转子叶尖开缝对跨声速轴流压气机性能及流场结构影响机理研究

Mechanism of Effects of Rotor Blade Tip Jet Slot on Performance and Flow Structure of Transonic Axial Compressor

关键词:  转子开缝  压气机  流场  流动控制  总压比  稳定裕度

Key words:  Rotor slot  Compressor  Flow field  Flow control  Total pressure ratio  Stability margin

摘要:

为了研究转子叶尖开缝对跨声速轴流压气机性能和流场结构的影响机理，设计了一种渐缩式射流缝，提出在转子叶尖不同相对位置开缝的流动控制方案，通过数值计算的方法对各开缝方案与压气机的流场进行对比分析。结果表明，开缝位置靠近前缘时压气机总压比提升了1.39%，但综合稳定裕度降低了0.18%；开缝位置靠近尾缘时，压气机总压比提升了2.78%，综合稳定裕度也提升了1.38%。分析发现，转子叶尖开缝能有效控制转子叶片表面流动分离，缓解叶尖通道堵塞，在所研究范围内，开缝位置越靠近尾缘，对静叶通道流场性能改善越明显，削弱气流分离的同时还能抑制气流沿叶高方向潜移，极大程度提高了压气机流场性能。

Abstract:

In order to study the mechanism of the effects of rotor blade tip jet slot on performance and flow structure of transonic axial compressor， a convergent jet slot was designed， and flow control cases of different jet slot position on rotor tip were proposed to compare the flow structure and performance between baseline and each case by simulation. Results show that when the slot position is close to the leading edge， the total pressure ratio of compressor increases by 1.39%， but the comprehensive stability margin decreases by 0.18%.When the slot position is close to the trailing edge， the total pressure ratio of compressor increases by 2.78% and the comprehensive stability margin increases by 1.38%. Rotor surface flow separation is well controlled by blade tip slot， and the tip passage blockage is relieved. Within the range of the study， when slot position is closer to the trailing edge， the performance of stator passage flow field is improved more obviously. The flow separation is weakened and the flow expansion along spanwise is restrained at the same time， so the flow field performance of compressor is improved greatly.