摘要
为了进一步研究叶尖小翼对跨声速压气机级稳定工作裕度的影响,采用数值方法对NASA Stage 37压气机级加装不同叶尖小翼的效果进行了研究。通过对比原型压气机级与加装叶尖小翼压气机级的流场特性,揭示了压力面叶尖小翼的扩稳机理。研究结果表明:随着压力面小翼宽度增加,压气机级的稳定工作裕度分别提高了7.35%、12.27%、19.49%、12.34%。压力面小翼的扩稳机理在于有效减弱了泄漏涡与激波的干涉程度,改善了转子区域的通流情况,同时减弱了下游静子的吸力面分离,使得静子区域低能流体减少,降低了流动损失。
In order to further investigate the influence of tip winglets on the stable operating margin of a transonic compressor stage,the effects of different tip winglets on NASA Stage 37 compressor stage were studied numerically by comparing the flow field characteristics of the prototype compressor stage to the compressor stage equipped with tip winglets.Additionally,the stability expansion mechanism of the pressure-side tip winglet was revealed.The results showed that with the increase of pressure-side tip winglet width,the stable operating margin increased by 7.35%,12.27%,19.49%and 12.34%,respectively.According to the stability expansion mechanism of the pressure-side tip winglet,the interference between the leakage vortex and the shock wave was weakened,the flow condition in the rotor area improved,and the separation on the downstream stator suction-side was reduced.Consequently,both the low-energy fluid and the flow loss in the stator area were diminished.
作者
钟兢军
王缘
赵傲
吴宛洋
ZHONG Jingjun;WANG Yuan;ZHAO Ao;WU Wanyang(Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China)
出处
《航空动力学报》
北大核心
2025年第3期369-379,共11页
Journal of Aerospace Power
基金
国家自然科学基金重点项目(52236005)
航空发动机及燃气轮机基础科学中心重点项目(P2022-B-Ⅱ-007-001)。
关键词
叶尖小翼
Stage
37压气机级
叶顶泄漏
稳定工作裕度
扩稳机理
tip winglets
Stage 37 compressor stage
tip leakage flow
stable operating margin
stability expansion mechanism
