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A platform for research: civil engineering, architecture and urbanism
Ceramic matrix composite elastic sealing element for aero-engine and preparation method
The invention relates to a ceramic matrix composite elastic sealing element for an aero-engine and a preparation method. The sealing element is a revolving body or a long strip, the cross section of the sealing element is omega-shaped, and the sealing element is riveted to the surface of a hot end part of an aero-engine by adopting a ceramic matrix composite rivet. The upper edge of the omega is in close contact with the other sealing surface. The opening size L of the sealing element can be compressed or bounced along with the rising and falling of the environment temperature of the engine and the change of environment conditions such as airflow impact and mechanical vibration of the engine, so that the nested structure of the hot end part or the effective sealing of the junction surfaceis realized. The density of the prepared ceramic matrix composite elastic sealing element is larger than or equal to 2.4g/cm<3>, and the porosity of the material is smaller than or equal to 6%. The strength retention rate is greater than or equal to 95% under the temperature condition of 1650K, and the cracking stress of the sealing material matrix is greater than or equal to 120MPa; when the bearing stress is smaller than or equal to 100MPa, the linear resilience characteristic is kept; and the service life is more than or equal to 5000 hours at the temperature of 1650K.
本发明涉及一种航空发动机用陶瓷基复合材料弹性密封件及制备方法，密封件为回转体或长条状，截面呈Ω形状，采用陶瓷基复合材料铆钉将本密封件铆接到航空发动机热端部件表面。Ω的上沿与另外一个密封面紧密接触。随着发动机环境温度升高和降低，以及发动机气流冲击、机械振动等环境条件变化，本密封件的开口尺寸L会被压缩或弹起，实现热端部件嵌套结构或对结面的有效密封。本发明制备的陶瓷基复合材料弹性密封件密度≥2.4g/cm，材料孔隙率≤6％。1650K温度条件下强度保持率≥95％，密封材料基体开裂应力≥120MPa；承受应力≤100MPa时，保持线性回弹特性；1650K温度下使用寿命≥5000小时。
Ceramic matrix composite elastic sealing element for aero-engine and preparation method
The invention relates to a ceramic matrix composite elastic sealing element for an aero-engine and a preparation method. The sealing element is a revolving body or a long strip, the cross section of the sealing element is omega-shaped, and the sealing element is riveted to the surface of a hot end part of an aero-engine by adopting a ceramic matrix composite rivet. The upper edge of the omega is in close contact with the other sealing surface. The opening size L of the sealing element can be compressed or bounced along with the rising and falling of the environment temperature of the engine and the change of environment conditions such as airflow impact and mechanical vibration of the engine, so that the nested structure of the hot end part or the effective sealing of the junction surfaceis realized. The density of the prepared ceramic matrix composite elastic sealing element is larger than or equal to 2.4g/cm<3>, and the porosity of the material is smaller than or equal to 6%. The strength retention rate is greater than or equal to 95% under the temperature condition of 1650K, and the cracking stress of the sealing material matrix is greater than or equal to 120MPa; when the bearing stress is smaller than or equal to 100MPa, the linear resilience characteristic is kept; and the service life is more than or equal to 5000 hours at the temperature of 1650K.
本发明涉及一种航空发动机用陶瓷基复合材料弹性密封件及制备方法，密封件为回转体或长条状，截面呈Ω形状，采用陶瓷基复合材料铆钉将本密封件铆接到航空发动机热端部件表面。Ω的上沿与另外一个密封面紧密接触。随着发动机环境温度升高和降低，以及发动机气流冲击、机械振动等环境条件变化，本密封件的开口尺寸L会被压缩或弹起，实现热端部件嵌套结构或对结面的有效密封。本发明制备的陶瓷基复合材料弹性密封件密度≥2.4g/cm，材料孔隙率≤6％。1650K温度条件下强度保持率≥95％，密封材料基体开裂应力≥120MPa；承受应力≤100MPa时，保持线性回弹特性；1650K温度下使用寿命≥5000小时。
Ceramic matrix composite elastic sealing element for aero-engine and preparation method
一种航空发动机用陶瓷基复合材料弹性密封件及制备方法
DONG NING (author) / LIU XIAOCHONG (author) / TU JIANYONG (author) / HE JIANGYI (author) / LIU CHIDONG (author) / SUN XIAOKUN (author) / CHENG LAIFEI (author)
2020-08-11
Patent
Electronic Resource
Chinese
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