摘要
以跨声速压气机NASA转子11为原型进行前掠改进,对得到的前掠转子与原型转子内流场进行了定常数值模拟,结果表明:在设计转速下前掠转子的性能有所提高,尤其是近失速流量有明显的降低.在周向总压畸变进气条件下,对转子11和前掠转子进行了非定常数值模拟,两者的性能较均匀进气条件下都出现了不同程度的下降,但前掠转子的近失速流量仍明显低于转子11,这是因为转子11叶尖区域处气流较前掠转子更易堵塞.
A forward swept rotor was produced on the basis of transonic compressor NASA rotor 11 original geometry. The steady flow fields of this forward swept rotor and ro- tor 11 have been numerically simulated under design rotation speed, which shows that the performance of forward swept rotor especially the stall margin has been improved. The un- steady simulation of the flow fields of forward swept rotor and rotor 11 indicates that the in- let circumferential total pressure distortion has caused the deterioration of performance. However the forward swept rotor has lower mass flow near stall point compared with the o- riginal rotor 11 under the inlet circumferential pressure distortion, because the flow field near the blade tip region benefits from the forward swept rotor.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第3期657-665,共9页
Journal of Aerospace Power
关键词
前掠转子
周向总压畸变进气
静压差
叶尖
失速
forward swept rotor
circumferential total pressure distortion inlet
static pressure difference
blade tip
stall
