摘要
为探究缝式机匣处理对对转压气机最先失速级的影响规律,以双级对转压气机为研究对象,采用数值模拟的方法,开展了缝式机匣处理对对转压气机最先失速级的影响研究。研究表明:缝式机匣处理下该对转压气机的失速初始扰动类型仍为突尖型失速,机匣处理前移压气机的最先失速级由转子R2转换为转子R1,而机匣处理后移未改变该压气机的失速级。机匣处理前移抑制了转子R2前缘溢流的发生,降低了叶片通道内的非定常脉动强度,而转子R1在近失速工况下叶片前缘溢流加剧,主流和泄漏流的交界面被推出叶片通道,同时叶片通道内的非定常脉动强度增大,最终使得转子R1首先进入失速状态;机匣处理向转子R2下游移动,难以抑制前缘溢流的发生,虽然此时转子R1也出现了前缘溢流现象,但转子R2前缘溢流更剧烈,主流和泄漏流交界面的位置更远离叶片前缘,更容易使压气机发生失速。
In order to explore the influence of slot casing treatment on the first stall stage of counter-rotating compressor,a two-stage counter-rotating compressor was taken as the research object.The influence of slot casing treatment on the first stall stage of the counter-rotating compressor was studied by numerical simulation method.The results showed that the slot casing treatment did not change the initial stall disturbance type of the counter-rotating compressor,which was still a spike stall.The first stall stage of the compressor was converted from rotor R2 to rotor R1 by the forward movement of the casing treatment,while the backward movement of the casing treatment did not change the stall stage of the compressor.After casing treatment,the leading edge spillage of the rotor R2 was inhibited,and the unsteady fluctuation intensity in the blade passage was reduced.However,the leading edge spillage of the rotor R1 was intensified under the near-stall condition.The interface between the mainstream and the leakage flow was pushed out of the blade passage.At the same time,the unsteady oscillation intensity in the blade passage was increased,which finally made the rotor R1 first enter the stall state.It was difficult to suppress the occurrence of leading edge spillage when the casing treatment was processed to move downstream of rotor R2.Although the leading edge spillage phenomenon also occurred at rotor R1 at this time,the leading edge spillage of rotor R2 was more intensified,and the position of the interface of the mainstream and leakage flow was further away from the leading edge of the blade,making it easier for the compressor to stall.
作者
王磊
高丽敏
茅晓晨
郭彦超
WANG Lei;GAO Limin;MAO Xiaochen;GUO Yanchao(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;The National Key Laboratory of Aerodynamic Design and Research,Northwestern Polytechnical University,Xi’an 710072,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2024年第6期259-274,共16页
Journal of Aerospace Power
基金
国家科技重大专项(J2019-Ⅱ-0016-0037)
国家自然科学基金重大专项(51790512)
国家自然科学基金(52106057)。
