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High temperature protective coating material suitable for single crystal nickel-based superalloy blades

A technology of nickel-based superalloy and protective coating, which is applied in the direction of metal material coating process, coating, ion implantation plating, etc., can solve the problem of poor oxidation resistance, achieve excellent high temperature oxidation resistance, and solve thermal growth Oxide film wrinkling, avoiding the effect of damage to mechanical properties

Active Publication Date: 2019-11-01
INST OF METAL RESEARCH - CHINESE ACAD OF SCI +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But pure γ'-Ni 3 Al cannot form a single alumina protective film, and its oxidation resistance is not as good as traditional high-temperature protective coating materials such as MCrAlY coating, β-NiAl coating and NiPtAl coating that can form a single alumina protective film

Method used

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  • High temperature protective coating material suitable for single crystal nickel-based superalloy blades
  • High temperature protective coating material suitable for single crystal nickel-based superalloy blades

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] The casting target is vacuum smelted and its chemical composition is Ni-8Co-7Cr-10Al-2.5Re-6Ta-0.1Hf-0.2Y (wt.%), and it is ground into a flat plate with a size of 380×128×8mm. The target is installed on a magnetron sputtering apparatus, and a coating is prepared on the surface of a single crystal nickel-based superalloy RenéN5 blade, and the coating thickness is 30-35 μm. Measured by EPMA, the coating chemical composition is: 9.1wt.%Co, 7.9wt.%Cr, 10.4wt.%Al, 2.0wt.%Re, 5.6wt.%Ta, 0.1wt.%Hf, 0.2wt.% Y, 64.7 wt. % Ni.

[0024] like figure 1 , using XRD to analyze the phase composition of the coating, it can be seen that the main crystal phase of the coating is γ'-Ni 3 Al. Subsequently, the γ' phase coating sample of the present invention, the comparative NiCrAlY coating sample and the RenéN5 substrate sample were subjected to 1050 ℃ × 500h cyclic oxidation test. The result is as figure 2 It can be seen from the observation of the oxidation kinetic curve that the w...

Embodiment 2

[0026] The vacuum melting and casting target material has the chemical composition of Ni-9Co-6Cr-12Al-2W-2Mo-4Ta-0.05Hf-0.3Y (wt. %), and is processed into a flat plate with a size of 380×128×8 mm. The target was installed on a magnetron sputtering apparatus, and the blade prepared by the second-generation single crystal superalloy RenéN5 was used as the substrate. After the surface of the substrate was cleaned, it was loaded into a vacuum chamber to prepare the coating. After the coating is deposited, the prepared samples are taken out after the temperature of the vacuum chamber drops to room temperature, and then placed in a vacuum annealing furnace for annealing at 1050 °C for 1 h. According to EDS analysis, the chemical composition of the coating is: 9.8wt.%Co, 6.4wt.%Cr, 11.2wt.%Al, 1.7wt.%W, 1.6wt.%Mo, 3.6wt.%Ta, 0.1wt% .% Y, 65.6 wt. % Ni. The Hf content is too low to be detected.

[0027] The phase composition of the coating was analyzed by XRD, and the main crystal ...

Embodiment 3

[0029] Vacuum melting casting target, its chemical composition is Ni-7Co-8.5Cr-10Al-2.5Re-4.5W-0.5Mo-6.5Ta-0.2Hf-0.1Y (wt.%), processed into a size of Φ100mm×40mm Cylindrical target. The blade prepared by the second-generation single crystal superalloy CMSX-4 was used as the substrate, and the substrate was loaded into the vacuum chamber after surface cleaning. The coating was deposited by multi-arc ion plating technology, and the specific parameters were as follows: vacuum chamber temperature 200°C, argon gas pressure 0.1Pa, arc current 70A, DC bias voltage -50V, duty ratio 20%. After the coating is deposited, the prepared samples are taken out after the vacuum chamber temperature drops to room temperature, and then placed in a vacuum annealing furnace at 600°C for 2 hours and 1050°C for 1 hour.

[0030] In this embodiment, the coating thickness is 35-40 μm. Through EDS analysis, the chemical composition of the coating is: 7.2wt.%Co, 8.3wt.%Cr, 9.4wt.%Al, 1.8wt.%Re, 3.9wt.%...

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Abstract

The present invention provides a high temperature protective coating material suitable for single crystal nickel-based superalloy blades. The high temperature protective coating material is prepared from 1.5-10.0 wt.% of Cr, 3.0-12.0 wt.% of Co, 8.0-12.0 wt.% of Al, 0-3.0 wt.% of Re, 0-6.0 wt.% of W, 0-2.0 wt.% of Mo, 0.5-7.0 wt.% of Ta, 0.01-0.2 wt.% of Hf, 0.1-0.3 wt.% of Y, and the balance Ni;and the high temperature protective coating material has a phase equilibrium structure of gamma' phase at 1050 DEG C. The high-temperature oxidation performance of a coating prepared from the high-temperature protective coating material is superior to that of an MCrAlY (M is Ni, Co, or NiCo) coating and a beta-NiAl coating, and comparable to that of a NiPtAl coating. The coating forms metallurgical bond with a substrate, but not like the MCrAlY coating, the beta-NiAl coating or the NiPtAl coating which forms a secondary reaction zone with a single crystal substrate, so that the problem that the coating damages the mechanical property of the single crystal substrate is avoided. The coating prepared from the material can be used as an independent high-temperature-resistant corrosion-resistant coating, and can also be used as a bonding layer of a thermal barrier coating, and the prepared thermal barrier coating has better thermal shock resistance life than a NiPtAl / YSZ thermal barrier coating.

Description

technical field [0001] The invention belongs to the field of high-temperature protective coatings, and particularly provides a high-temperature protective coating material suitable for single-crystal nickel-based superalloy blades. Background technique [0002] Gas turbine engines are the core of advanced aircraft, high-speed ships, and high-efficiency and clean power plants. Single crystal blades, high-efficiency cooling, and thermal barrier coatings are called the three key technologies of gas turbine engines. The thermal barrier coating is mainly composed of two parts, the outer layer is a low thermal conductivity ceramic layer, and the inner layer is a metal bonding layer. Among them, the function of the ceramic layer is to reduce the temperature of the blade, and the metal bonding layer can form a protective oxide film at high temperature, thereby protecting the internal alloy material. Traditional metal bonding layers mainly include diffusion coatings and MCrAlY cladd...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C23C14/35C23C14/16C23C14/58
CPCC22C19/057C22C19/058C23C14/165C23C14/35C23C14/5806
Inventor 朱圣龙姚红蕊鲍泽斌沈明礼王成牛云松王福会陈明辉
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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