Low-damage processing method of film holes in single crystal high-pressure-turbine hollow blade of aircraft engine

An aero-engine, hollow blade technology, applied in metal processing equipment, manufacturing tools, welding equipment and other directions, can solve the problem that the fatigue life of parts cannot be well guaranteed, avoid recrystallization, prevent damage to the wall, improve The effect of surface integrity

Active Publication Date: 2017-04-26
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0005] Aiming at the fact that the fatigue life of parts cannot be well guaranteed by the processing of air film holes in aero-engine turbine blades in the prior art, the problem to be solved by the invention is to provide an aero-engine single-crystal high-vortex hollow blade that can form excellent hole-making quality A low-damage processing method for gas film holes

Method used

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  • Low-damage processing method of film holes in single crystal high-pressure-turbine hollow blade of aircraft engine
  • Low-damage processing method of film holes in single crystal high-pressure-turbine hollow blade of aircraft engine

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Effect test

Embodiment 1

[0056] Parts: a single crystal high-vortex hollow blade of an aero-engine;

[0057] Before processing the air film holes, use absorbent cotton dipped in absolute alcohol to carefully wipe the surface of the blade, including the leaf pot, leaf back, tenon and other areas, to ensure that the area to be processed is completely covered, and then put the cleaned blade into a 70°C drying oven for drying Dry for 30min.

[0058] During this period, adjust the clamping state of the fixture and the blade to ensure the relative coordinates between the machine tool and the origin of the blade. Lock the clamp and blade at the same time.

[0059] Before the laser gas film hole, through the three-dimensional scanning auxiliary positioning module, the blade is scanned in all directions, and the estimated time is 10 minutes. Afterwards, point cloud processing is performed on the data points obtained after scanning to form hole position coordinate point data and generate a coordinate file, wh...

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Abstract

The invention provides a low-damage processing method of film holes in a single crystal high-pressure-turbine hollow blade of an aircraft engine. The low-damage processing method comprises the following steps: wiping the surface of the blade through degreasing cotton with absolute alcohol; transferring into a drying box to dry; arranging a clamp on a machine table, and aligning; assembling the dried blade on the clamp and locking; presetting scanning system parameters; scanning the blade; saving axis moving coordinate value of each hole to be processed under an automatically-generated machine coordinate system as a *.xls file; importing and generating a hole position file; performing compensative correction on the deviation value of a focus position of the hole to be processed; and setting the optimized laser processing technological parameters through a main processing interface. With the adoption of the low-damage processing method, the processed hole is outstanding in quality; a remelting layer, microcacks and recrystallization can be avoided after the single crystal material is processed, so that subsequent processing can be saved, and as a result, the fatigue life and the processing cycle of the blade can be prolonged and improved; the ablation threshold of the single crystal material can be effectively reduced; the recrystallization of the single crystal material can be avoided.

Description

technical field [0001] The invention relates to a processing method of an aero-engine component, in particular to a processing method of a single-crystal high-vortex hollow blade air film hole of an aero-engine with low damage. Background technique [0002] Aeroengine turbine blade air film hole processing is a key technology in blade manufacturing. An engine needs to drill more than 100,000 holes. The processing quality of the gas film hole determines the service life and stability of the part. At present, the most urgent need to be solved in the engine industry is the thermal influence problems such as remelted layer and micro cracks in the process of machining the gas film hole of the turbine blade. On this basis, the consistency of the hole needs to be further improved. [0003] At present, the traditional methods of machining the gas film holes of engine turbine blades are mainly EDM drilling, nanosecond laser drilling and electro-hydraulic beam drilling. Traditional ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23K26/382B23K26/60
CPCB23K26/382B23K26/60
Inventor 李伟剑桓恒刘瑞军高宇
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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