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Ceramic matrix composite elastic sealing element and forming process thereof
The invention belongs to the technical field of aero-engine hot end structural part sealing, and relates to a ceramic matrix composite elastic sealing element and a forming process thereof. The ceramic matrix composite elastic sealing element comprises a long-strip-shaped or annular elastic sealing element body, and the elastic sealing element body is made of a ceramic matrix composite material; the ceramic-based composite material is a C/SiC ceramic-based composite material or a SiC/SiC ceramic matrix composite material; the cross section of the elastic sealing element body is in an omega shape, the elastic sealing element body comprises an arc-shaped wall surface and two plane wall surfaces, the two plane wall surfaces are connected to the arc-shaped wall surface through cambered surfaces in a smooth transition mode, and connecting holes are formed in the two plane wall surfaces. Mechanical sealing between ceramic matrix composite hot end components under a high-temperature environment of 1200-1700K can be achieved, and long-service life and high-reliability sealing connection of precision machinery in the aerospace field is achieved.
本发明属于航空发动机热端结构件密封技术领域，涉及一种陶瓷基复合材料弹性密封件及其成型工艺，包括长条状或环形的弹性密封件本体，弹性密封件本体的材质为陶瓷基复合材料；陶瓷基复合材料为C/SiC陶瓷基复合材料或SiC/SiC陶瓷基复合材料；弹性密封件本体的横截面形状为Ω形，包括弧形壁面与两个平面壁面，两个平面壁面与弧形壁面通过弧面圆滑过渡连接，在两个平面壁面上开设有连接孔。可以实现1200K～1700K高温环境下陶瓷基复合材料热端部件之间的机械密封，满足航空航天领域精密机械的长寿命、高可靠密封连接。
Ceramic matrix composite elastic sealing element and forming process thereof
The invention belongs to the technical field of aero-engine hot end structural part sealing, and relates to a ceramic matrix composite elastic sealing element and a forming process thereof. The ceramic matrix composite elastic sealing element comprises a long-strip-shaped or annular elastic sealing element body, and the elastic sealing element body is made of a ceramic matrix composite material; the ceramic-based composite material is a C/SiC ceramic-based composite material or a SiC/SiC ceramic matrix composite material; the cross section of the elastic sealing element body is in an omega shape, the elastic sealing element body comprises an arc-shaped wall surface and two plane wall surfaces, the two plane wall surfaces are connected to the arc-shaped wall surface through cambered surfaces in a smooth transition mode, and connecting holes are formed in the two plane wall surfaces. Mechanical sealing between ceramic matrix composite hot end components under a high-temperature environment of 1200-1700K can be achieved, and long-service life and high-reliability sealing connection of precision machinery in the aerospace field is achieved.
本发明属于航空发动机热端结构件密封技术领域，涉及一种陶瓷基复合材料弹性密封件及其成型工艺，包括长条状或环形的弹性密封件本体，弹性密封件本体的材质为陶瓷基复合材料；陶瓷基复合材料为C/SiC陶瓷基复合材料或SiC/SiC陶瓷基复合材料；弹性密封件本体的横截面形状为Ω形，包括弧形壁面与两个平面壁面，两个平面壁面与弧形壁面通过弧面圆滑过渡连接，在两个平面壁面上开设有连接孔。可以实现1200K～1700K高温环境下陶瓷基复合材料热端部件之间的机械密封，满足航空航天领域精密机械的长寿命、高可靠密封连接。
Ceramic matrix composite elastic sealing element and forming process thereof
一种陶瓷基复合材料弹性密封件及其成型工艺
TU JIANYONG (author) / WANG JIAMIN (author) / HE JIANGYI (author) / XU JIANFENG (author) / CHENG LAIFEI (author)
2020-06-26
Patent
Electronic Resource
Chinese
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