公开(公告)号：US06244041B1

公开(公告)日：2001-06-12

申请号：US09394259

申请日：1999-09-10

申请人： Alexandr Alexandrovich Vasin ,  Stanislav Dmitrievich Kamensky ,  Boris Ivanovich Katorgin ,  Alexei Ivanovich Kolesnikov ,  Viktor Petrovich Nosov ,  Anatoly Ivanovich Stavrulov ,  Vladimir Vladimirovich Fedorov ,  Vladimir Konstantinovich Chvanov

发明人： Alexandr Alexandrovich Vasin ,  Stanislav Dmitrievich Kamensky ,  Boris Ivanovich Katorgin ,  Alexei Ivanovich Kolesnikov ,  Viktor Petrovich Nosov ,  Anatoly Ivanovich Stavrulov ,  Vladimir Vladimirovich Fedorov ,  Vladimir Konstantinovich Chvanov

IPC分类号： F02K995

CPC分类号： F02K9/62 ,  F02K9/52

摘要： The invention relates to rocket engine manufacturing, and may also be used in aircraft engine manufacturing. A chamber comprises a casing, ignition means and a mixing head. The mixing head consists of an internal injector face, a middle bottom, an external bottom. Bipropellant injectors are fixed in the internal injector face and the middle bottom. A portion of the bipropellant injectors are mounted projecting from the internal injector face, while another portion are recessed in the internal injector face. The ignition means are made from jet injectors mounted in a structural casing behind the internal injector face. Axes of diverging ports of jet injectors are positioned at an acute angle to an outlet from the structural casing and deflected in a circle in a lateral plane from the longitudinal axis of the structural casing in an identical direction. The chamber casing comprises a combustion chamber and a nozzle, made from an external structural envelope and an internal fire wall. A regenerative cooling passage is positioned between the external structural envelope and the internal fire wall. A ring-like slot of a gas-screen belt is made in the internal fire wall before the nozzle throat. The regenerative cooling passage of the chamber is made with a branched inlet. One of its branches communicates with the space of the chamber regenerative cooling passage between the nozzle throat and its scarf, a second branch—with the space of the chamber regenerative cooling passage before the nozzle throat, and a third—with the space of the chamber regenerative cooling passage before the ring-like slot of the gas-screen belt.

摘要翻译： 本发明涉及火箭发动机制造，也可用于飞机发动机制造。 腔室包括壳体，点火装置和混合头。 混合头由内部注射器面，中间底部，外部底部组成。 双通道注射器固定在内部注射器面和中间底部。 双组元推进剂注射器的一部分从内部注射器表面安装突出，而另一部分凹入内部注射器表面。 点火装置由安装在内部喷射器面后面的结构壳体中的喷射喷射器制成。 喷射喷射器的发散端口的轴线与结构壳体的出口成锐角地定位，并且沿着相同方向从结构壳体的纵向轴线在横向平面中以一个圆形的方式偏转。 室外壳包括由外部结构外壳和内部防火墙制成的燃烧室和喷嘴。 再生冷却通道位于外部结构外壳和内部防火墙之间。 气体屏蔽带的环状槽在喷嘴喉部之前的内部防火墙中制成。 室的再生冷却通道由分支入口制成。 其一个分支与喷嘴喉部和其围巾之间的腔室再生冷却通道的空间相通，第二分支与腔室再生冷却通道的空间在喷嘴喉部之间，第三分支与腔室的空间 气体屏蔽带环形槽前的再生冷却通道。