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Connecting piece of silicon carbide composite material/high-temperature alloy and connecting method and application thereof
The invention belongs to the technical field of ceramic and alloy connection, and discloses a silicon carbide composite material/high-temperature alloy connecting piece and a connecting method and application thereof. According to the method, high-entropy alloy powder serves as a connecting material, the connecting material is placed on the connecting surface of the silicon carbide composite material and the high-temperature alloy to prepare a prefabricated connecting piece, the prefabricated connecting piece is heated to 1300-1600 DEG C in an inert atmosphere or a vacuum environment, the pressure is 1-10 MPa, and the connecting piece of the silicon carbide composite material and the high-temperature alloy is obtained. The thickness of the connecting layer in the connecting piece is 5-20 microns, the shear strength of the connecting layer at the room temperature is 150-200 MPa, and the shear strength of the connecting layer at the temperature of 1200-1500 DEG C is 70-150 MPa. The connecting piece has high temperature resistance, oxidation resistance and corrosion resistance, and can be used in the field of connection of turbine blades, aero-engines or rocket propulsion chambers.
本发明属于陶瓷与合金连接技术领域，公开了一种碳化硅复合材料/高温合金的连接件及其连接方法与应用。该方法是以高熵合金粉体作为连接材料，将连接材料置于碳化硅复合材料和高温合金的连接表面制得预制连接件，将预制连接件在惰性气氛或真空环境中升温至1300～1600℃、压力为1～10MPa下进行连接，得到碳化硅复合材料和高温合金的连接件。该连接件中连接层的厚度为5～20μm，在室温下的剪切强度为150～200MPa，在1200～1500℃下的剪切强度为70～150MPa。该连接件具有耐高温、抗氧化和耐腐蚀，可用于涡轮叶片、航空发动机或火箭推进室连接领域。
Connecting piece of silicon carbide composite material/high-temperature alloy and connecting method and application thereof
The invention belongs to the technical field of ceramic and alloy connection, and discloses a silicon carbide composite material/high-temperature alloy connecting piece and a connecting method and application thereof. According to the method, high-entropy alloy powder serves as a connecting material, the connecting material is placed on the connecting surface of the silicon carbide composite material and the high-temperature alloy to prepare a prefabricated connecting piece, the prefabricated connecting piece is heated to 1300-1600 DEG C in an inert atmosphere or a vacuum environment, the pressure is 1-10 MPa, and the connecting piece of the silicon carbide composite material and the high-temperature alloy is obtained. The thickness of the connecting layer in the connecting piece is 5-20 microns, the shear strength of the connecting layer at the room temperature is 150-200 MPa, and the shear strength of the connecting layer at the temperature of 1200-1500 DEG C is 70-150 MPa. The connecting piece has high temperature resistance, oxidation resistance and corrosion resistance, and can be used in the field of connection of turbine blades, aero-engines or rocket propulsion chambers.
本发明属于陶瓷与合金连接技术领域，公开了一种碳化硅复合材料/高温合金的连接件及其连接方法与应用。该方法是以高熵合金粉体作为连接材料，将连接材料置于碳化硅复合材料和高温合金的连接表面制得预制连接件，将预制连接件在惰性气氛或真空环境中升温至1300～1600℃、压力为1～10MPa下进行连接，得到碳化硅复合材料和高温合金的连接件。该连接件中连接层的厚度为5～20μm，在室温下的剪切强度为150～200MPa，在1200～1500℃下的剪切强度为70～150MPa。该连接件具有耐高温、抗氧化和耐腐蚀，可用于涡轮叶片、航空发动机或火箭推进室连接领域。
Connecting piece of silicon carbide composite material/high-temperature alloy and connecting method and application thereof
一种碳化硅复合材料/高温合金的连接件及其连接方法与应用
SU LINGFENG (author) / GUO WEIMING (author) / HE SHENGJIN (author) / ZHAN CHUANGTIAN (author) / CHEN XIUBING (author) / LIN HUATAI (author)
2023-05-23
Patent
Electronic Resource
Chinese
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