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Method for repairing long-life thermal barrier coating of turbine blade of F-class ground heavy-duty gas turbine

A technology of turbine blades and thermal barrier coatings, applied in coatings, metal material coating processes, furnace types, etc., can solve the problems that the long-life thermal barrier coatings of turbine blades cannot be repaired, and achieve easy solution Embrittlement, reduced boundary layer separation, and reduced production costs

Inactive Publication Date: 2020-06-09
PLA NO 5719 FACTORY
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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 the long-life thermal barrier coating of turbine blades of F-class ground heavy-duty gas turbines, so as to solve the technical problem that the long-life thermal barrier coating of turbine blades cannot be repaired in the prior art

Method used

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  • Method for repairing long-life thermal barrier coating of turbine blade of F-class ground heavy-duty gas turbine
  • Method for repairing long-life thermal barrier coating of turbine blade of F-class ground heavy-duty gas turbine
  • Method for repairing long-life thermal barrier coating of turbine blade of F-class ground heavy-duty gas turbine

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0043] 1.1 Repair of thermal barrier coating:

[0044] After 48,000 equivalent operating hours (EOH) of the turbine blades of a F-class heavy-duty gas turbine, the back of the blade, the edge plate, and the inlet edge of the blade appeared coating pieces, coating cracks, and coating burns. The thermal barrier coating of the transparent vane is repaired, and the specific steps are as follows:

[0045] (1) Peel off the surface layer of the old thermal barrier coating on the turbine blade: use the sand blowing method to peel off the surface layer of the old thermal barrier coating, the white corundum particles are 60 mesh, the sand blowing pressure is 0.4MPa, and the distance is 150mm;

[0046] (2) Remove the old thermal barrier coating bonding layer on the turbine blade:

[0047] Use hydrochloric acid solution to remove the old thermal barrier coating adhesive layer, immerse the turbine blade with the surface layer of the old thermal barrier coating peeled off in a hydrochloric...

Embodiment 2

[0072] 2.1 Repair of thermal barrier coating:

[0073] After 48,000 equivalent operating hours (EOH) of the turbine blades of a F-class heavy-duty gas turbine, the back of the blade, the edge plate, and the inlet edge of the blade appeared coating pieces, coating cracks, and coating burns. The thermal barrier coating of the transparent vane is repaired, and the specific steps are as follows:

[0074] (1) Peel off the surface layer of the old thermal barrier coating on the turbine blades: use the sand blowing method to peel off the surface layer of the old thermal barrier coating, the white corundum particles are 60 mesh, the sand blowing pressure is 0.3MPa, and the distance is 140mm;

[0075] (2) Remove the old thermal barrier coating bonding layer on the turbine blade:

[0076] Use hydrochloric acid solution to remove the old thermal barrier coating adhesive layer, immerse the turbine blade with the surface layer of the old thermal barrier coating peeled off in a hydrochlori...

Embodiment 3

[0099] 3.1 Repair of thermal barrier coating:

[0100] After 48,000 equivalent operating hours (EOH) of the turbine blades of a F-class heavy-duty gas turbine, the back of the blade, the edge plate, and the inlet edge of the blade appeared coating pieces, coating cracks, and coating burns. The thermal barrier coating of the transparent vane is repaired, and the specific steps are as follows:

[0101] (1) Peel off the surface layer of the old thermal barrier coating on the turbine blade: use the sand blowing method to peel off the surface layer of the old thermal barrier coating, the white corundum particles are 60 mesh, the sand blowing pressure is 0.5MPa, and the distance is 160mm;

[0102] (2) Remove the old thermal barrier coating bonding layer on the turbine blade:

[0103] Use hydrochloric acid solution to remove the old thermal barrier coating adhesive layer, immerse the turbine blade with the surface layer of the old thermal barrier coating peeled off in a hydrochloric...

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Abstract

The invention provides a method for repairing a long-life thermal barrier coating of a turbine blade of a F-class ground heavy-duty gas turbine, and the method solves the technical problem that the long-life thermal barrier coating of the turbine blade in the prior art cannot be repaired. The method comprises the following steps of: (1) peeling off the old thermal barrier coating surface layer onthe turbine blade; (2) removing an old thermal barrier coating adhesive layer on the turbine blade; (3) preparing a new thermal barrier coating adhesive layer by hypersonic flame spraying; (4) preparing the new thermal barrier coating surface layer by plasma spraying; (5) vacuum pretreatment: (6) aging treatment: and (7) surface and cooling holes machining of the thermal barrier coating. Accordingto the invention, a special heat treatment system is designed, so that the performance of the thermal barrier coating is ensured without losing the service life of a blade substrate, and the endurance performance of 870 DEG C / 370MPa of the blade substrate can be increased to 105%-110% of the original value.

Description

technical field [0001] The invention relates to the field of gas turbine maintenance, in particular to a method for repairing a long-life thermal barrier coating for turbine blades of an F-level ground heavy-duty gas turbine. Background technique [0002] The turbine inlet temperature of a certain type of F-class ground heavy-duty gas turbine is as high as 1400 ℃, and the operating time is as long as tens of thousands of hours. After an overhaul period (16000EOH), the thermal barrier coating on the surface of the turbine blades (turbine moving blades and turbine stationary blades) has been damaged to varying degrees (including falling blocks, burning, cracks, degradation, etc.), seriously affecting the operation of the unit performance and safety. In order to meet the performance requirements of the unit and provide tens of thousands of hours of safe operation, it is necessary to repair the damaged turbine blade thermal barrier coating. [0003] At present, domestic resear...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/129C23C4/134C23C4/073C23C4/02C23C4/18C21D9/00C21D1/773
CPCC21D1/773C21D9/0068C23C4/02C23C4/18C23C4/073C23C4/129C23C4/134
Inventor 王冰雪罗奎林冯云彪何勇陈海生杨秀恩罗烽月胡兵
Owner PLA NO 5719 FACTORY
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