三维喷管设计  

Three-dimensional nozzle design

作　　者：覃粒子[1] 王长辉[1] 刘宇[1] 王一白[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2005年第6期499-503,521,共6页Journal of Propulsion Technology

基　　金：国家"八六三"计划(863-2-1-3-1);高等学校博士学科点专项科研基金资助课题

摘　　要：为了简化设计过程并获得满意的设计性能,以圆转方和圆转矩形喷管为例,对已有的三维喷管型面设计方法进行比较和总结,运用数值方法分析了型面转换起始位置和喷管出口高宽比的确定,提出了一套三维型面的直接生成方法,并给出相应的设计准则。经过实际设计和加工的检验,证明了设计方法的工艺可行性。在能够保证三维喷管的制造工艺条件以及冷却通道布置要求下,型面转换的起始位置可以尽量接近喉部;喷管出口截面的宽边不要超过窄边的1.5倍,应尽量接近于方形。In order to simplify the design process and obtain satisfying performances, taking round-to-square and rounato-rectangle nozzles as example, the exiting design methods for complex 3-D nozzles were compared and evaluated. The start position of contour transition and the shape of the exit cross section were analyzed by numerical simulation. A direct method for 3-D contour design was presented and proved to be technically feasible after actual fabrication. Two design criteria were developed： 1 ） the start position should be as close as possible to the throat within the technological level; 2） the exit cross section should be as similar as possible to a square, and if applying rectangular outlet, the size of the broader side should be 1.5 times greater than the dimension of the narrower side.

关 键 词：火箭发动机 三维喷管^+ 型面设计 数值仿真 性能 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]