Repairing method of aero-engine blade

An aero-engine and repair method technology, applied in the direction of improvement of process efficiency, improvement of energy efficiency, additive processing, etc., can solve problems such as unfavorable high-temperature mechanical properties of repaired blades, inability to form solidified structures with directional growth, etc., and achieve good mechanical properties , reducing the effect of transverse grain boundaries

Active Publication Date: 2020-11-24
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The traditional additive manufacturing method currently used uses the method of rotating 67° between adjacent deposition layers for scanning, but the rotation of the scanning path is not conducive to the epitaxial g

Method used

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  • Repairing method of aero-engine blade
  • Repairing method of aero-engine blade
  • Repairing method of aero-engine blade

Examples

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Embodiment 1

[0035] Such as figure 1 As shown, the laser molding module includes an optical window 10, a powder spreading device 11, a molding cavity 12, a substrate 13, a lifting mechanism 14, and a powder scraping device 15; the optical window 10 is located above the molding cavity 12, and a lifting mechanism is installed in the molding cavity 12 14. The substrate 13 is horizontally installed on the lifting mechanism 14, the powder spreading device 11 is located on one side of the molding cavity 12, and the powder scraping device 15 is located on the other side of the molding cavity 12.

[0036] It is worth mentioning that the lifting mechanism 14 can be a piston, and a groove for fixing the workpiece to be processed is opened in the middle of the base plate 13 , and a mounting hole is opened on the base plate 13 , and then fixed on the lifting mechanism 14 by bolts 16 .

[0037] The laser light emitted by the laser reaches the scanning system after passing through the light guide system...

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Abstract

The invention relates to the field of aviation key part repairing, in particular to a repairing method of an aero-engine blade. The repairing method comprises the following steps that a blade to be repaired is fixed in a forming cavity of selective laser melting equipment; powder is laid in the forming cavity to cover a to-be-repaired area of the blade, a laser beam is used for scanning and melting the powder along a set path at set power, and the scanning path is in the chordwise direction of the blade; after a molten pool is solidified, a deposition layer is formed, on the premise that powder is not added, the power of the laser beam is reduced, the deposition layer is scanned again according to the set path to eliminate crystal grains on the surface of the deposition layer, and then a remelting layer is formed; and the operations are repeatedly carried out until repairing is completed. Thus, the powder is deposited on the blade layer by layer in the chordwise direction of the blade,columnar crystals can grow epitaxially and directionally in the heat flow direction, the transverse grain boundary of the blade in the chordwise direction is reduced, and the repaired blade shows good mechanical properties at high temperature.

Description

technical field [0001] The invention relates to the field of repairing key aviation parts, in particular to a repairing method for an aeroengine blade. Background technique [0002] Titanium alloys and nickel-based superalloys have very superior comprehensive mechanical properties, and are the main materials for aeroengine blades, blisks and overall blisks. Due to the harsh service environment of aero-engines, the blades will be cracked, corroded, and worn under long-term high-temperature and high-pressure conditions, resulting in failure and scrapping of the workpiece. Traditional repair methods such as argon tungsten arc welding and linear friction welding are prone to defects such as pores, hydrogen embrittlement, and cracks. In view of the above problems, there is an urgent need to adopt an advanced repair technology to achieve high-quality and efficient repair of damaged parts, restore the geometric and mechanical properties of damaged parts, prolong their service life...

Claims

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Application Information

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IPC IPC(8): B22F7/06B22F3/105B22F3/24B33Y10/00B33Y40/20
CPCB22F3/24B22F7/062B22F2003/248B22F2007/068B33Y10/00B33Y40/20Y02P10/25
Inventor 何蓓张述泉田象军李卓朱言言程序
Owner BEIHANG UNIV
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