Abradable sealing composite coating material and preparation method thereof

A composite coating and abrasion technology, which is applied in the field of aero-engines, can solve problems such as cracking and peeling, frequent repairs of coatings, and affecting the safety of the engine, so as to reduce thermal stress, avoid high-temperature oxidation, and have good resistance to water vapor corrosion and corrosion resistance. The effect of oxidation properties

Pending Publication Date: 2022-04-12
SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the thermal expansion coefficient of ceramic matrix composites (4.5-5.9×10 -6 K -1 ) significantly lower than nickel-based superalloy materials (15-17×10 -6 K -1 ), 6~8wt.%Y 2 o 3 · ZrO 2 The thermal expansion coefficient of the ceramic base material (10-11.8×10 -6 K -1 ) does not match the ceramic matrix composite material, and 6~8%wt.%Y 2 o 3 · ZrO 2 When the material works above 1200°C, the transformation from tetragonal phase to cubic phase and monoclinic phase will occur during the circulating cooling process. The generation of monoclinic phase will cause the volume of the coating to expand (about 4%) and crack and peel off. The coating needs frequent repairs. Affect the safety of engine work

Method used

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  • Abradable sealing composite coating material and preparation method thereof
  • Abradable sealing composite coating material and preparation method thereof
  • Abradable sealing composite coating material and preparation method thereof

Examples

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preparation example Construction

[0037] Preparation of the bonding layer. Specifically, the Si-containing bonding layer is prepared on the surface of the base material, that is, the plasma spraying method is used, and the silicon powder is used as the raw material to spray the silicon coating. The parameters of the plasma spraying process include: current 300-700A, argon gas flow rate 40 ~60slm, hydrogen flow rate 5~15slm, spraying power 30~50kW, spraying distance 100~300mm, powder feeding rate 10~35r / min. The thickness of the adhesive layer is 50 to 500 μm, preferably 50 to 200 μm. The SiC bonding layer can also be prepared. On the basis of preparing the silicon coating, the SiC coating can be formed by heat treatment at a high temperature of 1400-1800 °C for 1-4 hours in an atmosphere protection.

[0038] Preparation of toppings. The powder used for the wearable sealing surface layer is sprayed on the substrate with the bonding layer by using the plasma spraying method. Among them, the parameters of the ...

Embodiment 1

[0044] Step 1: Sandblasting the surface of the C / SiC substrate with a blasting pressure of 0.2 MPa to obtain a surface pretreated substrate.

[0045] Step 2: Prepare a Si layer on the surface of the pretreated substrate by using a plasma spraying method, and the spraying process parameters are shown in Table 2.

[0046] Table 2 Process parameters of plasma sprayed Si coating

[0047] Plasma gas Ar 38slpm Powder carrier gas Ar 2.5 slpm electric current 500A Plasma gas H 2

[0048] Step 3: heat-treat the substrate with the Si coating in a vacuum atmosphere furnace at 1550° C. for 3 hours, so that the Si layer reacts in situ to form a SiC bonding layer.

[0049] Step 4: Prepare Yb on the surface of the SiC bonding layer by plasma spraying 2 Si 2 o 7 -10wt.% h-BN composite coating, the spraying process parameters are shown in Table 3.

[0050] Table 3 Plasma sprayed Yb 2 Si 2 o 7 Process parameters of -10 wt% h-BN coating

[0051] Plasma...

Embodiment 2

[0054] Using C / SiC as the substrate, the Si layer is prepared by plasma spraying method as the bonding layer, and the surface layer is Yb 2 Si 2 o 7 Coating, spraying process parameters are shown in Table 4. The prepared coating microhardness Hv 0.5 It is 4.44±0.23GPa. The abradability of the coating was evaluated by friction and wear experiments, and the evaluation conditions were the same as in Example 1. The average friction coefficient of the coating is 0.178±0.007, and the volume wear rate is (13.82±1.02)×10 -4 mm 3 / N·m. Compared with the YSZ coating in the comparative example, the microhardness is reduced by 25%, the friction coefficient is reduced by 12%, and the volume wear rate is increased by 135%. The performance requirements of lower coefficient of friction and higher wear rate of the layer.

[0055] Table 4 Plasma sprayed Yb 2 Si 2 o 7 Coating process parameters

[0056] Plasma gas Ar 38slpm Powder carrier gas Ar 2.5 slpm electric cu...

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Abstract

The invention relates to an abradable sealing composite coating material and a preparation method thereof. The abradable sealing composite coating material comprises an internal bonding layer containing Si or SiC and a rare earth silicate abradable sealing surface layer which are sequentially laminated on the surface of a ceramic matrix material, the rare earth silicate is at least one of Y2SiO5, Er2SiO5, Gd2SiO5, Yb2SiO5 and Yb2Si2O7, and the rare earth silicate is at least one of Y2SiO5 and Er2SiO5.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to an abradable sealing coating material that can be used on the surface of a ceramic matrix composite material and a preparation method thereof. Background technique [0002] During the service of an aero-engine, affected by factors such as centrifugal force, thermal expansion, and high-temperature creep, the components of the rotor and the casing will be deformed, which will affect the service performance of the engine. One of the main technologies to solve this problem is to deposit an abradable seal coating on the surface of the component, which can provide a good seal and seal when the gap changes, without damaging the rotor blade. The abradable sealing coating needs to meet the requirements of high temperature resistance, abradability, low friction coefficient and low hardness. At present, the common abradable sealing coating materials mainly include NiAl, AlSi, MCrAlY a...

Claims

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Application Information

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IPC IPC(8): C04B41/89
Inventor 牛亚然秦丹丹钟鑫李红郑学斌
Owner SHANGHAI INST OF CERAMIC CHEM & TECH CHINESE ACAD OF SCI
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