Method for overlaying wear-resistant layer of blade shroud of turbine working blade

A wear-resistant layer and blade technology, which is applied in the field of tungsten argon arc welding technology, can solve the problems of easy aging cracks in the matrix and increase the difficulty of surfacing welding operation, so as to improve the working life, wide application prospects and high technology maturity. Effect

Inactive Publication Date: 2011-06-29
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] For the above-mentioned special-shaped blade, the existing technology mainly has the following technical difficulties: First, the blade is cast with DZ417G alloy, and the sum of Al and Ti mass percentages is close to 10% in terms of chemical composition, which greatly exceeds that of high-temperature alloy materials. In the surfacing process, aging cracks are prone to appear in the weld heat-affected zone and its matrix...

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  • Method for overlaying wear-resistant layer of blade shroud of turbine working blade
  • Method for overlaying wear-resistant layer of blade shroud of turbine working blade

Examples

Experimental program
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Effect test

Embodiment 1

[0027] Embodiment 1 A method for surfacing wear-resistant layer of blade shroud of turbine working blade

[0028] The T800 cobalt-based wear-resistant alloy welding wire developed by the American GE company B50TF193 standard is used to surfacing the wear-resistant layer of the low-pressure turbine blade crown (small inclination, small damping surface "Z-shaped tooth" structure). The content of this embodiment is mainly as follows:

[0029] 1. Preparation before welding

[0030] 1.1 Solution heat treatment: The solution heat treatment system is to raise the temperature to 1220 ° C ± 10 ° C, keep it warm for 4.0h ~ 4.5h, and then cool it with argon in vacuum.

[0031] 1.2 Cleaning before welding: use mechanical grinding to clean the surfacing welding surface and its surrounding 15mm area, including the surface where the edge is connected to the surfacing welding surface, clean the welding wire, the surfacing welding surface and its surrounding area with acetone or alcohol, and ...

Embodiment 2

[0044] Embodiment 2 A method for surfacing wear-resistant layer of blade shroud of turbine working blade

[0045] The S-6 cobalt-based wear-resistant alloy welding wire developed by the American Metal Society AMS5788 standard is used to surfacing the wear-resistant layer of the blade crown ("Z-shaped tooth" structure) of the low-pressure turbine blade.

[0046] In this example, S-6 cobalt-based alloy welding wire is used, and its main component is Co-Cr-W alloy. Compared with Example 1, the inclination angle of the "Z-shaped tooth" of the working blade crown of this low-pressure turbine exceeds 90 degrees, which is relatively easy in welding operation, and does not need to be separately surfacing at the root of the transfer R, which is only applied to Example 1 Parameter 2 can complete the surfacing. The surface of the surfacing layer should be silver-gray metallic luster (depending on the alloy composition of the welding wire) after visual inspection after welding, and other...

Embodiment 3

[0047] Embodiment 3 A method for surfacing wear-resistant layer of turbine working blade crown

[0048] A method for overlaying a wear-resistant layer on a blade crown of a working turbine blade uses manual argon tungsten arc welding, and its specific process parameters meet the following requirements:

[0049] Welding wire selection: T800 cobalt-based wear-resistant alloy welding wire developed according to the standard B50TF193 of GE Company of the United States and S-6 cobalt-based wear-resistant alloy welding wire developed according to the standard AMS5788 of the American Institute of Metals; diameters are: φ1.6mm and φ1.2mm; tungsten Pole grade and diameter: WCe20φ2.0mm; nozzle diameter: φ12mm, welding current: 20A~25A, shielding gas flow: 10L / min~12L / min.

[0050] Specifically, in the method for overlaying the wear-resistant layer of the blade crown of the turbine working blade, when performing the operation of overlaying the "Z-shaped tooth" of the blade crown and tran...

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Abstract

The invention discloses a method for overlaying a wear-resistant layer of a blade shroud of a turbine working blade. In the method, manual tungsten electrode argon arc welding is used, and the specific process parameters meet the requirements that: welding wires are selected from a T800 cobalt-based wear-resistant alloy welding wire which is researched according to a B50TF193 standard of AmericanGeneral Electric Company and an S-6 cobalt-based wear-resistant alloy welding wire which is researched according to an American metal society standard AMS5788; the diameters are phi 1.6mm and phi 1.2mm respectively; a mark and the diameter of a tungsten electrode are WCe20 and phi 2.0mm; the diameter of a nozzle is phi 12mm; welding current is between 20 and 25A; and the flow rate of protective gas is between 10L/min and 12L/min. By the method, the condition of incomplete penetration or over-melting of a Z-shaped gear switching part R is avoided, the problem of overheating of welding is also solved, and the occurrence probability of welding cracks is greatly reduced or avoided. The method completely meets the requirements of the wear-resistant layer in a high-temperature working state after welding.

Description

Technical field: [0001] The invention relates to a tungsten argon arc welding process for a special-type turbine working blade crown, and particularly provides a method for overlaying a wear-resistant layer on a turbine working blade crown. Background technique: [0002] In the prior art, the working blades of the I-IV stages of the low-pressure turbine of a certain type of engine are made of DZ417G directionally solidified alloy. It has the characteristics of small inclination angle and small damping surface. [0003] Because the working blades of the middle and low-pressure turbines of the above-mentioned certain type of engine are directional solidified blades without margin, and the blade crown is a "Z-shaped tooth" structure. In order to effectively reduce the wear problem between the blades, usually the "Z-shaped tooth" The wear-resistant alloy layer is surfacing on the surface, which greatly improves the working life of the turbine blade. Generally speaking, the mai...

Claims

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Application Information

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IPC IPC(8): B23K9/04B23K9/16B23K9/095B23K9/235
Inventor 宋文清曲伸邵天巍杜静高山李光泽
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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