High-temperature abradable seal coating and preparation method thereof

A sealing coating and wear-resistant technology, which is applied in the direction of coating, metal material coating process, fusion spraying, etc., can solve the problems of turbine rotor blade tip wear, coating loss of abradable effect, high probability of coating cracking, etc. , to achieve the effect of reducing wear, simple structure and improving sealing effect

Inactive Publication Date: 2018-06-19
AECC AVIATION POWER CO LTD
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

The high-temperature sealing coating invented by Beijing Aeronautical Manufacturing Engineering Research Institute (Patent No.: 201410616508.4) has large pores, and oxygen is easy to oxidize the coating MCrAlY in a high-temperature environment, forming Al2O3, Cr2O3 and other hard and brittle oxide phases. This increases the hardness of the coating, and the tip of the turbine rotor blade that is worn against it during the use of the engine is severely worn, and the coating loses its abradability, and the coating structure is complex, the coating has a high probability of cracking, and batch production is difficult.

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  • High-temperature abradable seal coating and preparation method thereof

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preparation example Construction

[0028] In the preparation method of the high-temperature abradable sealing coating of the present invention, the sprayed coating is subjected to stress relief and diffusion treatment by vacuum heat treatment every 0.8-1.5 mm of spraying, and the vacuum heat treatment is such that the vacuum degree is less than or equal to 6.65×10 -2 Under the vacuum environment of pa, the coated coating is kept at 950℃~1100℃ for 4h~6h, and then slowly cooled to below 500℃.

[0029] In the preparation method of the high-temperature abradable sealing coating of the present invention, supersonic flame spraying adopts kerosene and oxygen as combustion spraying gas, and hydrogen and oxygen can also be used as combustion spraying gas, the flow rate of oxygen is 1700SCFH~2000SCFH, and the flow rate of kerosene is 4GPH~6GPH, nitrogen as carrier gas, flow rate is 20SCFH~30SCFH, powder feeding rate is 20g / min~40g / min, spraying distance is 300mm~450mm.

[0030] In the preparation method of the high-tempe...

Embodiment 1K465

[0035] Example 1 The preparation method of the high temperature abradable coating on the outer ring of the high pressure turbine of the K465 superalloy substrate

[0036]In this example, supersonic flame spraying equipment is used, and the base material is K465 superalloy to prepare a CoNiCrAlY high-temperature sealing coating on the outer ring of the high-pressure turbine. Specifically include the following steps:

[0037] Clean painted surfaces of parts with acetone or gasoline, then protect non-painted surfaces with thermal spray tape.

[0038] Use clean and dry 20-mesh alumina sand to sandblast the sprayed surface of the outer ring of the high-pressure turbine, the wind pressure is 0.4MPa, the surface roughness of the substrate after treatment is 7μm, and then the protective tape is removed.

[0039] The high temperature abradable coating is prepared on the surface of the sandblasted parts by supersonic flame spraying equipment. % Cr, 8 wt % Al, 0.5 wt % Y, and the balan...

Embodiment 2

[0042] Embodiment 2 The preparation method of high temperature abradable coating of single crystal superalloy substrate

[0043] The invention adopts supersonic flame spraying to prepare NiCrAlY high temperature sealing coating, and the base material is DD5 single crystal high temperature alloy. Specifically include the following steps:

[0044] The sprayed surface was cleaned with acetone or gasoline, and then the substrate was roughened by laser. The surface roughness of the treated substrate was 6 μm. A high-temperature abradable coating was prepared on the surface of the roughened DD5 single crystal substrate by supersonic flame spraying equipment. The powder adopts NiCrAlY alloy powder. Based on the mass of NiCrAlY alloy powder as 100%, the NiCrAlY alloy powder includes: 22wt% Cr, 10wt% Al, 1.0wt% Y, the balance is Ni, and the alloy powder particle size range is 15 ~45μm. The coating is vacuum heat treated for every 1.0mm of spraying, and the total thickness of the coat...

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Abstract

The invention provides a high-temperature abradable seal coating and a preparation method thereof. The MCrALY alloy powder is sprayed to the surface of a base body through a supersonic flame sprayingdevice to prepare a coating, multiple times of spraying are carried out on the surface of the base body, and the deposition thickness of the single spraying is smaller than or equal to 0.01mm; stressrelief and diffusion treatment are carried out on the sprayed coating with the thickness of 0.5-1.0mm by adopting vacuum heat treatment; and finally spraying is carried out to obtain a sealing coatingwith the thickness larger than or equal to 1.5mm. The sealing coating prepared by the preparation method has the advantages of oxidation resistance, high-temperature low hardness, abrasion resistance, high temperature stability, thermal shock resistance and high bonding strength, the working temperature can reach 1100 DEG C, the abrasion of a turbine rotor blade can be obviously reduced, the abrasion resistance and the reliability of the coating are improved, the service life of the coating is prolonged, the service life of the turbine rotor blade is obviously prolonged, the maintenance costof the engine is remarkably reduced, and the reliability of the engine is improved.

Description

technical field [0001] The invention belongs to the technical field of abradable coatings, and relates to a high-temperature abradable sealing coating and a preparation method thereof. Background technique [0002] The outer ring of the aero-engine turbine is in the environment of high temperature, high-speed counter-grinding, and high-speed airflow scouring. Improving the air path sealing between the outer ring of the turbine and the rotor blades can significantly improve the working efficiency of the turbine. The outer ring of the turbine is usually made of superalloy material. Superalloy has good high temperature strength, but its high temperature hardness, poor wearability, direct use is likely to cause damage and wear of the working blade, and poor air tightness. In addition, the high temperature oxidation resistance of the superalloy is poor, and it is easy to be ablated during the working process, which leads to the expansion of the tip clearance of the turbine blade...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/129C23C4/073C22C19/05C22C19/07
CPCC23C4/129C22C19/058C22C19/07C23C4/073
Inventor 王建锋梁小龙王斌利张会盈胡江波黄宝庆李迎军原红星
Owner AECC AVIATION POWER CO LTD
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