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A high-temperature ceramic-based abradable sealing coating structure and its preparation method

A high-temperature ceramic and sealing coating technology, which is applied in the coating, metal material coating process, fusion spraying, etc., can solve the problems of affecting the working safety of the engine, coating peeling off, large coating friction coefficient, etc.

Active Publication Date: 2020-07-07
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Although the current plasma sprayed nickel-chromium-aluminum-yttrium-based, cobalt-nickel-chromium-aluminum-yttrium-based and cobalt-chromium-aluminum-yttrium-based high-temperature sealing coatings can work at a temperature of 1100°C, the coating has a large friction coefficient and high hardness, which is harmful to engine blade wear. Seriously, the coating is oxidized significantly during high temperature operation, and the coating often peels off, which affects the safety of the engine.

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  • A high-temperature ceramic-based abradable sealing coating structure and its preparation method
  • A high-temperature ceramic-based abradable sealing coating structure and its preparation method

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preparation example Construction

[0029] Embodiments of the present invention aim at existing plasma spraying 6~8%Y in the prior art 2 o 3 · ZrO 2 The working temperature of the ceramic-based sealing coating cannot exceed 1200 °C. Although the plasma sprayed nickel-chromium-aluminum-yttrium-based, cobalt-nickel-chromium-aluminum-yttrium-based and cobalt-chromium-aluminum-yttrium-based high-temperature sealing coatings currently used can work at a temperature of 1100 °C, but The coating has a large friction coefficient and high hardness, which will cause serious wear to the engine blades. The coating will oxidize significantly during high-temperature operation, and the coating will often peel off and fall off, which will affect the safety of the engine. The invention provides a high-temperature ceramic-based abradable sealing coating structure and a preparation method thereof. High temperature ceramic based abradable seal coating structure includes:

[0030] The bottom layer of NiCoCrAlTaY high temperature a...

Embodiment 1

[0046] Clean the superalloy turbine outer ring parts with 120 aviation gasoline, and then sandblast the parts with clean and dry 46 mesh brown corundum sand. The NiCoCrAlTaY bottom layer was sprayed on the sandblasted turbine outer ring parts by vacuum plasma spraying process, the spraying power was 54KW, the spraying distance was 280mm, and the bottom layer thickness was 0.20mm.

[0047] The atmospheric plasma spraying process is used to prepare the abradable sealing coating surface layer on the vacuum plasma sprayed NiCoCrAlTaY bottom layer, and the surface layer plasma sprayed powder material is made of Sc 2 o 3 , Y 2 o 3 Binary rare earth oxide co-doped ZrO 2 Ceramic powder+6%CaF 2 +8% polyphenylene is mechanically mixed, the atmospheric plasma spraying power is 42KW, the spraying distance is 70mm, and the surface layer thickness is 2.2mm.

[0048] Heat the parts with abradable sealing coating at 550°C for 8 hours in a box-type resistance furnace to remove the polyphe...

Embodiment 2

[0051] Clean the superalloy turbine outer ring parts with 120 aviation gasoline, and then sandblast the parts with clean and dry 46 mesh brown corundum sand. The NiCoCrAlTaY bottom layer is sprayed on the sandblasted turbine outer ring parts by vacuum plasma spraying process, the spraying power is 50KW, the spraying distance is 270mm, and the bottom layer thickness is 0.15mm.

[0052] The atmospheric plasma spraying process is used to prepare the abradable sealing coating surface layer on the vacuum plasma sprayed NiCoCrAlTaY bottom layer, and the surface layer plasma sprayed powder material is made of Sc 2 o 3 , Y 2 o 3 Binary rare earth oxide co-doped ZrO 2 Ceramic powder+8%CaF 2 +12% polyphenylene is mechanically mixed, the atmospheric plasma spraying power is 42KW, the spraying distance is 70mm, and the surface layer thickness is 2.5mm.

[0053] Heat the parts with abradable sealing coating at 600°C for 6 hours in a box-type resistance furnace to remove the polyphenyl...

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Abstract

The invention provides a high-temperature ceramic-based abradable seal coating structure and a preparation method thereof. The coating structure comprises a base layer and an a surface layer, whereinNiCoCrAlTaY high-temperature antioxidant materials are sequentially laminated on the surface of a base body of a high-temperature alloy turbine outer ring part, and the surface layer is formed by mixing Sc2O3 and Y2O3 binary rare earth oxide with ZrO2 materials, CaF2 materials and polyphenyl ester materials; and in the surface layer materials, the polyphenyl ester is a pore-forming material, and CaF2 is a high-temperature antifriction self-lubricating ceramic material. The high-temperature ceramic-based abradable seal coating can be applied to sealing of gas paths of an aero-engine and a ground gas turbine high-pressure turbine, the working temperature can reach 1300 DEG C, and the requirement for sealing the gas paths of the aero-engine and the ground gas turbine high-pressure turbine.

Description

technical field [0001] The invention relates to the technical field of high-temperature coating preparation for aero-engines and ground gas turbines, in particular to a high-temperature abradable sealing coating structure and a preparation method thereof. Background technique [0002] High-pressure turbine abradable seal refers to the gas path sealing method adopted to prevent high-temperature gas from leaking from the high-pressure side along the tip of the blade to the low-pressure side. The high temperature abradable sealing coating is a functional coating used to control the gas path gap of a gas turbine engine. The radial gap between the outer ring of the engine turbine and the tip of the rotor blade directly affects the efficiency of the turbine, which has a great impact on the performance of the engine. In order to obtain excellent performance of the gas turbine engine, the tip of the rotor blade should be minimized Radial clearance with the outer ring of the turbine...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/08C23C4/10C23C4/134C23C4/18
CPCC23C4/08C23C4/10C23C4/134C23C4/18
Inventor 李其连李淑青王纯杨伟华
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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