摘要
对一种蛇形进气道开展了地面工作状态下的抽吸试验研究,结果表明,在该状态下进气道出口截面的总压恢复系数较低、流场畸变较大。为此,本文采用附面层抽吸技术对其进行了地面抽吸状态下的流场控制试验研究。研究结果表明:(1)地面工作状态下,随着出口马赫数的增加,蛇形进气道出口截面的总压恢复系数不断下降,而稳态周向畸变指数、紊流度和综合畸变指数均上升,稳态径向畸变指数变化不大。本研究的蛇形进气道在出口马赫数为0.45时,总压恢复系数为0.90,综合畸变指数为13.85%,总压恢复较低,畸变较大,超出了一般航空发动机的承受范围。(2)与原型方案的地面抽吸试验结果相比,采用附面层抽吸技术后,进气道出口截面的总压恢复系数得到了提高。在出口马赫数为0.45,相对抽吸量为0.043时总压恢复系数提高了2.6%。
Experimental results of the air pumping of a serpentine inlet under ground running show that the total pressure recovery at the exit is low and the distortion at the exit is large. To solve this problem, a boundary layer suction test is carried out. The results prove that： （1） When the Maeh number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient ,turbulence intensity and synthesis distortion increase. When the serpentine inlet is running at the exit Mach number Mar=0. 45, the total pressure recovery coefficient equals 0. 90, and synthesis distortion equals 13.85%. So it can be seen that the distortion of the flow delivered by the inlet is too large to fit the engine. （2） Compared with the experimental results of the archetypal airpumping under ground running, using boundary layer suction technique can increase the total pressure recovery of the inlet. When Mar=0. 45 the relative suction flow rate equals 0. 043, the total pressure recovery increases by 2.6 %
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2007年第1期30-36,共7页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
蛇形进气道
流场控制
地面工作状态
附面层抽吸试验
相对抽吸量
serpentine inlet
flow control
ground running
boundary layer suction（BLS）experiment
relative suction flow rate
