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Ceramic-based composite material elastic sealing member and forming process thereof
The invention belongs to the technical field of aero-engine hot-end structural member sealing, particularly relates to a ceramic-based composite material elastic sealing member and a forming process thereof, and aims to overcome the defects of poor temperature resistance, high dead weight and the like generally existing in the current conventional high-temperature elastic sealing member. The ceramic-based composite material elastic sealing member comprises a long-striped or annular elastic sealing member body, the material of the long-striped or annular elastic sealing member body is a ceramic-based composite material; the ceramic-based composite material is C/SiC ceramic-based composite material or SiC/SiC ceramic-based composite material; a cross section shape of the elastic sealing member body is N-shaped, two adjacent wall surfaces are in smooth transition connection through an arc surface; and a connecting hole is formed in one of the two opposite and parallel wall faces. Mechanical sealing between hot end components of the ceramic-based composite material under the high-temperature environment of 1,200 K to 1,700 K can be achieved, and long-service-life and high-reliability sealing connection of precision machinery in the aerospace field can be met.
本发明属于航空发动机热端结构件密封技术领域，具体涉及一种陶瓷基复合材料弹性密封件及其成型工艺，解决现有高温弹性密封件普遍存在耐温性能不佳、自重较高等缺陷，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N形，相邻两个壁面通过弧面圆滑过渡连接；在相对且平行的两个壁面的其中一个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-based composite material elastic sealing member and forming process thereof
The invention belongs to the technical field of aero-engine hot-end structural member sealing, particularly relates to a ceramic-based composite material elastic sealing member and a forming process thereof, and aims to overcome the defects of poor temperature resistance, high dead weight and the like generally existing in the current conventional high-temperature elastic sealing member. The ceramic-based composite material elastic sealing member comprises a long-striped or annular elastic sealing member body, the material of the long-striped or annular elastic sealing member body is a ceramic-based composite material; the ceramic-based composite material is C/SiC ceramic-based composite material or SiC/SiC ceramic-based composite material; a cross section shape of the elastic sealing member body is N-shaped, two adjacent wall surfaces are in smooth transition connection through an arc surface; and a connecting hole is formed in one of the two opposite and parallel wall faces. Mechanical sealing between hot end components of the ceramic-based composite material under the high-temperature environment of 1,200 K to 1,700 K can be achieved, and long-service-life and high-reliability sealing connection of precision machinery in the aerospace field can be met.
本发明属于航空发动机热端结构件密封技术领域，具体涉及一种陶瓷基复合材料弹性密封件及其成型工艺，解决现有高温弹性密封件普遍存在耐温性能不佳、自重较高等缺陷，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N形，相邻两个壁面通过弧面圆滑过渡连接；在相对且平行的两个壁面的其中一个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-based composite material elastic sealing member 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) / LIU MENGZHU (author) / WANG WENHONG (author) / CHENG LAIFEI (author)
2020-07-17
Patent
Electronic Resource
Chinese
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