两型超声速进气道平飞减速时的稳定性  

Stability of two types of supersonic inlets during a level deceleration flight

作　　者：符小刚[1] 李俊浩[1] 杨柳 FU Xiaogang;LI Junhao;YANG Liu(Aero-engine Flight Test Technology Research Institute,Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院发动机所,西安710089

出　　处：《航空动力学报》2024年第1期200-206,共7页Journal of Aerospace Power

摘　　要：通过飞行试验,研究了一种二元斜板式及蚌式超声速进气道在马赫数1.5快收发动机油门平飞减速至马赫数为1.05过程中的畸变及稳定性水平。对比表明:减速过程中二元进气道总压畸变、稳定性裕度均随发动机换算转速的下降减小后保持稳定,而蚌式进气道畸变先上升再下降后保持稳定,稳定性裕度先下降再略微上升后保持稳定。减速过程前半段,蚌式进气道畸变更大,二元进气道稳定性裕度下降更快;减速过程后半段,两型进气道畸变水平接近,稳定性裕度均较低。分析也表明,仅使用流量系数的相对差值计算的进气道稳定裕度反映的进气道流通能力信息比使用总压恢复系数与流量系数之比的相对差值更全面,推荐采用前者作为进气道稳定性裕度评价指标。The distortion and stability level of a 2-D ramp and a bump supersonic inlet during a level deceleration flight from Mach number 1.5 with the throttle lever pulled in rapidly to Mach number 1.05 were investigated through flight test.Comparison showed that during the deceleration flight,both total pressure distortion and stability margin of the 2-D inlet declined with the decrease of the engine's conversion speed and then kept stable,while distortion of the bump inlet rose first and then declined and then kept stable,and the stability margin first decreased and then increased slightly and then kept stable.In the first half of the deceleration process,distortion of the bump inlet was higher and stability margin of the 2-D inlet decreased more rapidly,but in the second half of the process,distortion of the two types of inlet was close and stability margin was low.Also the analysis revealed that the inlet stability margin calculated only with flow coefficient actually reflected more information about the flow capacity of the inlet other than that calculated with total pressure recovery coefficient and flow coefficient,so the former was recommended to be used as the evaluation index of inlet stability margin.

关 键 词：蚌式进气道 进气道喘振 进气畸变 流量系数 稳定性裕度 

分 类 号：V217.1[航空宇航科学与技术—航空宇航推进理论与工程]