公开(公告)号：US06860099B1

公开(公告)日：2005-03-01

申请号：US10263297

申请日：2003-01-09

申请人： George D. Xenofos ,  W. Neill Myers ,  Huu Trinh ,  R. Scott Michaels

发明人： George D. Xenofos ,  W. Neill Myers ,  Huu Trinh ,  R. Scott Michaels

IPC分类号： F02K9/62 ,  F02K9/97 ,  F02K9/00 ,  F02K9/42 ,  F02K9/72

CPC分类号： F02K9/62 ,  F02K9/972

摘要： An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermined spaced apart distance from the chamber wall of the combustion chamber at an impingement track. By providing the fuel at a steeper angle relative to the chamber walls than the oxidizer, the fuel can be utilized to provide a fuel rich zone near the chamber walls to assist in cooling the chamber walls during operation.

摘要翻译： 与火箭推进器一起使用的喷射器具有与多个氧化剂口分离的多个燃料口。 氧化剂和燃料端口配对在一起，沿着具有径向和切向部件的路径引导它们各自的流体，使得两个流体在冲击轨道处以与燃烧室的室壁预定间隔开的距离冲击。 通过以比氧化器相对于室壁更陡的角度提供燃料，燃料可以用于在室壁附近提供富燃区，以在操作期间帮助冷却室壁。