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High-temperature alloy turbine blade repair material and repair process using same

A technology of turbine blades and superalloys, applied in metal processing equipment, manufacturing tools, arc welding equipment, etc., can solve problems such as surface damage

Active Publication Date: 2013-08-14
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

[0005] In order to solve the problem of superalloy turbine blade surface damage and other components repairing, the purpose of the present invention is to provide a superalloy turbine blade repair material and its supporting technology

Method used

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  • High-temperature alloy turbine blade repair material and repair process using same
  • High-temperature alloy turbine blade repair material and repair process using same
  • High-temperature alloy turbine blade repair material and repair process using same

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] In this example, the micro-arc spark deposition repair material is composed of the following components by weight percentage: Co15%, Cr18%, Al6.5%, Ta4%, Re2%, Y0.56%, C0.04%, and the rest is Ni . The above-mentioned repair material is made into a round bar with a diameter of 3mm and a length of 50mm, and the area to be repaired is surfacing by using the micro-arc spark deposition process. The surfacing welding process parameters are 800W power and 300HZ frequency. After the processing is completed, the repaired parts are put into a vacuum furnace for heat treatment. The heat treatment system: first solid solution at 1200°C for 3 hours, air-cooled to room temperature; then aged at 850°C for 10 hours, and cooled to room temperature with the furnace.

[0030] As shown in Figure 1(a)-(b), it can be seen that there is no crack in the repair layer, the bonding interface between the repair layer and the blade matrix is ​​metallurgical fusion, the structure is uniform, and the...

Embodiment 2

[0032] In this embodiment, the micro-arc spark deposition repair material is composed of the following components by weight percentage: Co18%, Cr10%, Al7%, Ta8%, Re2%, Hf0.24%, Y0.75%, C0.01%, The rest is Ni. The above-mentioned repair material is made into a round bar with a diameter of 6mm and a length of 100mm, and the micro-arc spark deposition process is used to perform surfacing welding on the area to be repaired. The surfacing welding process parameters are power 200W, frequency 150HZ, and the processing process is carried out in a vacuum glove box. After the processing is completed, the repaired parts are put into a vacuum furnace for heat treatment. The heat treatment system: first solid solution at 1150°C for 4 hours, then air-cooled to room temperature; then aged at 900°C for 4 hours, and cooled to room temperature with the furnace.

[0033] As shown in Figure 2(a)-(b), it can be seen that there is no crack in the repair layer, the bonding interface between the repa...

Embodiment 3

[0035] In this embodiment, the micro-arc spark deposition repair material is composed of the following components by weight percentage: Co5%, Cr20%, Al5%, Ta2%, Re5%, Hf2%, Y0.9%, C0.1%, and the rest are Ni. The above-mentioned repair material is made into a round bar with a diameter of 2mm and a length of 30mm, and the area to be repaired is surfacing by using the micro-arc spark deposition process. It is carried out in the box. After the processing is completed, the repaired parts are put into a vacuum furnace for heat treatment. The heat treatment system: first solid solution at 1230°C for 2 hours, then air-cooled to room temperature; then aged at 800°C for 20 hours, and cooled to room temperature with the furnace.

[0036] In this embodiment, the repair layer has no cracks, the bonding interface between the repair layer and the blade matrix is ​​metallurgical fusion, the structure is uniform, and the main strengthening phase is γ'.

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Abstract

The invention belongs to high-temperature alloy turbine blade repair and remanufacturing technology, and in particular discloses a high-temperature alloy turbine blade repair material and a repair process using the repair material. The micro-arc spark deposition repair material comprises the following ingredients based on weight percent: 45-60% of Ni, 0-25% of Co, 10-25% of Cr, 5-7% of Al, 2-8% of Ta, 0-6% of Re, 0-2% of Hf, 0-1% of Y and 0-0.1% of C, and the total weight is 100%. The repair process comprises the following steps of: fabricating a round bar with 2-6mm of diameter and 20mm of length using the above repair material, carrying out surfacing on the to-be-repaired area using the micro-arc spark deposition process, wherein the surfacing process parameters are as follows: power is 100W-1500W and the frequency is 100-500HZ, and the processing process is carried out under argon protection or in a vacuum glove box; placing the repair part into a vacuum furnace for thermal treatment after the processing is finished, wherein the thermal treatment process is as follows: solution treatment is carried out at 1150-1230 DEG C for 1-6 hours, and the aging is 4-20 hours at 800-900 DEG C. The novel repair material and the repair process using the repair material are provided for defect repair on the surface of the turbine blade so that the repair of high gamma' high-temperature alloy blade using the high gamma' high-temperature alloy repair material is possible and a novel solution plan is provided for the near / equal strength repair of the high-temperature alloy blade.

Description

technical field [0001] The invention belongs to high-temperature alloy turbine blade repair and remanufacturing technology, specifically a high-temperature alloy turbine blade repair material and a repair process thereof. Background technique [0002] Al and Ti are the main precipitation strengthening elements of high-strength nickel-based superalloys. With the increase of Al+Ti content, the volume percentage of precipitation strengthening phase γ′-Ni3(Al,Ti) in the alloy increases, and the high-temperature strength of the alloy increases accordingly. Modern high-performance aero-engines and gas turbine blades are mainly made of high-Al+Ti nickel-based superalloys. These components are expensive. For example, the price of IN-738 alloy polycrystalline blades produced by GE is about 15,000 US dollars per piece, and the price of directional and single crystal blades exceeds 30,000 US dollars per piece. These parts work in high temperature, high pressure, corrosive gas environm...

Claims

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Application Information

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IPC IPC(8): C22C19/05C22C30/00B23K9/04
Inventor 谢玉江王明生杨彦红韩旭
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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