Crack repair process for high-pressure turbine blade tip in gas turbine

A technology for high-pressure turbines and gas turbines, applied in the field of metal surface crack repair, can solve the problems of high-pressure turbine blade tip cracks that are rarely reported in public literature, and achieve the goal of avoiding cracks at the interface between repair welding materials and base materials, easy operation, and simple process methods Effect

Inactive Publication Date: 2006-12-27
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the repair of high-pressure turbine blade tip wear, fusion welding methods such as argon arc welding and laser welding and non-fusion welding methods such as brazing and diffusion welding are generally used. There are literature and patent reports at home and abroad in this regard, but high-pressure turbine blades The repair of sharp cracks is rarely reported in public literature at home and abroad

Method used

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  • Crack repair process for high-pressure turbine blade tip in gas turbine
  • Crack repair process for high-pressure turbine blade tip in gas turbine
  • Crack repair process for high-pressure turbine blade tip in gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] The tip crack repair of a high-pressure turbine blade of an aero-engine, the material is K465 alloy, the specific steps are as follows:

[0033] 1. According to the length and intensity of cracks on the tip of the high-pressure turbine blade, the cracks are removed by grinding in the form of openings. The maximum depth of the opening is 5mm, and the width is suitable for completely removing cracks and minimizing the loss of the base material.

[0034] 2. Under the protection of argon gas, the 3H-ES-6 metal surface strengthening repair machine developed by the Institute of Metal Research, Chinese Academy of Sciences is used for high-energy micro-arc spark (electric spark) deposition. The electrode diameter is Φ1mm, and the electrode is surfacing welding layer by layer in the repair welding area Until the entire repair welding area is filled and a grinding allowance is left.

[0035] 3. The high-energy micro-arc spark deposition material is GH44.

[0036] 4. Carry out sh...

Embodiment 2

[0042] The difference from Example 1 is:

[0043] A high-pressure turbine blade tip crack repair of an aero-engine, the blade material is Rene80, and the opening filler welding is used for repairing, the maximum opening depth is 7mm, the repair material is IN625 powder, and the average particle size is about 270 mesh. Under the protection of helium, the laser welding process is used to surfacing layer by layer in the repair welding area until the entire repair welding area is filled and a grinding allowance is left. Afterwards, grinding, testing, polishing, and shot blasting are carried out, and finally the blade is heat-treated at 1050°C for 80 hours to restore performance.

[0044] The high-pressure turbine blades repaired by this process meet the repair technical standards through X-ray and fluorescence detection.

Embodiment 3

[0046] The difference from Example 1 is:

[0047] A high-pressure turbine blade tip crack repair of an aero-engine, the blade material is K24, and the opening filler welding is used for repairing, and the maximum opening depth is 5mm. Under the protection of helium, first use the 3H-ES-6 metal surface strengthening repair machine developed by the Institute of Metal Research, Chinese Academy of Sciences to perform high-energy micro-arc spark deposition to preset the bottom layer (the electrode diameter is Φ3mm, the bottom layer height is 100um), and then use metal powder Carry out laser welding, build up welding layer by layer in the repair welding area until the entire repair welding area is filled and a grinding allowance is left. The electrodes and powder are Haynes 230. Afterwards, grinding, testing, polishing, and shot blasting are carried out, and finally the blade is heat-treated at 1180°C for 10 hours to restore performance.

[0048] In this embodiment, high-energy mic...

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Abstract

The present invention belongs to the metal surface crack repairing method, meaning the tip crack repairing method of a gas-turbine engine high-pressure turbine blade. The method comprises polishing apertures for complete crack removal based on the crack conditions of the gas-turbine engine high-pressure turbine blade tip, carrying out surfacing welding in the repair welding zone using low-heat input welding technology and implementing heat treatment process to the repaired blade. The present invention has the virtues of simple process, needing no vacuum or preheating, small damage to blade base materials, realizing loss-free repair to the high-pressure turbine blade tip cracks and reducing repair cost. The invention can be used to repair both the gas-turbine engine high-pressure turbine blade tip cracks and steam turbine, smoke turbine and other turbine mechanisms high-pressure or low-pressure blade tip cracks. And the aircraft engine high-pressure turbine blade repaired with the method has passes 368h long-term bench trial check.

Description

technical field [0001] The invention belongs to a method for repairing cracks on metal surfaces, in particular to a method for repairing cracks at the tip of a high-pressure turbine blade of a gas turbine. Background technique [0002] Modern gas turbines are widely used in aero engines and ground electric gas turbines. With the improvement of engine efficiency, the temperature of engine gas is getting higher and higher. At the same time, the high-temperature gas produced by engine combustion is also highly corrosive and oxidizing. The high-pressure turbine blades are located in the turbine part of the gas turbine. The hottest gas discharged from the combustion chamber directly acts on the vicinity of the blade tips of the turbine blades. Due to the start and stop of the engine or sudden state changes, the blade tips will generate high thermal stress. At the same time, the high-temperature creep of the blades The tip of the variable elongation blade and the outer casing are ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/00
Inventor 王茂才谢玉江王东生王晓微
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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