转子叶顶间隙值及改型对压气机性能影响的数值模拟
Numerical Simulation on the Influence of Tip Clearance Value and Shape Modification on Compressor Performance
李志鹏 1张国臣 1张成烽 1徐志晖 1曹志远2
作者信息
- 1. 沈阳航空航天大学 航空发动机学院,沈阳 110136
- 2. 西北工业大学 动力与能源学院,西安 710129
- 折叠
摘要
为了分析转子叶顶间隙值和改型对压气机性能的影响,以典型轴流跨声速压气机NASA stage 35为对象,对不同叶顶间隙值的压气机进行数值模拟.结果表明:叶顶间隙增大并且泄漏流强度提高,会导致脱体激波位置前移,转子吸力面激波作用位置后移,前缘溢流现象减弱,叶尖泄漏涡与激波作用增强,间隙区域涡量增加,靠近前缘的涡核向下游移动,但附面层与激波之间的作用减弱;不同叶顶间隙值的压气机失速机制不同,在小间隙下压气机失速是由叶尖泄漏涡和转子吸力面附面层分离共同作用引起的,在大间隙下压气机失速是由叶尖泄漏涡引起的;在研究的变化范围内,叶顶间隙值为0.50τ时,压气机性能最好,峰值效率和稳定裕度分别提高了0.16%和2.39%;将最优间隙改型成平行扩张式和正弦波间隙后,压气机性能提高,脱体激波后移,叶尖泄漏涡与激波作用程度减弱,转子吸力面附面层分离减弱,改型间隙能够减少叶片制作材料,减轻发动机质量.
Abstract
To analyze the effect of rotor tip clearance values and tip clearance shape modifications on compressor performance,numerical simulations were conducted on a typical axial flow transonic compressor NASA Stage 35 with different tip clearance values.The results show that with the increase of tip clearance and leakage flow intensity,the position of the detached shock wave moves forward,the position of the shock wave acting on the suction surface of the rotor blade moves backward,leading edge spillage phenomenon is weakened,the interaction between the tip leakage vortex and the shock wave is strengthened,the vorticity in the tip clearance area increases,and the vortex core near the leading edge moves downstream,but the interaction between the boundary layer and the shock wave is weakened;The stall mechanisms of compressor with different tip clearance values were different,the stall of the compressor with small tip clearance is caused by the joint action of the of the tip leakage vortex and the rotor blade suction surface boundary layer separation,while the stall of the compressor with large tip clearance is caused by tip leakage vortex;Within the range investigated,when the tip clearance is 0.50τ,the compressor has the best performance,with peak efficiency and stability margin increased by 0.16%and 2.39%,respectively;After the optimized uniform tip clearance is modified to parallel to divergent tip clearance and sinusoidal tip clearance,the compressor performance is improved,the detached shock wave moves backward,the interaction between tip leakage vortex and shock wave is weakened,and the boundary layer separation on the rotor blade suction surface is weakened,and the tip clearance shape modification can reduce blade mate-rial usage and engine mass.
关键词
叶尖泄漏流/激波/前缘溢流/附面层分离/叶顶间隙改型/转子/压气机/航空发动机Key words
tip leakage flow/shock wave/leading edge spillage flow/boundary layer separation/tip clearance shape modification/rotor/compressor/aeroengine引用本文复制引用
出版年
2024
NETL
NSTL
万方数据