Abstract: A lean rotor was produced on the basis of transonic compressor NASA rotor 11 original geometry. The unsteady numerical simulation for the flow fields of this lean rotor and rotor 11 under design rotation speed was performed. The numerical results show that the static pressure difference at lean rotor tip section leading edge is lower compared with original rotor. The position of low axial velocity fluid at lean rotor tip is nearer to the outlet, and the lean rotor prevents the low energy fluid on suction side flowing into the blade tip clearance.

Key words: Rotor; Circumferential lean; Circumferential total pressure distortion inlet; Static pressure difference; Blade tip；Axial velocity

摘要： 以跨声速轴流压气机NASA转子11为原型进行周向弯曲改进,对得到的周向弯曲转子与原型转子内流场在相同的进出口条件和设计转速下进行了非定常数值模拟,结果表明:在一个非定常周期的不同时刻,弯曲叶片叶尖前缘压力面与吸力面静压差都小于原型转子,弯曲转子叶尖处低轴向速度气流团的位置相比原型转子更靠近出口,同时弯曲叶片吸力面附面层内的低能流体更不容易向叶尖区域迁移。 

关键词: 转子;周向弯曲;周向总压畸变进气;静压差;叶尖;轴向速度