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多单元圆转方塞式喷管的性能计算和分析
引用本文:王一白,王长辉,刘宇,覃粒子.多单元圆转方塞式喷管的性能计算和分析[J].航空动力学报,2007,22(4):639-644.
作者姓名:王一白  王长辉  刘宇  覃粒子
作者单位:北京航空航天大学,宇航学院,北京,100083
基金项目:国家高技术研究发展计划(863计划)
摘    要:采用NND差分格式求解三维平均雷诺N-S方程的数值方法,对多单元圆转方塞式喷管的性能进行了计算.首先比较了钟型喷管、二维喷管、圆转方喷管、方形喉部方形出口喷管的流动特点和性能,然后研究了转方位置、转方后型面和出口圆角对圆转方内喷管性能的影响以及圆转方结构型式、内喷管倾角、塞锥型面变化对塞式喷管性能的影响,并且给出了具有较高性能的多单元圆转方塞式喷管设计方案.研究结论对于多单元圆转方塞式喷管的优化设计有一定的参考作用.

关 键 词:航空、航天推进系统  塞式喷管  圆转方内喷管  塞锥型面  性能  多单元  塞式喷管  性能计算  分析  inner  round  analysis  参考作用  优化设计  设计方案  高性能  变化  塞锥型面  倾角  结构型式  影响  喷管性能  圆角  位置  研究
文章编号:1000-8055(2007)04-0639-06
收稿时间:2006/3/28 0:00:00
修稿时间:2006年3月28日

Performance calculations and analysis of multi-module aerospike nozzles with round to rectangle inner nozzles
WANG Yi-bai,WANG Chang-hui,LIU Yu and QIN Li-zi.Performance calculations and analysis of multi-module aerospike nozzles with round to rectangle inner nozzles[J].Journal of Aerospace Power,2007,22(4):639-644.
Authors:WANG Yi-bai  WANG Chang-hui  LIU Yu and QIN Li-zi
Institution:School of Astronautics, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronauticsand Astronautics, Beijing 100083, China
Abstract:Based on an non-oscillatory and non-free parameters dissipation difference (NND) scheme to solve three-dimensional Reynolds averaged Navier-Stokes equations, performance calculations and analysis of multi-module aerospike nozzles with round to rectangle inner nozzles were investigated. Flow characteristics and performance of four inner nozzles including bell nozzle, two-dimensional nozzle, round to square inner nozzle and square throat to square exit nozzle were compared. Then performance of round to rectangle inner nozzles that have different structures such as contour changing points, contours after changing points and exit arc radiuses were discussed. The effects of different structures of inner nozzles, different nozzle obliquities and different plug contours on the multi-module linear aerospike nozzles were also presented. And a design scheme of the optimized aerospike nozzle was given. Conclusions can provide some reference for studying design of the multi-module linear aerospike nozzles with round to rectangle inner nozzles.
Keywords:aerospace propulsion system  aerospike nozzle  round to rectangle inner nozzle  plug contour  performance
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