摘要
简化发动机冷气预旋系统,对特定结构的两种冷气进口预旋角度的转静盘腔系统,开展冷气温降和流阻特性的试验研究.建立预旋系统旋转试验台,在旋转部件表面采用微型压力传感器测量压力,经过标定校正后获得预旋系统的出口总压.获得了旋转雷诺数、无量纲质量流量对预旋系统温降和流阻特性的影响规律.研究结果表明:对两种角度的预旋喷嘴,无量纲温降随无量纲质量流量的增大先增大后减小,随旋转雷诺数的增大而减小;无量纲压降随无量纲质量流量的增大而增大,随旋转雷诺数的增大而减小.
The effect of rotational Reynolds number and non-dimensional mass flow rate on the drop of cooling air temperature and flow loss of a simplified aero-engine pre-swirl system were investigated experimentally for two pre-swirl angles.A test rig was set up.Micro pressure transducers for measuring pressure of rotating disk surface were fixed on the disk,and the relative total pressure of the outlet of the pre-swirl system was obtained after calibrations.The rules of influences on drop of cooling air temperature and flow losses performance of pre-swirl cooling system were achieved.This shows that the cooling air temperature rises and then goes down with the increase of non-dimensional mass flow rate in the range of this study and these two pre-swirl angles,and decreases with the rising rotational Reynolds number;non-dimensional flow loss increases with the enlargement of non-dimensional mass flow rate,and decreases with the increment of the rotational Reynolds number.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第12期2698-2703,共6页
Journal of Aerospace Power
关键词
冷气系统
转静盘腔
预旋
温降
流阻
cooling system
rotor-stator cavity
pre-swirl
drop of cooling air temperature
flow losses
