Method for preparing reignition turbine first-stage work bladetip wear-resistant coating

A wear-resistant coating and blade technology, applied in the direction of coating, metal material coating process, etc., can solve the problems of matrix cracks, the influence of the safety and life of turbine working blades, and no research reports, and achieve a large coating thickness. , The effect of many hard reinforcing phases and high bonding strength

Inactive Publication Date: 2010-05-12
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, the wear-resistant coating is prepared on the tip surface of the first-stage working blade of the heavy-firing turbine in China, which is mainly prepared by argon tungsten shielded arc welding, which has good wear resistance, but the substrate under the surfacing welding will produce cracks. The use safety and life of turbine working blades have an impact
[0004] At present, there are

Method used

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  • Method for preparing reignition turbine first-stage work bladetip wear-resistant coating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0018] The first-stage working blade of the reburning turbine is fixed on the workbench of the laser coating equipment, with the blade tip facing up; operate the numerical control panel to move the infrared scanning device, and use the infrared beam to scan the edge of the blade tip surface. The diameter of the infrared beam is 3mm. The outer edge of the infrared beam during scanning is tangent to the outer edge of the leaf tip surface; according to the scanning trajectory, the scanning trajectory program control program records the positions of 18 scanning points, and the trajectory program control program automatically fits to generate the laser beam scanning trajectory during laser coating. The formed curve is similar to the shape of the outer edge of the blade tip surface scanned by the infrared beam.

[0019] Start the laser generating device of the laser coating equipment, under the condition that the inert gas purges and protects the tip surface of the blade, the alloy p...

Embodiment 2

[0032] The scanning trajectory method is the same as that in Embodiment 1, and the scanning trajectory program-controlled program records 19 scanning point positions.

[0033] Start the laser generating device of the laser coating equipment, under the condition that the inert gas purges and protects the tip surface of the blade, the alloy powder is synchronously delivered to the tip surface of the blade, and the alloy powder is melted with the laser beam to prepare a wear-resistant coating. The diameter of the laser spot is The scanning speed is 2.5mm, the scanning speed is 100mm / min, the transmission speed of the alloy powder is 4L / min, the output power of the laser is 2000W, and the laser beam is scanned according to the trajectory to complete the coating.

[0034] The alloy powder is a Co-based self-fluxing alloy powder, and its composition by weight percentage is C 1.3%, Cr 30.0%, Si 1.3%, Fe 3.2%, W 4.3%, Ni 3.0%, and the balance is Co.

[0035] The inert gas is argon, an...

Embodiment 3

[0038] The scanning trajectory method is the same as that in Embodiment 1, and the scanning trajectory program control program records 20 scanning point positions.

[0039] Start the laser generating device of the laser coating equipment, under the condition that the inert gas purges and protects the tip surface of the blade, the alloy powder is synchronously delivered to the tip surface of the blade, and the alloy powder is melted with the laser beam to prepare a wear-resistant coating. The diameter of the laser spot is The scanning speed is 3mm, the scanning speed is 300mm / min, the transmission speed of the alloy powder is 8L / min, the output power of the laser is 3000W, and the laser beam is scanned according to the trajectory to complete the coating.

[0040] The base material of the first-stage working blade of the reburning turbine is nickel-based cast superalloy K488, and the alloy powder is Co-based self-fluxing alloy powder, and its composition is C 1.1%, Cr 29.0%, Si 1...

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Abstract

The invention discloses a method for preparing a reignition turbine first-stage work bladetip wear-resistant coating, which comprises the following steps of: (1) scanning the edge of the end face of the bladetip by using an infrared scanning device of laser coating equipment to enable a scanning track program control program to record the position of a scanned point; and (2) starting a laser generator of the laser coating equipment, transferring alloy powder to the end face of the bladetip under the protection of inert gases, and melting the alloy powder with laser beams. The matrix material of the reignition turbine first-stage work blade is a nickel-based cast high-temperature alloy K488 and the alloy powder is Co-based self-fusing alloy powder. The method for preparing the coating improves the high-temperature wear resistance of the coating, also improves automatic control level and production efficiency of the coating preparation and guarantees the stability of the quality of the product.

Description

technical field [0001] The invention relates to a method for preparing a coating of a turbine blade, in particular to a method for preparing a wear-resistant coating for a first-stage working blade of a reburning turbine. Background technique [0002] As the operating conditions of aero-engines and gas turbines become more and more severe, the requirements for performance are getting higher and higher. Therefore, special coating materials and preparation technologies have become one of the key technologies in the manufacture of modern aero-engines and gas turbines. Coatings are mainly divided into thermal barrier coatings, wear-resistant coatings, sealing coatings, erosion-resistant coatings, and dimension repair coatings, among which wear-resistant coatings require higher hardness and lower coefficient of friction. [0003] The service life of heavy-duty gas turbines is long, and the service life of the first-stage turbine blades with large size and complex structure is req...

Claims

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Application Information

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IPC IPC(8): C23C24/10C22C19/07
Inventor 祝文卉高宇刘佳涛孟庆武李伟剑张湘君王长利
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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