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Fast manufacturing method of film hole without recast layer for Ni-based superalloy blade

A technology of nickel-based superalloy and manufacturing method, applied in the direction of manufacturing tools, metal processing equipment, laser welding equipment, etc., to achieve large economic benefits, simple operation, and beneficial fatigue life

Inactive Publication Date: 2011-02-09
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] In order to solve the problem of completely and quickly removing the recast layer, the object of the present invention is to provide a rapid manufacturing method for nickel-based superalloy blades without recast layer air film holes. The recast layer is removed by soaking in a chemical solution and drilled with a laser. or electric spark drilling process to form a complete set of process methods for rapid preparation of nickel-based superalloy blades without recast layer gas film holes

Method used

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  • Fast manufacturing method of film hole without recast layer for Ni-based superalloy blade
  • Fast manufacturing method of film hole without recast layer for Ni-based superalloy blade
  • Fast manufacturing method of film hole without recast layer for Ni-based superalloy blade

Examples

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Effect test

Embodiment 1

[0043] It is applied to the first-stage rotor blade of a high-pressure turbine of an aero-engine, and the blade is a directional cast nickel-based superalloy DZ4. The blades have a hollow labyrinth structure, and nearly a hundred air film holes are designed on both the inlet and outlet sides.

[0044] The hole is made by 80J Nd:YAG solid-state laser pulse irradiation, the energy of the laser beam is 80J, and the diameter of the hole is 0.5mm. There is a recast layer on the edge of the air film hole of the blade, with a thickness of 100 μm. Residues are accumulated in the hole, the shape of the hole is irregular, and there are cracks in the recast layer, as shown in Figure 2(a). These leaves are processed according to the above-mentioned technological process route, and the chemical solution is composed of: hydrochloric acid 20vol.%, nitric acid 30vol.%, copper sulfate 0.01 mol / liter, and the rest is water. The temperature of the chemical solution is 60°C, and the soaking time ...

Embodiment 2

[0046] It is applied to the first-stage rotor blade of high-pressure turbine of an aero-engine, and the blade is directional cast nickel-based superalloy DZ125. The blades have a hollow labyrinth structure, and nearly a hundred air film holes are designed on both the inlet and outlet sides.

[0047] Using CO 2 The hole is made by continuous laser irradiation, the power of the laser beam is 1200W, and the diameter of the hole is 1mm. There is a recast layer on the edge of the air film hole of the blade, with a thickness of 100 μm. Residues are accumulated in the hole, the shape of the hole is irregular, and there are cracks in the recast layer, as shown in Figure 2(a). These leaves are processed according to the above-mentioned technological process route, and the composition of the chemical solution is: hydrochloric acid 30vol.%, nitric acid 40vol.%, copper sulfate 0.012 mol / liter, and the rest is water. The temperature of the chemical solution is 50° C., the soaking time is...

Embodiment 3

[0049] It is applied to the first-stage rotor blade of a high-pressure turbine of an aero-engine, and the blade is a directional cast nickel-based superalloy DD6. The blades have a hollow labyrinth structure, and nearly a hundred air film holes are designed on both the inlet and outlet sides.

[0050] The hole is made by electric spark discharge, and the diameter of the hole is 0.3mm. There is a recast layer on the edge of the air film hole of the blade, with a thickness of 20 μm. Residues are accumulated in the hole, the shape of the hole is irregular, and there are cracks in the recast layer, as shown in Figure 2(a). These leaves are processed according to the above-mentioned technological process route, and the composition of the chemical solution is: hydrochloric acid 25vol.%, nitric acid 40vol.%, copper sulfate 0.012 mol / liter, and the rest is water. The temperature of the chemical solution is 70° C., the soaking time is 50 minutes, the frequency of ultrasonic vibration ...

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Abstract

The invention belongs to the metal hole processing technology, in particular to a fast manufacturing method of a film hole without a recast layer for a Ni-based superalloy blade. Firstly, holes with required sizes are manufactured on a blade body of the Ni-based superalloy blade of a gas turbine according to design requirements; secondly, chemical solution is adopted for soaking the perforated blade, ultrasonic vibration is needed in the entire soaking process of the blade in the chemical solution; and laser recast layers of the periphery of all of the holes of the blade and residues in hole paths or electric spark recast layers and residues thereof are thoroughly eliminated after soaking, and the blade with round, smooth holes without the recast layer is obtained. The hole manufacturing method has the characteristics of speediness, high efficiency, high quality and low cost, can eliminate polycrystalline structure layers of the periphery of the film cooling holes of monocrystal and directional freezing Ni-based superalloy blade, and keeps consistency of crystal structure of the blade. The film cooling holes without the recast layers can be prepared on DZ4, DZ125 and DD6 alloy blades by utilizing the method.

Description

technical field [0001] The invention belongs to the metal small hole processing technology, in particular to a rapid manufacturing method of a nickel-base superalloy blade without a recast layer gas film hole. Background technique [0002] Gas turbines are widely used in aero-engine aircraft, ground power generation devices, ships and rocket propulsion devices, etc., and are important contemporary power generators. Turbine blades made of nickel-based superalloys are important hot-end components of gas turbines. With the development of high-efficiency and high-power gas turbines, the temperature of the gas in front of the turbine is greatly increased, and the temperature that the blades need to withstand is getting higher and higher. For this reason, the blade material adopts a nickel-based superalloy with high Al and Ti content, and develops from a polycrystalline structure to the current directional and single crystal structure, while the blade manufacturing develops from ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23F1/28B23K26/38B23H9/14B23K26/382
Inventor 王茂才谢玉江王东生张杰
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI