公开(公告)号：US07137254B1

公开(公告)日：2006-11-21

申请号：US10312914

申请日：2000-07-05

申请人： Gorokhov Victor Dmitrievich ,  Lobov Sergey Dmitrievich ,  Chernichenko Vladimir Victorovich

发明人： Gorokhov Victor Dmitrievich ,  Lobov Sergey Dmitrievich ,  Chernichenko Vladimir Victorovich

IPC分类号： F02C1/00 ,  B05B7/06

CPC分类号： F23D11/106 ,  F02K9/52 ,  F23D11/12

摘要： The invention relates to power plants, in particular to devices for mixing and atomizing propellant components, and may be used for development injection elements and injector heads of liquid-fuel rocket engines (LRE).The task of the invention is to increase the propellant component combustion efficiency via the increase of propellant component contact area.This task is solved by provision of radial grooves 3 in the outlet portion of a hollow tip 1 of the coaxial-jet injection element, the said hollow tip connecting the cavity of one propellant with the combustion zone, a sleeve 5 surrounding the said tip providing an annular gap 4 connecting the cavity of another propellant with the combustion zone. The sleeve inner surface outlet portion is equidistant relatively to the tip grooves outer surface, and the outlet cross-section area between the sleeve equidistant surface and the tip grooves is Fr=(0,6-2,2)Fo, where Fo is the groove cross-section area at the tip outlet, 2 dependent claims, 3 Figures.

摘要翻译： 本发明涉及发电厂，特别涉及用于混合和雾化推进剂组分的装置，并且可用于液体燃料火箭发动机（LRE）的开发喷射元件和喷射头。 本发明的任务是通过增加推进剂组分接触面积来提高推进剂组分的燃烧效率。 该任务通过在同轴喷射注入元件的中空尖端1的出口部分中设置径向凹槽3来解决，所述中空尖端将一个推进剂的空腔与燃烧区连接，围绕所述尖端的套筒5提供 连接另一推进剂的空腔与燃烧区的环形间隙4。 套筒内表面出口部分相对于尖端沟槽外表面等距，并且套筒等距表面和尖端沟槽之间的出口横截面面积为（0.6-2， 2）F o o o，其中F o o o是尖端出口处的槽横截面积，2个从属权利要求，3图。