内置中心支板的RBCC变几何二元进气道设计与数值模拟  

Design and numerical simulation of a two-dimensional RBCC variable-geometry inlet with a central strut

作　　者：张浩[1] 李光熙[2] 李江[1] 秦飞[1] 何国强[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072 [2]西安航天动力研究所,西安710100

出　　处：《固体火箭技术》2014年第2期184-191,共8页Journal of Solid Rocket Technology

摘　　要：针对使用RBCC发动机作为第一级动力的两级入轨飞行器，提出了一种内置中心支板的可变几何二元混压式进气道方案。该进气道工作马赫数范围0—7，设计点Ma=5。通过调节唇口外罩角度以及喉部的高度，可改变进气道的几何构型。数值模拟结果表明：（1）该进气道通过采取变几何和吸除措施能够在Ma=2．4下实现自起动，为引射模态向亚燃模态转级提供了必要条件；（2）采用变几何措施可显著拓宽进气道在起动状态下正常工作的马赫数范围；（3）亚燃和超燃模态典型马赫数下，进气道出口各项性能指标适中，可以满足RBCC发动机燃烧室对进口空气参数的要求；（4）通过变几何调节，还可提高进气道的抗反压能力。A variable-geometry RBCC inlet scheme in the form of two-dimensional mixed-compression with a central strut inside was put forward for a TSTO vehicle using RBCC engine as the first stage power.The inlet can operate from Mach number 0 to 7 and the design point Mach number is 5.The geometry configuration of the inlet could be changed through adjusting the angle of cowl lip and the height of throat.The results of numerical simulation indicate ： （ 1 ） the inlet self-starting can be realized at Ma = 2.4 by chan- ging its configuration and bleeding, which provides a necessary condition for the transition from ejector mode to ramjet mode; （2） the change of inlet＇s geometry can greatly widen the Mach number range in which the inlet operate normally at starting mode ; （ 3 ） the performance parameters of the inlet are moderate at typical flight Maeh numbers in ramjet and scramjet mode, which could meet the requirement of RBCC engine combustor for entrance air parameters ; （4） adjusting its geometry configuration can also improve the in- let＇s resistance to back pressure.

关 键 词：RBCC 变几何进气道 宽马赫数 数值模拟 引射模态 亚燃模态 

分 类 号：V423[航空宇航科学与技术—飞行器设计]