Method for quick repair of nickel-base superalloy turbine disk at the end of service

A nickel-based superalloy and turbine disc technology, which is applied in the field of rapid repair of nickel-based superalloy turbine discs at the end of service, to achieve the effect of reducing the number density, simple operation and restoring mechanical properties

Active Publication Date: 2021-01-12
UNIV OF SCI & TECH BEIJING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there is no reasonable solution to this problem in the industry, and no effective means have been proposed to dissolve the brittle topological close-packed phase that already exists in the aging superalloy so as to restore performance and prolong the service life of high-temperature components.

Method used

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  • Method for quick repair of nickel-base superalloy turbine disk at the end of service
  • Method for quick repair of nickel-base superalloy turbine disk at the end of service
  • Method for quick repair of nickel-base superalloy turbine disk at the end of service

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] In this embodiment, pulse current treatment is performed on a small-sized aged superalloy turbine disk. Specific steps are as follows:

[0031] Step 1: Take 25mm×3.5mm×0.6mm aged turbine disk material, and sand the surface with 600, 1500, 2000 grit sandpaper in turn until there are no visible defects to the naked eye to ensure good contact with the pulse electrode.

[0032] Step 2: Determine the pulse processing parameters. The parameter range of the pulse current is set, and the parameters of the pulse current are determined to be 40Hz, 20μs, 3000A, and the action time is 10h.

[0033] The third step: pulse current processing. Fix the polished turbine disc on the output end of the pulse power supply with a clamp, and perform pulse current treatment on it for 20 min at room temperature.

[0034]The fourth step: observe the distribution of brittle topological close-packed phase by metallographic microscope. A 3.5mm×5mm×0.6mm slice was made from any position of the ag...

Embodiment 2

[0037] In this embodiment, pulse current treatment is performed on a small-sized aged superalloy turbine disk. Specific steps are as follows:

[0038] Step 1: Take 25mm×3.5mm×0.6mm aged turbine disk material, and sand the surface with 600, 1500, 2000 grit sandpaper in turn until there are no visible defects to the naked eye to ensure good contact with the pulse electrode.

[0039] Step 2: Determine the pulse processing parameters. The parameter range of the pulse current is set, and the parameters of the pulse current are determined to be 400Hz, 60μs, 200A, and the action time is 10min.

[0040] The third step: pulse current processing. Fix the small-sized turbine disk after grinding on the output end of the pulse power supply with a clamp, and perform pulse current treatment on it for 10 min at room temperature.

[0041] The fourth step: observe the distribution of brittle topological close-packed phase by metallographic microscope. A 3.5mm×5mm×0.6mm slice was made from a...

Embodiment 3

[0044] In this embodiment, pulse current treatment is performed on a small-sized aged superalloy turbine disk. Specific steps are as follows:

[0045] Step 1: Take 25mm×3.5mm×0.6mm aged turbine disk material, and sand the surface with 600, 1500, 2000 grit sandpaper in turn until there are no visible defects to the naked eye to ensure good contact with the pulse electrode.

[0046] Step 2: Determine the pulse processing parameters. The parameter range of the pulse current is set, and the parameters of the pulse current are determined to be 30000Hz, 75μs, 150A, and the action time is 5min.

[0047] The third step: pulse current processing. The small-sized turbine disk after grinding was fixed on the output end of the pulse power supply with a clamp, and it was treated with pulse current for 5 minutes at room temperature.

[0048] The fourth step: observe the distribution of brittle topological close-packed phase by metallographic microscope. A 3.5mm×5mm×0.6mm slice was made ...

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Abstract

The invention relate to the technical field of advanced aviation engine turbine disc service life prolonging, and provides a method for rapidly repairing a nickel-base high-temperature alloy turbine disc at the last phase of service. Pulse current treatment is performed on the performance-deteriorated high-temperature alloy turbine disc at the last phase of service at a certain temperature. The method remarkably improves the microscopic structure and mechanical property of the alloy turbine disc. The parameter range of pulse treatment includes the frequency of 10-30000 Hz, the pulse width of 10-500 [mu]s, the current of 10-5000 A and the acting time of 1 minute to 10 hours. Treatment can be performed on the turbine disc at the last phase of service at a low temperature, the number densityof a brittle topological dense heap phase in a material is reduced, and the mechanical property of the aged high-temperature alloy turbine disc is restored to the maximum extent; and the method is short in treatment time and low in temperature, can greatly reduce energy consumption, meets the requirement of the current industrial green development program, provides a new method for prolonging theservice life of the high-temperature alloy turbine disc, and has broad application prospects.

Description

technical field [0001] The invention relates to the technical field of life extension of advanced aero-engine turbine disks, in particular to a method for rapidly repairing a nickel-based superalloy turbine disk at the end of service. Background technique [0002] As the most important and most promising aero-engine temperature-bearing materials today, superalloys are widely used due to their good oxidation resistance, corrosion resistance, excellent tensile, durability, fatigue properties and long-term microstructure stability. It is used in modern aerospace technology and shows strong vitality in the field of advanced aerospace engines. The service life of the turbine disk has always been the focus of the industry. The service life of advanced aero-engines is generally around 5000h. When a superalloy turbine disk is used under long-term high temperature and high stress conditions, a large number of topological close-packed phases (TCP phases) will be formed in the materia...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C22F3/00
CPCC22F3/00
Inventor 张新房张海荷秦书洋
Owner UNIV OF SCI & TECH BEIJING
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