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Method for conducting powder sintering and forming and restoring to large blade gap defects of gas turbine

A gas turbine blade, sintering forming technology, which is applied in the field of gas turbine blade large gap defect powder sintering molding repair, can solve the problems of low strength, high cost, variability, etc., achieve high repair efficiency and reduce scrapped blade parts loss effect

Active Publication Date: 2015-05-20
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

[0006] The purpose of the present invention is to provide a method for repairing gas turbine blade large-gap defect powder sintering and molding, which can solve the large three-dimensional defects such as cracks, ablation holes and corrosion pits of nickel-based, cobalt-based and iron-based alloy blades with high aluminum and titanium content. Space defects are difficult to repair, variability, low strength, high cost, and cannot be repaired in a timely and reliable manner.

Method used

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  • Method for conducting powder sintering and forming and restoring to large blade gap defects of gas turbine

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Effect test

Embodiment 1

[0038] During the second overhaul of a large aeroengine with turbofan structure, thermal fatigue cracks were found in three places on the edge plate of the first-stage three-piece guide vane of the gas turbine. The crack length is about 10-20mm and the depth is penetrating. The crack is located at the corner R between the edge plate and the blade body, where the wall thickness is 1-3mm. The blade is a hollow structure, and the blade material is Жc6y alloy. The total content of Al+Ti in the alloy is more than 8wt%. Cracks are easy to occur during fusion welding, and the material is not weldable, and it is difficult to repair by argon arc welding. Although laser micro-welding and micro-arc deposition coating technology can heal cracks, it is time-consuming and the thermal fatigue resistance of the repaired welding area is much lower than that of the base alloy, which cannot meet the test run requirements. The invention not only can heal the cracks quickly and conveniently, but a...

Embodiment 2

[0051] A power plant in Guangdong imported a gas turbine-steam turbine combined cycle generator set. During maintenance, it was found that the nozzle of the gas turbine, that is, the guide vane, was severely corroded and cracked. The material of the nozzle is FSX-414 cobalt-based alloy. The structure of the nozzle is a three-blade conjoined body. There are many penetrating cracks and cracks on the edge plate of the nozzle. The exhaust edge of the nozzle blade is formed by thermal corrosion. Gap and lack of flesh. The blades of the nozzle are hollow, with air-cooling holes on the exhaust side, and the coating on the surface of the blades is plasma sprayed CoNiCrAlY coating. Using laser micro-integral welding and micro-arc deposition coating methods to repair, the workload is too large, the efficiency is low, and the thermal fatigue resistance of the repair layer is not high. By adopting the invention, all cracks and corrosion gaps can be repaired together, and the efficiency i...

Embodiment 3

[0066] A coal-coking plant in Shandong Province, China, in order to reduce the environmental pollution and energy utilization of coal-coking furnace tail gas venting, adopts a turboshaft gas turbine, and uses the coal-coking furnace tail gas as gas to drive the turbine to rotate and drive the generator to generate electricity. However, although the exhaust gas of the furnace has undergone desulfurization and desalination treatment, the sulfur, chlorine and some harmful impurities in the exhaust gas are relatively high, and the combustion ash containing these substances is mostly deposited on the crown of the first-stage turbine rotor blade. The lower part and the first-stage guide vane body form molten salt at high temperature, resulting in severe thermoelectric corrosion of the blade, which makes the blade matrix thinner and even eroded through and broken. The material of the blade is K403 (K3) nickel-based high-temperature casting alloy. Also because the alloy’s Al+Ti content...

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Abstract

The invention relates to the field of maintaining a gas turbine, and in particular relates to a method for conducting powder sintering and forming and restoring to large blade gap defects of a gas turbine, which is used in large gap defects such as crack, ablation holes, corrosion pits and the like caused in service process of a turbine rotor blade, a static guide blade and guider and a nozzle assembly of a high propulsion ratio aircraft engine, a heavy type power combustor, a delivery combustor and a naval vessel combustor. The powder sintering, forming and restoration process are as follows: firstly applying a surface activating treatment material on trimmed and cleaned defects, filling the space of the defects with a nickel-based or cobalt-based alloy subjected to B activating treatment, plasticizing and forming, and achieving restoration by high-temperature sintering and connection. The method can solve the problem that the large blade gap defects of Al-Ti high-temperature alloy can not be restored to cause scrap. The blade restoration strength is high, no deformation exists, the speed is fast and the cost is low.

Description

technical field [0001] The invention relates to the field of gas turbine maintenance, in particular to a method for repairing gas turbine blades with large gap defects by powder sintering and forming, such as turbine rotor blades and static guides of high-thrust ratio aero-engines, heavy-duty electric gas turbines, transport gas turbines, and naval gas turbines. The large gap defects such as cracks, ablation holes and corrosion pits caused by blades, guides and nozzle parts during service use are repaired by powder sintering molding. Background technique [0002] At present, gas turbines are widely used in aeroengines and ground power generation devices. With the improvement of engine efficiency, the gas temperature of the engine is getting higher and higher. At the same time, the high-temperature gas produced by engine combustion is also highly corrosive and oxidizing. [0003] The high-pressure turbine blades are located in the turbine part of the gas turbine. The hottest...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P6/00
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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