公开(公告)号：US20160312744A1

公开(公告)日：2016-10-27

申请号：US15029920

申请日：2014-10-10

Applicant: SNECMA

Inventor： Robert GAZAVE

IPC: F02K9/64

CPC classification number: F02K9/64 ,  F05D2230/60 ,  F05D2250/72 ,  F05D2300/603

Abstract: A rocket propulsion chamber and a method of fabricating such a propulsion chamber are provided. The propulsion chamber includes a combustion chamber, a wall of the combustion chamber having a cooling circuit wherein a first propellant flows. A thermostructural composite material shell is placed against the outside of the combustion chamber and including a diverging nozzle extending beyond the bottom end of the combustion chamber, wherein a fraction of the thermostructural composite material shell is covered in a radially strong outer reinforcing shell for containing deformation of the combustion chamber and thermostructural composite material shell, the thermostructural composite material shell and the outer reinforcing shell forming a unitary assembly.

Abstract translation: 提供火箭推进室和制造这种推进室的方法。 推进室包括燃烧室，燃烧室的壁具有第一推进剂流动的冷却回路。 将热结构复合材料壳放置在燃烧室的外部，并且包括延伸超过燃烧室底端的发散喷嘴，其中一部分热结构复合材料壳体被覆盖在径向强的外部增强壳体中，用于容纳变形 的燃烧室和热结构复合材料外壳，热结构复合材料外壳和外加强外壳形成一体式组件。