摘要
用实验的方法获取了高位垂直进气径向出流的静盘表面压力分布和转静腔内的旋流系数.实验结果表明:在低于0.6倍半径的范围内,沿半径增大方向静压随之增大;在射流孔处压力降至最低,而后又突然升高并逐步趋于平稳;静盘表面压力随着流量的增加而增加,随着旋转雷诺数的增加而降低;在旋转雷诺数小于等于2.6×106、流量系数小于等于4.50×104的范围内两盘间可以形成稳定的旋转核心.此外,在实验范围内,流量系数和旋转雷诺数对旋流系数值的影响较小.
The pressure distribution of a static disk and relative rotational speed in the rotor-stator cavity were experimentally investigated. Results show that the static pressure increases with the radial accretion within 0.6 radius range, and the lowest value of pressure appears at the ejection hole and then increases sharply to the moderate stage along the radial direction. The pressure upon the static disk increases with the augmentation of flow rate, and decreases with the increase of rotational Reynolds number. A steady rotational core can be formed when the value of rotational Reynolds number is less than 2.6 ×10^6 and the mass flow rate less than 4.5 Reynolds number have 0 ×10^4. In addi little influences tion, the variations of mass flow rate and rotational on the relative rotational speed.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第1期53-57,共5页
Journal of Aerospace Power
关键词
转静系
高位进气
压力分布
旋流系数
rotor-stator system
high-positioned inflow
pressure distribution
relative rotational speed
