公开(公告)号：US20160177875A1

公开(公告)日：2016-06-23

申请号：US14905923

申请日：2014-07-23

Applicant: ASTRIUM SAS

Inventor： Jean-Philippe DUTHEIL

IPC: F02K9/86 ,  F02K1/80 ,  F02K9/97

CPC classification number: F02K9/86 ,  F02K1/805 ,  F02K9/90 ,  F02K9/97 ,  F02K9/978 ,  F05D2220/80 ,  F05D2240/128 ,  F05D2240/55

Abstract: The invention relates to a combustion gas discharge nozzle for a rocket engine including a stationary part and a moving part, extending the stationary part, the moving part, made using flaps, being positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle including a sealing device between the fixed part and the moving part in the form of a flexible membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connecting the end of the stationary part to a border of the flaps or petals forming the moving part, the flexible membrane forming an annular tubing, the device being provided with means for injecting gas at the flexible membrane between the stationary part and the moving part extending the nozzle.

Abstract translation: 本发明涉及一种用于火箭发动机的燃烧气体排放喷嘴，其包括固定部分和活动部分，使固定部分延伸，使用襟翼制成的移动部分位于固定部分的下游并形成喷嘴的延伸部分， 所述喷嘴包括位于所述固定部分和所述可移动部分之间的密封装置，所述密封装置以柔性膜的形式承受所述喷嘴出口处的燃烧气体的局部温度，并将所述固定部分的端部连接到所述翼片或瓣部的边缘 移动部分，柔性膜形成环形管，该装置设置有用于在静止部分和延伸喷嘴的移动部分之间的柔性膜处注入气体的装置。