端壁SJA对压气机叶栅角区分离影响
Effect of endwall SJA on the corner separation of compressor cascade
郑维新 1曾聪 2陈绍文2
作者信息
- 1. 中国联合重型燃气轮机技术有限公司,北京 100016
- 2. 哈尔滨工业大学能源科学与工程学院,哈尔滨 150001
- 折叠
摘要
针对某型轴流压气机叶栅角区存在流动分离的问题,利用扫频射流激励器(SJA)主动流动控制技术,采用非定常数值计算方法对端壁SJA控制压气机平面叶栅角区分离的影响机理进行研究,分析和讨论了 SJA位置布置、射流压比设定、射流偏角设定的影响规律和流场特性.研究结果表明:端壁SJA主要影响端壁和叶片表面附面层的发展和迁移,通过抑制集中脱落涡的生成与发展,以达到抑制角区分离、减小角区流动损失的目的;当SJA布置在轴向位置xSJA/b=85％处、靠近吸力面时,降低流动损失的效果最佳;当SJA射流压比大约为1.01时,利用仅占主流0.03％的射流流量就可使得总压损失系数减小13.4％.此外,通过合理设计SJA射流偏角可有效改善端壁SJA存在的"扫掠盲点"问题,使得SJA控制效果得到进一步提高.
Abstract
To address the issue of flow separation in the corner region of an axial flow compressor,an active flow control technique called sweeping jet actuator(SJA)was employed.Unsteady numerical simulations were conducted to investigate the impact of endwall SJA jets on mitigating flow separation in the compressor's corner region.The effects of SJA placement,jet pressure ratio,jet skew angle,and their influence on flow characteristics were analyzed and discussed.The results indicated that the endwall SJA jets primarily affected the development and migration of the boundary layer on the endwall and blade surfaces.By suppressing the generation and development of concentrated shedding vortices,the corner separation was suppressed and the flow loss in the corner was reduced.Moreover,the optimal configuration for loss reduction was achieved when the SJA was positioned at approximatelyxSJA/b=85％along the axial direction and close to the suction surface.When the jet pressure ratio for the SJA was approximately 1.01,with the help of only 0.03％of the mainstream flow for the jet flow,a relative reduction of 13.4％in total pressure loss coefficient can be achieved.Furthermore,by appropriately designing the jet skew angle,the issue of"sweeping blind spots"in the endwall SJA can be effectively mitigated,leading to further enhancement of the SJA controlling effectiveness.
关键词
压气机叶栅/角区分离/扫频射流激励器(SJA)/非定常流动控制/射流位置/总压损失Key words
compressor cascade/corner separation/sweeping jet actuators(SJA)/unsteady fow control/injection position/total pressure loss引用本文复制引用
基金项目
航空科学基金(2023M039077001)
国家自然科学基金(U2233207)
出版年
2024
NETL
NSTL
万方数据