固体火箭技术2007，Vol.30Issue(1)：21-25,5.
固冲发动机补燃室内强迫对流条件下硼颗粒燃烧速率研究
Study on Burning Rate of Boron Particles in Secondary Chamber of Ducted Rocket under Forced Convection Conditions
胡建新 1夏智勋 1王德全1
作者信息
- 1. 国防科学技术大学航天与材料工程学院,长沙,410073
- 折叠
摘要
Abstract
In the secondary combustion chamber of ducted rocket, there always exists a relative speed between the boron particle and air stream. Hence, it is required to study the effect of forced convection on the burning rate of the boron particle. The analysis made use of the boundary layer and flame-sheet approximations to describe the reacting flow. The governing boundary layer equations were solved by expanding the velocity, temperature and species distributions into series of azimuthal angle. Profiles of these variables at several angular positions along the particle surface were presented. An explicit expression for the burning rate of the boron particle was developed in terms of the Reynolds and mass transfer numbers. The partial differential equations for the two-dimensional boundary layer were simplified into a set of ordinary differential equations by a similarity transformation and then their numerical solution can be easily obtained.关键词
固体火箭冲压发动机/硼颗粒/强迫对流/燃烧速率/燃烧模型Key words
solid ducted rocket engine/boron particle/forced convection/burning rate/combustion model分类
航空航天引用本文复制引用
胡建新,夏智勋,王德全..固冲发动机补燃室内强迫对流条件下硼颗粒燃烧速率研究[J].固体火箭技术,2007,30(1):21-25,5.
