摘要
针对无人机动力装置的需求,为某小推力的涡轮喷气发动机进行了单级离心压气机的气动设计.所用的压气机设计方法为:从一维的热力计算出发来进行流道结构设计,以二维通流计算为基础,通过调整各排叶片的环量分布,来获得所要求的气动性能,并通过叶片任意造型最终生成与通流计算结果较为一致的三维叶型,最后通过三维计算流体动力学(CFD)计算来分析气动设计的性能结果.最终设计出的离心压气机在设计点的各项性能参数均达到了设计要求,并且在各个转速下压气机的特性线比较平缓,压气机有较为宽广的稳定工作范围.
An aerodynamic design of a small centrifugal compressor for some pilotless aircraft was presented in this paper. One dimensional thermal calculation was conducted to configure the flow path. And based on two-dimensional through flow design, the required aerodynamic performance was obtained by adjusting the distribution of velocity circulation of the blade rows. Then three-dimensional blade airfoils can be got by arbitrary camber lines blading. At last,three dimensional CFD （computational fluid dynamics） calculation was used to analyze the result of the aerodynamic design. All performance parameters of the centrifugal compressor meet the design requirement at design point. And the performance curves at all speeds are really flat. Therefor the work stability of the compressor have a fairly broad scope.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第3期557-564,共8页
Journal of Aerospace Power
基金
国家自然科学基金(50136010
50676004
50736007)
关键词
通流设计
任意造型
离心叶轮
分流叶片
气动设计
through flow design
arbitrary camber lines blading
centrifugal impeller
splitter blade
aerodynamic design
