摘要
为了探索不同轴向偏转角处理机匣对压气机稳定裕度的影响,以一个亚声压气机为平台通过实验与数值仿真方法探索了8 130r/min设计转速下3种与轴向成不同角度的处理机匣对该压气机稳定性的作用.详细的分析了各流量工况下不同处理机匣叶顶的流动结构、叶顶载荷分布、处理机匣缝(或槽)内的流动、周向平均后叶顶的损失分布和缝内喷射气流的轴向动量.研究发现:随着缝(或槽)与轴向所成夹角的增大,整个流量范围内,处理机匣的扩稳能力先增强后减弱;大流量工况下,转子叶顶载荷增加,转子的等熵效率降低.
Experimental and numerical simulations were performed on a subsonic compressor to investigate the stabilizing mechanisms of casing treatment with different axial angles at rotation speed of 8130r/min.Flow structures and static pressure distribution of rotor tip,flow structure in the slots（or grooves）,loss distribution in rotor tip,axial momentum of the injected flow at different mass flows were studied.Results confirmed that the capability of the casing treatment of extending the compressor stall margin first increased and then decreased within the whole mass flow range,the loading of rotor tip increased and the isentropic efficiency decreased under large mass flow with the increasing axial angle of the casing treatment.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2015年第8期1900-1908,共9页
Journal of Aerospace Power
基金
国家自然科学基金重点项目(51236006)
关键词
处理机匣
轴向偏转角
轴流压气机
流场
机理
casing treatment
axial angle
axial flow compressor
flow field
mechanism
