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High-temperature gradient sealing coating for gas turbine and preparation method thereof

A gas turbine and sealing coating technology, which is applied in coating, metal material coating technology, metal processing equipment, etc., can solve the problem that the gas corrosion resistance of the underlying material cannot meet the gas turbine, reduce the service life of the sealing coating and equipment, and cause problems. Applicable to problems such as ground gas turbines, to achieve the effect of preventing oxidation failure rate, preventing shedding failure, and reducing interface stress

Pending Publication Date: 2020-12-04
武汉钢铁有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the improvement of material performance and structural design alone can no longer meet the needs of industries such as high thrust-to-weight ratio and high flow in the rapidly developing gas turbine, and high-temperature protective coating technology has become the most important way to achieve efficient operation of gas turbines
The fourth generation of high-temperature protective coatings - zirconia coatings have been applied to some aero-engine high-temperature components (guide vanes, flame tubes, heat shields, etc.), but this coating is not suitable for ground gas turbines
Because there are two obvious differences between gas turbines and aero engines: the service life of gas turbines (or one-time repair life) is more than 20 times that of aero engines, reaching 100,000 hours (overhaul life of 25,000 hours), while the thermal power currently used for aero engines The service life of the barrier coating is only a few hundred hours; the gas corrosion resistance of the underlying material cannot meet the needs of gas turbines. The combustion and compression media of CCPP gas turbines in iron and steel enterprises are mainly blast furnace and coke oven gas, which are by-products of iron and steel enterprises. The cleanliness of the gas is extremely low , the gas contains a large amount of corrosive pollutants such as tar, naphthalene, benzene, sulfide, water vapor and solid particles, which make the high-temperature parts withstand more severe high-temperature corrosion, making the organic active groups embrittled, aging and failing, reducing the Sealing coating and equipment service life, so it is urgent to develop and research a high-temperature sealing coating suitable for CCPP gas turbines in the domestic steel industry

Method used

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  • High-temperature gradient sealing coating for gas turbine and preparation method thereof
  • High-temperature gradient sealing coating for gas turbine and preparation method thereof
  • High-temperature gradient sealing coating for gas turbine and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] A method for preparing a high-temperature gradient sealing coating for a gas turbine, comprising the steps of:

[0031] (1) Milling

[0032] (1.1) Ingredients and coating:

[0033] Adhesive bottom layer: The bottom layer material is NiCoCrAlY alloy powder, and the raw material powder is accurately weighed according to the weight percentage, Cr40%; Al 12%; Ni 36%, Co 8%; Y 4%; the raw material is passed through the ternary mixed binder and A multi-layer mechanical agglomeration coating process is used to make a bonded bottom layer slurry.

[0034] Oxygen barrier layer: Accurately weigh raw material powder by weight percentage, 65% zirconium niobium alloy, 15% nanometer α-Al 2 o 3 , 20% nano-aluminum powder, in which zirconium-niobium alloy is made by mixing zirconium (Zr) and niobium (Nb) in a ratio of 1:1. Process to make oxygen barrier layer slurry.

[0035] Sealing surface layer: Accurately weigh raw material powder according to weight percentage, 75% nano ZrO 2...

Embodiment 2

[0053] A method for preparing a high-temperature gradient sealing coating for a gas turbine, comprising the steps of:

[0054] (1) Milling

[0055] (1.1) Ingredients and coating:

[0056] Adhesive bottom layer: the bottom layer material is NiCoCrAlY alloy powder, and the raw material powder is accurately weighed according to the weight percentage, Cr48%; Al 15%; Ni 30%, Co 5%; Y 2%; the raw material is passed through the ternary mixed binder and A multi-layer mechanical agglomeration coating process is used to make a bonded bottom layer slurry.

[0057] Oxygen barrier layer: Accurately weigh raw material powder by weight percentage, 70% zirconium niobium alloy, 10% nanometer α-Al 2 o 3 , 20% nano-aluminum powder, in which zirconium-niobium alloy is made by mixing zirconium (Zr) and niobium (Nb) in a ratio of 1:1. Process to make oxygen barrier layer slurry.

[0058] Sealing surface layer: Accurately weigh raw material powder according to weight percentage, 80% nano ZrO 2...

Embodiment 3

[0073] A method for preparing a high-temperature gradient sealing coating for a gas turbine, comprising the steps of:

[0074] (1) Milling

[0075] (1.1) Ingredients and coating:

[0076] Adhesive bottom layer: The bottom layer material is NiCoCrAlY alloy powder, and the raw material powder is accurately weighed according to the weight percentage, Cr30%; Al 10%; Ni 50%, Co 5%; Y 5%; A multi-layer mechanical agglomeration coating process is used to make a bonded bottom layer slurry.

[0077] Oxygen barrier layer: Accurately weigh raw material powder by weight percentage, 70% zirconium niobium alloy, 15% nanometer α-Al 2 o 3 , 15% nano-aluminum powder, in which zirconium-niobium alloy is made by mixing zirconium (Zr) and niobium (Nb) in a ratio of 1:1, and the raw materials are selected, pre-coated, and evenly coated by multiple layers Process to make oxygen barrier layer slurry.

[0078] Sealing surface layer: Accurately weigh raw material powder according to weight percen...

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Abstract

The invention relates to the technical field of coating preparation, in particular to a high-temperature gradient sealing coating for a gas turbine and a preparation method thereof. The high-temperature gradient sealing coating for the gas turbine comprises a bonding bottom layer, an oxygen barrier layer and a sealing surface layer, the spraying raw material of the bonding bottom layer is NiCrAl alloy agglomeration powder or NiCoCrAlY alloy agglomeration powder, the spraying raw material of the oxygen barrier layer is multi-component aluminum-coated zirconium-niobium alloy agglomeration powder, and the multi-component aluminum-coated zirconium-niobium alloy agglomeration powder comprises the components of 60-70wt% of zirconium-niobium alloy, 10-20wt% of nano alpha-Al2O3 and 20-30wt% of nano aluminum powder. The spraying raw material of the sealing surface layer is nano zirconium oxide based agglomerated powder, and the nano zirconium oxide based agglomerated powder comprises the components of 75-90wt% of nano ZrO2, 5-15wt% of nano Y2O3 and 5-20wt% of nano alpha-Al2O3. The prepared high-temperature gradient sealing coating for the gas turbine has the characteristic of long service life.

Description

technical field [0001] The invention relates to the technical field of coating preparation, in particular to a high-temperature gradient sealing coating for a gas turbine and a preparation method thereof. Background technique [0002] Iron and steel enterprises are high-energy-consuming enterprises, whose energy consumption accounts for 10-20% of the total energy consumption in the country, 20-25% of the total energy consumption of the industrial sector, and energy consumption accounts for about 25% of the production cost of the enterprise, while Gas produced in steel production accounts for 30-40% of the total energy, and is an important secondary energy source for steel enterprises. How to use the by-product gas to reduce energy consumption and improve the comprehensive utilization rate of energy is an important way for iron and steel enterprises to improve economic efficiency and realize green manufacturing. CCPP is the most efficient secondary energy saving device for i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/134C23C4/137C23C4/073C23C4/06C23C4/10C23C4/02C22C30/00C22C19/05C22C27/06B22F1/02B82Y30/00
CPCC23C4/134C23C4/137C23C4/073C23C4/06C23C4/10C23C4/02C22C30/00C22C27/06C22C19/058B82Y30/00B22F1/102
Inventor 刘刚锋粟伟明田维汉魏利明柯海刚胡翰
Owner 武汉钢铁有限公司
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