不同抽吸孔布局的进气道抗反压能力机理分析  

Mechanism Analysis of Resistance Back Pressure of Inlet with Different Suction Slots

作　　者：王亮[1] WANG Liang(Shenhua Group Zhungeer Energy CO., Ltd., Inner Mongolia 017000, China)

机构地区：[1]神华准格尔能源有限责任公司矸石发电公司,内蒙古鄂尔多斯017000

出　　处：《节能技术》2022年第1期30-35,共6页Energy Conservation Technology

基　　金：运动激波稳定在超声速进气道喉道的设想及原理探讨(51976182)。

摘　　要：基于雷诺平均数值计算方法,针对进出口面积相等的两种布局抽吸孔设计,分析了超声速进气道在不同反压比的进气道流场特性,尤其是不同压比条件下抽吸孔内的流场变化情况,获得了进气道从起动到不起动的抽吸孔内的流场变化及壁面压力分布。结果表明:随着反压比的增大,在进气道喉部区域形成较强的密度梯度;模型-1的正激波传播到进气道唇口区域,正激波使得马赫数降低到0.68,抽吸孔进口壁面出现分离现象,分离引起的再附激波使得马赫数增加到1.37,进气道是起动状态;而模型-2在压比等于15.1时,抽吸孔左侧壁面出现较大的分离包,进气道唇口出现溢流,进气道出现不起动现象。In order to deeply analyze the flow field characteristics of supersonic inlet start/unstart under different back pressure ration by Navier-Stokes simulation,the flow field characteristics and wall pressure distribution were obtained of inlet start to unstart process.The results show that the strong density gradient is formed in the inlet throat area with the increase of the back pressure ratio;The normal shock wave is propagated to the lip area of the inlet of Model-1 when the back pressure ratio is 15.1.The separation vortex of suction slot is formed,The reattachment shock wave caused by separation increases the Mach number to 1.37,the inlet is in the starting state;But inlet of model-2 is unstart due to overflow in the inlet lip.

关 键 词：反压比 进气道不起动 分离涡 壁面压力 抽吸孔 密度梯度 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]