Integral repair method for longitudinal intensive damage of blade crown of aero-engine turbine rotor blade

A technology of turbine rotor and repair method, which is applied in the direction of process efficiency improvement, energy efficiency improvement, additive manufacturing, etc., can solve the problems of blade crown geometric continuous structure damage, difficult to achieve blade repair, and matrix material degradation, etc., and achieves improvement of environmental strength. , Conducive to standardized operations, remove the effect of thorough

Inactive Publication Date: 2019-09-06
PLA NO 5719 FACTORY
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Problems solved by technology

Due to the large number of the above damages, the large coverage area, the large wall thickness reduction, the geometric continuous struc

Method used

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  • Integral repair method for longitudinal intensive damage of blade crown of aero-engine turbine rotor blade
  • Integral repair method for longitudinal intensive damage of blade crown of aero-engine turbine rotor blade
  • Integral repair method for longitudinal intensive damage of blade crown of aero-engine turbine rotor blade

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Embodiment Construction

[0031] The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings, but the protection scope of the present invention is not limited to the following description.

[0032] Such as Figure 1~7 As shown in , an integral repair method for the longitudinal dense damage of the turbine rotor blade shroud, including the following steps:

[0033] S1. Grinding and removing the damaged blade crown, taking the upper surface of the integral casting cover plate of the blade as the reference, removing all structures above the reference, and exposing the metallic luster plane, such as figure 2 shown.

[0034] In step S1, the grinding removal method is CNC lathe or manual grinding and removal.

[0035] S2. Remove the surface cracks under the cast cover plate, and remove the cracks and the surrounding surface as a whole, such as image 3 As shown, the laser additive manufacturing technology is used to fill the surf...

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Abstract

The invention discloses an integral repair method for the longitudinal intensive damage of a blade crown of an aero-engine turbine rotor blade. The integral repair method for the longitudinal intensive damage of the blade crown of the aero-engine turbine rotor blade comprises the following steps of firstly mechanically grinding the blade, integrally removing a damaged blade crown, adopting laser for repairing cracks under a casting cover plate, and fixing a blade tip cover plate onto the blade crown of the blade; then adopting an integral type laser solid forming technology for integrally forming the blade crown, manually processing a formed blade crown surface, and recovering a runner type surface; and finally, carrying out nondestructive testing on the repaired turbine blade, and puttinginto use after the blade meets a criterion. According to the integral repair method for the longitudinal intensive damage of the blade crown of the aero-engine turbine rotor blade provided by the invention, the integral repairing method is adopted, so that not only is degradation material removed thoroughly, but also the one-by-one repair process is avoided, and the workload is reduced; and meanwhile, through using a special repair material, a combination property of the crown material is improved.

Description

technical field [0001] The invention relates to the field of aero-engine maintenance, in particular to an integral repair method for longitudinal intensive damage of the vane shroud of an aero-engine turbine rotor blade. Background technique [0002] Turbine working blades are one of the core components of aero-engines, which are subjected to centrifugal force, thermomechanical alternating loads, high-temperature oxidation, and thermal corrosion during long-term use. Under the combined effect of the above, the leaf crown has produced longitudinal intensive damage, such as: blade tip oxidation corrosion thinning, longitudinal intensive cracks, pitting corrosion, and longitudinal groove-shaped opening corrosion damage caused by the combined action of intensive cracks and corrosion, which have already damaged the blade. The leaf canopy caused large structural damage. Due to the large number of the above damages, the large coverage area, the large wall thickness reduction, the ...

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Application Information

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IPC IPC(8): B22F7/06B22F3/105B33Y10/00
CPCB22F7/062B33Y10/00B22F2007/068B22F10/00B22F10/38B22F10/66B22F10/36B22F10/12B22F10/50Y02P10/25B23P6/002
Inventor 张铀罗奎林罗九龙罗烽月何勇陈海生杨秀恩王冰雪张凯
Owner PLA NO 5719 FACTORY
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