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Laser hard-surface coating process method of titanium alloy vane of gas turbine

A technology of gas turbines and process methods, which is applied in the field of laser processing, can solve problems such as surface wear of blade tips and blade damping shoulders, and achieve the effects of high production yield, convenient hardness adjustment, and easy preparation

Inactive Publication Date: 2009-12-30
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

[0003] In order to solve the surface wear problem of the blade tip and the blade damping shoulder of the titanium alloy blade of the gas turbine, the object of the present invention is to provide a laser cladding hard surface coating process method for the titanium alloy blade of the gas turbine

Method used

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Examples

Experimental program
Comparison scheme
Effect test

preparation example Construction

[0037] (3) Preparation of powder: mechanical rolling ball mill or high-energy ball mill;

[0038] (4) Before laser irradiation, the leaves and powder are dried at 25℃~150℃.

[0039] 4. Laser irradiation: in Ar gas, He gas, N 2 Under the protection of one or two or more mixed gases, conduct CO 2 Continuous laser irradiation or solid-state laser pulse irradiation, with the help of a computer to control the laser round-trip irradiation;

[0040] In the present invention, the process parameters of the solid-state laser for laser irradiation are as follows:

[0041] The wavelength is 1.06 microns;

[0042] The energy of each pulse is 5~80J;

[0043] The pulse width is 2~16ms;

[0044] Scanning focusing beam spot diameter is 0.2~2mm;

[0045] The pulse frequency is 1~20Hz;

[0046] Scanning speed 1~10mm / s;

[0047] In the present invention, the process parameters of the carbon dioxide light laser for laser irradiation are as follows:

[0048] The wavelength is 10.6 microns;

[0049] Pow...

Embodiment 1

[0055] The secondary blades of a certain type of aero-engine compressor are made of TC4 titanium alloy with a dual-phase structure of α+β. The blade tip is arc-shaped and the wall thickness is about 1.0mm. The graphite block is used to make an overmold mold suitable for the tip of the blade and fix it on the tip of the blade. In order to maintain good cooling of the sleeve mold, a water cooling channel is also provided; in order to achieve good protection of the powder without oxidation, a protective gas nozzle is set on the sleeve mold. Will contain (5~20)wt% Cr 3 C 2 TC4+Cr 3 C 2 The evenly mixed powder is dried at 120°C for 2 hours, and is preset into the static powder bed formed by the mold set and the blade tip through an automatic feeding mechanism. Followed by 10 4 ~10 5 W / cm 2 Energy density CO 2 The laser beam is scanned and irradiated at a speed of 3-10mm / s, protected by argon, with a wavelength of 10.6 microns, an output power of 1000W, and a scanning focused beam spot ...

Embodiment 2

[0058] The damping shoulder of the compressor blade of a ground-based electric gas turbine is made of TAl 1 titanium alloy and the structure is α quasi-single-phase structure. Due to the wear of the damping surface of the shoulder, the height is reduced by about 0.5mm after polishing. The blade shoulder is divided into the back of the blade and the two sides of the basin, and the damping surface is spindle-shaped. Use copper material to make the over-molded mold, and clamp the over-molded mold on the shoulder of the blade. In order to maintain good cooling of the sleeve mold, a water cooling channel is also provided; in order to achieve good protection of the powder without oxidation, a protective gas nozzle is set on the sleeve mold. The coating powder is a high-energy ball-milled mixed powder of TAl 1 alloy powder + WC powder (WC powder accounts for 5-15 wt%), dried at 100°C for 2 hours, and placed the powder by glue bonding. The blade is fixed on the surface of the XY table con...

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Abstract

The invention belongs to a laser processing technology for enhancing the surface hardness, i.e. the wearing resistance of titanium or titanium alloy, in particular to a laser hard-surface coating process method of a titanium alloy vane of a gas turbine. In the invention, corresponding mantle clamping fixture is adopted according to the geometrical shapes of structure of vane apex or damping convex shoulders of the vane, powder is placed in the mantle clamping fixture in advance, a static powder bed is formed by the mantle clamping fixture and the powder added in the mantle clamping fixture, powder is uniformly placed on the vane apex of the vane or the damping convex shoulders of the vane in advance by the static powder bed, and inert gases or N2 is adopted to protect a laser radiation area and carry out laser radiation on the vane. A hard-surface coating with the hardness of 35 to 62 HRC and the thickness of 0.05 to 2.0mm can be formed on the vane apex or the damping convex shoulder of the titanium alloy vane when the invention is adopted. The invention has the advantages that vacuum is not needed; laser cladding can be carried out only under the protection of inert gases of Ar, He, and the like in atmosphere conditions; the operation is convenient; and the formed hard-surface coating and basal body of the vane have good adapter properties in physics and chemistry.

Description

Technical field [0001] The invention belongs to a laser processing technology for improving the surface hardness of titanium or titanium alloy, that is, the wear resistance, and is specifically a laser hard surface coating process method for a titanium alloy blade of a gas turbine. Background technique [0002] At present, gas turbines are widely used in aero engines and ground power generation devices. Titanium alloys are widely used in gas turbine compressor blades, intermediate casings, anti-icing shells and cups, oil pump impellers and other parts due to their high specific strength and excellent corrosion resistance. With the development of high-power and high-performance gas turbines, the use of titanium alloys will increase. However, titanium alloys are limited in application due to their lower hardness and non-wear resistance. At the same time, the titanium alloy parts currently in use often suffer wear damage and fail. For example, the compressor blades of gas turbines a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C24/10C22C14/00C22C32/00
Inventor 王茂才谢玉江王东生张杰
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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