摘要
在叶尖切线速度U=480 m/s的条件下,对级压比为2.4、负荷系数为0.42的风扇进口级进行了初步的气动设计,并进行了数值验证.分析了转子尖部和静子根部的设计难点,重点考察了进口预旋分布、设计压比分布、转子叶尖激波前马赫数、静子根部进口马赫数以及静子出口气流角等参数,以及静子附面层抽气对性能的影响及其内部机制.结果表明:采用常规设计的转子能够达到0.42的负荷系数;在该负荷条件下,静子根部会出现进口超声的情况,并在根部通道中产生强烈的正激波;如果静子根部存在贯穿通道的正激波,即D因子较小,仍会发生严重的分离失速.
The preliminary aerodynamic design of an inlet fan stage was validated by numerical simulation.The inlet fan stage was designed to produce a total pressure ratio of 2.4 and loading coefficient of 0.42 at tip speed of 480 m/s.The design difficulty of rotor tip and stator hub was analyzed.Some design parameters were especially assessed,such as inlet swirl angle,design pressure ratio,rotor pre-shock Mach number,inlet Mach number and outlet angle of stator.The boundary layer bleeding at stator hub and its＇ mechanism were discussed.It is concluded that conventional rotor has capability to attain the loading coefficient of 0.42;the inlet flow near the stator hub is supersonic under such loading level and strong normal shock exists in hub passage of stator;the normal shock spreads through the hub passage and incurs severe separation stall even though the diffusion factor is low.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第11期2548-2555,共8页
Journal of Aerospace Power
关键词
高负荷风扇
气动设计
转子尖部
静子根部
附面层抽气
highly loaded fan； aerodynamic design； rotor tip； stator hub； boundary layer bleeding；
