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Silicon-based composite coating, preparation method and application thereof and aero-engine

An aero-engine and composite coating technology, which is applied in the field of materials, can solve the problems of low temperature resistance of Si coating and cannot meet the requirements, and achieve the effect of improving high temperature viscosity and good heat resistance

Pending Publication Date: 2021-01-29
GUANGDONG INST OF NEW MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] At present, the temperature resistance of the Si coating used as the bonding layer in the EBC coating on the surface of the ceramic matrix composite is not high, which cannot meet the application requirements of the future high thrust ratio aeroengine (>12) turbine inlet temperature up to 1700 °C

Method used

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  • Silicon-based composite coating, preparation method and application thereof and aero-engine
  • Silicon-based composite coating, preparation method and application thereof and aero-engine

Examples

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preparation example Construction

[0064] The Si-HfO prepared by the preparation method provided by this application 2 Silicon based composite coating containing HfSiO 4 High temperature stable phase and form HfO with higher temperature in Si coating 2 High temperature resistant skeleton (such as figure 1 and figure 2 shown). The Si-HfO 2 The porosity of the silicon-based composite coating is about 0.1-0.3%. It is worth noting that the above-mentioned high-temperature stable phase and high temperature in the high-temperature-resistant framework can be understood as being resistant to a temperature of at least 1700°C.

[0065] Preferably, the above-mentioned silicon-based composite coating is Si-HfO 2 / Yb 2 Si 2 o 7 / Rare earth doped ZrO 2 Composite coating, that is, the coating includes Si-HfO arranged sequentially from the inside to the outside 2 Layer, Yb 2 Si 2 o 7 layer and rare earth doped ZrO 2 Floor. In addition, the silicon-based composite coating of the present application can also be ...

Embodiment 1

[0069] The SiC / SiC composite material was ultrasonically cleaned with gasoline and alcohol in sequence, and then the non-sprayed area was pasted and protected with cloth glue, and then the sprayed area was sandblasted with No. 40 corundum grit at 0.5MPa pressure, and cleaned with dry high-pressure air Remove residual grit. Coating Si-HfO on the surface of CMC by atmospheric plasma spraying 2 Composite coating, the process is sprayed with Laval nozzle plasma spray gun, and the parameters of atmospheric plasma spraying are as follows: current is 550A, argon flow rate is 45SLPM, hydrogen flow rate is 8SLPM, Si powder delivery rate is 12g / min, HfO 2 Powder feeding rate is 5g / min, Si raw material and HfO 2The raw material is sent to the center of the flame flow independently and simultaneously by means of double-pipe independent simultaneous powder feeding. The obtained silicon-based composite coating has a porosity of 0.1%, and the coating is kept at 1400° C. for 1000 hours with...

Embodiment 2

[0071] The SiC / SiC composite material was ultrasonically cleaned with gasoline and alcohol in sequence, and then the non-sprayed area was pasted and protected with cloth glue, and then the sprayed area was sandblasted with No. 40 corundum grit at 0.5MPa pressure, and cleaned with dry high-pressure air Remove residual grit. Coating Si-HfO on the surface of CMC by atmospheric plasma spraying 2 Composite coating, the process is sprayed with Laval nozzle plasma spray gun, and the atmospheric plasma spraying parameters are as follows: current is 500A, argon gas flow rate is 40SLPM, hydrogen gas flow rate is 6SLPM, Si powder feeding rate is 8g / min, HfO 2 Powder feeding rate is 5g / min, Si raw material and HfO 2 The raw material is sent to the center of the flame flow independently and simultaneously by means of double-pipe independent simultaneous powder feeding. The porosity of the obtained silicon-based composite coating is 0.1%, and the coating is kept at 1400° C. for 900 hours ...

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Abstract

The invention provides a silicon-based composite coating, a preparation method and application thereof and an aero-engine, and belongs to the technical field of materials. The preparation method comprises the steps that atmospheric plasma spraying is adopted for spraying a Si-HfO2 composite coating on the surface of a ceramic matrix composite, and a double-pipe independent simultaneous powder feeding mode is adopted for atmospheric plasma spraying so that a Si raw material and an HfO2 raw material can be independently fed to a flame flow center at the same time. The method is simple and convenient to operate, a compact and uniform Si-HfO2 silicon-based composite coating can be obtained, and the service temperature of a silicon-based bonding layer in the silicon-based composite coating is increased. The prepared silicon-based composite coating has better temperature resistance and can meet the design requirements of aero-engines in the future. The silicon-based composite coating can beused for processing an aero-engine, so that the aero-engine has good heat resistance.

Description

technical field [0001] The invention relates to the field of material technology, in particular to a silicon-based composite coating, a preparation method and application thereof, and an aero-engine. Background technique [0002] A generation of materials, a generation of aircraft, aero-engines as the jewel in the crown of the industry, its service performance directly affects the air dominance of advanced aircraft. A high-performance engine is an important manifestation of a country's core competitiveness, and the service temperature (temperature-bearing capacity) of "one plate and two blades" (turbine plate, stationary blade, and moving blade) is an important symbol of an advanced engine. High thrust-to-weight ratio and high safety are the goals of future aero-engine development, and the continuous improvement of thrust-to-weight ratio will inevitably lead to an increase in the temperature of the front inlet of the aero-engine turbine. The inlet temperature of the turbine...

Claims

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Application Information

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IPC IPC(8): C04B41/87
CPCC04B41/009C04B41/5096C04B41/4527C04B41/87
Inventor 张小锋邓子谦牛少鹏王超李昕邓春明宋进兵毛杰杨焜徐丽萍戴红亮刘敏周克崧
Owner GUANGDONG INST OF NEW MATERIALS
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