Process method for repairing gas turbine vanes by micro-arc deposition coating

A technology for gas turbine blades and a process method, which is applied in the field of gas turbine maintenance, can solve the problems of easy deformation, complex repair process and high cost, and achieves the effects of easy operation and simple process method.

Active Publication Date: 2012-11-28
无锡中科金研激光燃气轮机部件有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a gas turbine blade micro-arc deposition coating repair process, which solves the problems in the prior art that the repair process is complex, easy to deform, high cost, and cannot be repaired in time and reliably.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] The gas delivery device of an oilfield uses MS5001PG gas turbine as the driving force. During the overhaul at the beginning of 2006, it was found that some blade tips of the first-stage turbine rotor blades (hollow structure) of the gas turbine were broken, and some blade blades had pits of different sizes. The surface coating of most blades peeled off locally. The material of the blade is GTD111 nickel-based superalloy, because it contains >8wt% (Al+Ti). Cracks during fusion welding, non-weldable materials, difficult to repair by laser cladding welding and argon arc welding. According to the analysis, the damage of the blades of this stage is caused by the impact of the external rotor. The test of micro-arc deposition coating IMR-N800 nickel-based superalloy on GTD 111 nickel-based superalloy block shows that there are no cracks on the base material, deposited layer and their bonding interface, which can be repaired by welding.

[0030] The repair process for cracks...

Embodiment 2

[0042]A coal coking plant uses a turboshaft gas turbine to generate electricity from the tail gas produced by the coal-coke reformer, which effectively solves the serious problem of air pollution caused by the venting of the tail gas, and at the same time obtains a higher net income for the plant. However, due to the high content of S, Cl, C and other impurities in the tail gas of coal-coke conversion (depending on the coal quality), the first-stage rotor blade (hollow structure, K403 nickel-based superalloy) of the gas turbine and the first-stage guide The blades (hollow structure, K403 nickel-based superalloy) have severe thermal corrosion, so that the crown of the moving blade and the piercing of the stationary blade will occur in less than 4000 hours of service. The high speed hits the second and third stage blades behind and destroys them, resulting in a shutdown. The micro-arc deposition coating process was used to repair the corroded first-stage moving blades and statio...

Embodiment 3

[0058] A power plant in Shenzhen adopts a gas turbine-steam turbine-cycle power generation system produced by GE. The main form of damage and failure of the gas turbine blade is that the blade tip of the first-stage turbine rotor blade wears and shortens, which reduces the power efficiency of the gas turbine. Because the interior of the first-stage moving blade is a labyrinth-shaped hollow air-cooled structure, and is made of high-temperature nickel-based superalloy, and the surface of the blade has an anti-oxidation coating, the price is expensive, and foreign imports are not only difficult to purchase, but also restricted. Using the micro-arc deposition coating process to repair the tip of the blade with Co-based alloy, it not only solves the urgent need, but also prolongs the service life of the blade and reduces the cost of overhaul exponentially.

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Abstract

The invention relates to the maintenance field of gas turbines, in particular to a process method for repairing gas turbine vanes by a micro-arc deposition coating. The invention relates to a process method that adopts the micro-arc deposition coating to repair the local damage area of a geometrical component or a surface coating caused during the service process of air compressor vanes of a heavy gas turbine, turbine rotor vanes and guider vanes / nozzles. The method can carry out micro-arc deposition coating restoration on the gas turbine vanes. The micro-arc deposition coating process is defined into a metallurgical process as follows: an electrode rod is used as an anode; a workpiece is used as a cathode; the high-frequency direct-current pulse micro-arc discharge is carried out betweenthe electrode rod and a workpiece surface; and the material of the electrode rod is self-consumed and transferred to the contact area of the workpiece surface; and the environment during the transferring and depositing process of material is inert gas or vacuum or insulating oil. The process method can solve the problems that in the prior art, the restoration process is complex, the deformation occurs easily, the cost is high, and the restoration can not be done reliably and timely.

Description

technical field [0001] The invention relates to the field of gas turbine maintenance, in particular to a gas turbine blade micro-arc deposition coating repair process method, especially the geometric structure caused by the service process of compressor blades, turbine rotor blades and guider blades / nozzle parts of heavy gas turbines. The local damaged area of ​​the shape and surface coating is repaired by micro-arc deposition coating. Background technique [0002] Gas turbine is a turbo turbine engine that can convert fuel oil, gas, biogas, coal coking gas, etc. into mechanical driving force. , Ships, locomotives, metallurgy, petroleum, chemical industry and other industrial production drives, especially on ground power devices, gas turbine-generator power generation systems and gas turbine-steam turbine-generator combined cycle power generation systems are widely used. With the ever-increasing demand for energy saving and environmental protection, such as heavy oil and bl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P6/00B23H9/10
Inventor 王茂才王东生
Owner 无锡中科金研激光燃气轮机部件有限公司
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