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Application of diffusion barrier material, high-temperature coating and preparation method and application thereof, and gas turbine hot end part

A hot-end component and coating technology, which is applied in metal material coating process, coating, ion implantation plating, etc., can solve the problems of anti-oxidant element consumption, coating failure, performance degradation, etc., and achieve high temperature stability and high temperature oxidation resistance, good compactness and thermal stability, simple preparation method

Active Publication Date: 2020-06-26
GUANGDONG INST OF NEW MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when the coating is exposed to high-temperature oxidizing environment for a long time, the oxidation resistance elements in the coating will be continuously consumed, which will eventually cause performance degradation and lead to coating failure.

Method used

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  • Application of diffusion barrier material, high-temperature coating and preparation method and application thereof, and gas turbine hot end part
  • Application of diffusion barrier material, high-temperature coating and preparation method and application thereof, and gas turbine hot end part
  • Application of diffusion barrier material, high-temperature coating and preparation method and application thereof, and gas turbine hot end part

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preparation example Construction

[0068] The present application also proposes a method for preparing the above-mentioned high-temperature coating, which may include the following steps: preparing an outer layer on the surface of the inner layer.

[0069] For reference, the preparation method of the inner layer may include, but is not limited to, magnetron sputtering, chemical vapor deposition or electron beam evaporation. In actual operation, the above method can be used to prepare the inner layer on the surface of the base alloy.

[0070] As an option, the substrate can be DD5 single crystal superalloy, DD6 single crystal superalloy, DZ22 nickel-based superalloy, DZ125 nickel-based superalloy, K403 nickel-based superalloy, K417 nickel-based superalloy, K423 nickel-based superalloy, IC6 single crystal superalloy or GH605 cobalt-based superalloy.

[0071] Preferably, before preparing the inner layer, the substrate can be cleaned first. For example, the substrate can be degreased and washed. Organic reagents...

Embodiment 1

[0090] The substrate is made of DD5 single crystal superalloy with a size of 20mm×10mm×3mm. Firstly, the magnetron sputtering technology is used to prepare MoSi of about 0.5μm 2 Inner layer, MoSi 2 The purity of the target material is 99.95 wt%. The substrate sample is ultrasonically degreased with acetone, cleaned with absolute ethanol, dried and placed in a vacuum chamber. Magnetron sputtering process parameters: substrate temperature 150°C, argon gas to maintain pressure 0.5Pa, target current 2.0A, pulse bias -100V, ion source current 1.0A. The outer layer of NiAlHfRu of about 70 μm was prepared by arc ion plating, and the preparation parameters of arc ion plating were: substrate temperature 350°C, argon pressure 2Pa, arc current 120A, DC bias voltage -50V, duty cycle 70%.

[0091] In this embodiment, the chemical composition of the NiAlHfRu coating is: Ni content 50 at.%, Al content 49 at.%, Hf content 0.5 at.%, Ru content 0.5 at.%.

[0092] The NiAlHfRu / MoSi obtained a...

Embodiment 2

[0094] The substrate is made of K417 nickel-based superalloy with a size of 20mm×10mm×3mm. Firstly, the magnetron sputtering technology is used to prepare MoSi with a thickness of about 5 μm. 2 inner layer. The substrate sample is ultrasonically degreased with acetone, cleaned with absolute ethanol, dried and placed in a vacuum chamber. Magnetron sputtering process parameters: substrate temperature 150°C, argon gas to maintain pressure 0.3Pa, target current 1.5A, pulse bias -200V, ion source current 1.0A. The outer layer of NiCoCrAlYTa of about 50 μm is prepared by electron beam evaporation plating method, and the preparation parameters are: substrate temperature 800 ° C, vacuum degree 3 × 10 -2 Pa, voltage 20KV, electron gun current 1.5A.

[0095] In this embodiment, the chemical composition of the NiCoCrAlYTa coating is: Co content 18wt.%, Cr content 30wt.%, Al content 10wt.%, Y content 1.5wt.%, Ta content: 2wt.%, the rest is Ni .

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Abstract

The invention provides application of a diffusion barrier material, a high-temperature coating and a preparation method and application thereof, and a gas turbine hot end part, and belongs to the technical field of high-temperature protective coatings. The components of the diffusion barrier material include MeSi2, and Me includes Cr or Mo. The diffusion barrier material is compact in crystal structure and good in high-temperature-oxidation-resistant property, and has good thermal expansion compatibility with a base material; the high-temperature coating comprises an outer layer and an inner layer with the diffusion barrier material; the high-temperature coating can inhibit mutual diffusion of alloy components between a base body and the coating, the high-temperature-oxidation-resistant capacity of the coating is improved, meanwhile the situation that the mechanical property of the base body is lowered due to mutual diffusion is avoided, and the service life of parts is prolonged; andthe preparation method of the high-temperature coating is mature and reliable and good in repeatability, and large-area industrial production is easy to implement; and both the diffusion barrier material and the high-temperature coating can be used for machining the gas turbine hot end part, and the gas turbine hot end part containing the diffusion barrier material or the high-temperature coatinghas the long service life and high working reliability.

Description

technical field [0001] The invention relates to the technical field of high-temperature protective coatings, in particular to an application of a diffusion barrier material, a high-temperature coating, a preparation method and application thereof, and a hot end component of a gas turbine. Background technique [0002] Gas turbine hot end components are subjected to high temperature, high pressure, and high load coupling during service, so high temperature protective coatings must be used to meet their service requirements. High temperature oxidation resistant coatings have been well applied in the high temperature protection of hot end components of gas turbines. However, when the coating is exposed to a high-temperature oxidizing environment for a long time, the oxidation-resistant elements in the coating will be continuously consumed, which will eventually cause performance degradation and lead to coating failure. [0003] In view of this, the present application is propo...

Claims

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Application Information

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IPC IPC(8): C23C14/30C23C14/18C23C14/06C23C14/32C23C14/35C23C4/134C23C4/131C23C4/129C23C4/08C23C4/073
CPCC23C14/30C23C14/32C23C14/35C23C14/0623C23C14/18C23C4/134C23C4/129C23C4/131C23C4/08C23C4/073
Inventor 石倩汪唯郭朝乾代明江林松盛王红莉苏一凡唐鹏韦春贝李洪
Owner GUANGDONG INST OF NEW MATERIALS
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