrier coating mode of the turbine stator blade, and the removal method of the thermal barrier coating is chemical method, sand blowing or high-pressure water jet;

[0032] S2. Mark the ablation site;

[0033] S3. Process the ablation area: remove the ablation area at the marked position, and ensure that the removal area is a regular-shaped processing groove. The treatment method for removing the ablation area is CNC milling or EDM;

[0034] S4. Cutting the patch material: according to the size of the processing groove, cut the patch material of the corresponding size from the metal injection molded sheet;

[0035] S5. Grinding width: use a pneumatic grinding pen and a hard rotary file to grind the notch of the processing groove and the patch mater...

Embodiment 2

[0044] A vacuum brazing method for repairing an aero-engine turbine stator blade patch, comprising the following steps;

[0045] S1. Removing the thermal barrier coating: remove the thermal barrier coating according to the thermal barrier coating mode of the turbine stator blade, and the removal method of the thermal barrier coating is chemical method, sand blowing or high-pressure water jet;

[0046] S2. Mark the ablation site;

[0047] S3. Process the ablation area: remove the ablation area at the marked position, and ensure that the removal area is a regular-shaped processing groove. The treatment method for removing the ablation area is CNC milling or EDM;

[0048] S4. Cutting the patch material: according to the size of the processing groove, cut the patch material of the corresponding size from the metal injection molded sheet;

[0049] S5. Grinding width: use a pneumatic grinding pen and a hard rotary file to grind the notch of the processing groove and the patch mater...

Embodiment 3

[0058] A vacuum brazing method for repairing an aero-engine turbine stator blade patch, comprising the following steps;

[0059] S1. Removing the thermal barrier coating: remove the thermal barrier coating according to the thermal barrier coating mode of the turbine stator blade, and the removal method of the thermal barrier coating is chemical method, sand blowing or high-pressure water jet;

[0060] S2. Mark the ablation site;

[0061] S3. Process the ablation area: remove the ablation area at the marked position, and ensure that the removal area is a regular-shaped processing groove. The treatment method for removing the ablation area is CNC milling or EDM;

[0062] S4. Cutting the patch material: according to the size of the processing groove, cut the patch material of the corresponding size from the metal injection molded sheet;

[0063] S5. Grinding width: Use a pneumatic grinding pen and a hard rotary file to grind the notch of the processing groove and the patch mater...

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Abstract

The invention discloses a vacuum brazing method for patch repairing of a stator blade of an aero-engine turbine. The method comprises the following steps that a thermal barrier coating is removed; anablated portion is labeled; the ablated portion is processed; a patch repairing material is cut; width polishing is carried out; spot welding is carried out; heat preservation is carried out; vacuum brazing is carried out; diffusion treatment is carried out; polishing and patching are carried out; and postwelding checking is carried out. According to the vacuum brazing method, the problem that theablation fault of the turbine stator blade cannot be repaired through a traditional brazing or fusion welding manner is solved; the repairing effect is good, the scrappage rate of the turbine statorblade is reduced, and cost is reduced; the vacuum brazing method is simple in operation process, quality control is stable, brazing filler metal generated after brazing is carried out is small, and the process is simple, fast and reliable. For turbine stator blades repaired in batches, a plurality of turbine stator blades are drawn randomly for long test evaluation, and it is further ensured thatthe turbine stator blades repaired in this batch meet the requirement of actual use.

Description

technical field [0001] The invention relates to the field of aero-engine maintenance, in particular to a vacuum brazing method for repairing a patch of an aero-engine turbine stator blade. Background technique [0002] The aeroengine turbine stator blades are located in the engine combustion chamber unit body, and the turbine stator blades are mainly used to guide the high-temperature combustion airflow, and do work on the next-stage high-pressure turbine rotor blades in one direction, thereby driving the engine to generate thrust. Turbine stator blades are subjected to high temperature, high pressure gas corrosion and cold and heat fatigue during the working process, and failures such as ablation often occur in parts of high thermal stress, resulting in the scrapping of the blades. [0003] However, ablation failures cannot be repaired by conventional brazing or welding methods. At present, there are no public reports at home and abroad that can repair the ablation failure...

Claims

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Application Information

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IPC IPC(8): B23P6/00B23K1/008
CPCB23K1/008B23P6/002
Inventor 郭连平翟建楠杨秀恩陈海生冯志岛段俊菲
Owner PLA NO 5719 FACTORY
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