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Laser cladding repairing technical method for labyrinth seal of turbine disc

A laser cladding and process method technology, applied in metal material coating process, coating and other directions, can solve problems such as the influence of personnel skill level, unstable repair quality, poor process stability, etc., to achieve good repeatability, avoid pores and The effect of poor fusion and full forming appearance

Active Publication Date: 2018-03-16
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

Turbine disc grate teeth are very thin, and the edge thickness of the grate teeth is only 0.2mm~0.3mm. Using argon arc welding is prone to undercutting, parts deformation and other problems, and is affected by the skill level of personnel, poor process stability and unstable repair quality

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  • Laser cladding repairing technical method for labyrinth seal of turbine disc
  • Laser cladding repairing technical method for labyrinth seal of turbine disc

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Embodiment Construction

[0024] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0025] like figure 1 As shown, it is a schematic diagram of the structure of the turbine disc grate. Among the figures, Φ is the diameter of the turbine disc, and 1 is the sealing grate. GH4169 spherical alloy powder with the same powder particle size as the turbine disc body material is used as the cladding material;

[0026] Process method of the present invention is specifically as follows:

[0027] First, in the argon atmosphere protection box, install the turbine disk on the rotating and swinging working turntable, so that the center of the turbine disk and the center of the working turntable are coaxial;

[0028] Secondly, use acetone or absolute ethanol to wipe the grate teeth of the turbine disc to remove dirt; then, according to the inclination angle of the grate teeth, the working turntable is deflected at a certain angle,...

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Abstract

The invention discloses a laser cladding repairing technical method for a labyrinth seal of a turbine disc. The laser cladding repairing technical method for the labyrinth seal of the turbine disc comprises the following steps that the turbine disc is clamped in an inert atmosphere protection box, the to-be-repaired labyrinth seal is cleaned and then subjected to laser cladding, and the repaired portion is machined, specifically, cleaning of the to-be-repaired labyrinth seal includes matrix pre-melting and powder supply cladding which are conducted in sequence, as for matrix pre-melting, a laser unit is adopted for irradiating the to-be-repaired labyrinth seal of the turbine disc so that a matrix of the to-be-repaired labyrinth seal can be molten, and as for powder supply cladding, laser cladding is conducted on the to-be-repaired labyrinth seal of the turbine disc in a mode that a powder supply nozzle conducts lateral powder supply. By means of the technical method, the abraded labyrinth seal can recover to the initial geometric shape and technical indexes and can be reused.

Description

technical field [0001] The invention relates to the field of aero-engine maintenance, in particular to a laser cladding repair process method for aero-engine turbine disc grate teeth. Background technique [0002] The turbine disk is a key component of an aero-engine. The grate seal is a non-contact dynamic seal that uses the sudden expansion and contraction of the channel to increase the flow resistance to limit fluid leakage. It is an effective, long-term seal widely used in aero-engines. The life-sealed structure is mainly used for the top of the compressor and turbine stages and blades. In order to reduce seal leakage and improve engine operating efficiency, it is necessary to minimize the movement gap between the rotor and the stator. The gap is affected by the radial movement caused by cumulative support errors, dynamic deflection and thermal deformation, and there is a minimum value, but it is difficult to determine during design. If the gap is too large, the airflo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C24/10B23P6/00
CPCB23P6/00C23C24/106
Inventor 王辉明康文军朱红钢阮成勇耿军儒尉秧丰雷明李文涛
Owner AECC AVIATION POWER CO LTD
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