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Ceramic matrix composite elastic sealing element and forming process thereof
The invention belongs to the technical field of sealing of aero-engine hot end structural parts, and particularly relates to a ceramic matrix composite elastic sealing element and a forming process thereof. The problems that a high-temperature elastic sealing element in the prior art is generally poor in temperature resistance, high in self weight and the like are solved. 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; the ceramic matrix composite is a C/SiC ceramic matrix composite or a SiC/SiC ceramic matrix composite; and the cross section of the elastic sealing element body is in a U shape, two opposite and parallel wall faces are connected through an arc face, and a connecting hole is formed in one wall face. By means of the ceramic matrix composite elastic sealing element and the forming process thereof, mechanical sealing betweenceramic matrix composite hot end components in the high-temperature environment of 1200K-1700K can be achieved, and long-service-life and high-reliability sealing connection of precision machines inthe 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，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、自重较高等问题，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U形，相对且平行的两个壁面通过弧面连接，且其中一个壁面上开设有连接孔。本发明可以实现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 sealing of aero-engine hot end structural parts, and particularly relates to a ceramic matrix composite elastic sealing element and a forming process thereof. The problems that a high-temperature elastic sealing element in the prior art is generally poor in temperature resistance, high in self weight and the like are solved. 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; the ceramic matrix composite is a C/SiC ceramic matrix composite or a SiC/SiC ceramic matrix composite; and the cross section of the elastic sealing element body is in a U shape, two opposite and parallel wall faces are connected through an arc face, and a connecting hole is formed in one wall face. By means of the ceramic matrix composite elastic sealing element and the forming process thereof, mechanical sealing betweenceramic matrix composite hot end components in the high-temperature environment of 1200K-1700K can be achieved, and long-service-life and high-reliability sealing connection of precision machines inthe 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，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、自重较高等问题，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U形，相对且平行的两个壁面通过弧面连接，且其中一个壁面上开设有连接孔。本发明可以实现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) / CHEN XU (author) / GUO HONGQIANG (author) / CHENG LAIFEI (author)
2020-07-17
Patent
Electronic Resource
Chinese
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