基于NURBS曲线的涡控蛇形进气道设计  

Design of vortex-controlled serpentine inlet based on NURBS curve

作　　者：黄晨[1] 谢文忠[1] 靖建朋[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国人民解放军驻西安飞机工业(集团)有限责任公司军事代表室,西安710089

出　　处：《航空动力学报》2013年第10期2355-2363,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(11002069)

摘　　要：利用NURBS(non-uniform rational B-spline)曲线成功实现了涡控蛇形进气道参数化描述,并运用数值仿真方法对其中两个关键设计参数进行参数化研究.仿真结果表明:①第二S弯上壁面两侧后掠状凸起型面诱导的受控旋涡能够将低能流牵引至出口两侧,从而抑制大范围的气流分离,但凸起角取值需权衡选取,否则将不利于涡控蛇形进气道综合性能的改善.②通过抬高第二S弯下壁面能够减缓上壁面沿程逆压力梯度,进而影响第二S弯上壁面的流态,恰当的取值能够以微小的总压损失换取大幅度的畸变改善.③当设计参数选取恰当时,涡控蛇形进气道在设计状态下总压恢复系数为0.966 7,畸变指数为0.245 1.进气道性能较传统方案有显著改善,使得蛇形进气道迈向工程实用成为可能.A parametric description method was established using NURBS （nonuniform rational Bspline） curve, and effects of two key parameters on the inlet performance were studied by numerical simulation. Results show.（1） Controlled vortex induced by backswept convex pon the second Sduct can lead low momentum flow to side regions of AIP （aerody namic interface plane）, and the separation region can be reduced. The value of convex angle need to be selected appropriately, otherwise the convex angle is not conducive to the im provement of the vortexcontrolled serpentine inlet performance. （2） Uplifting the lower wall of second Sduct properly could alleviate the adverse pressure gradient on the wall, which has positive effects on the flow within ducts. （3） While the design parameters are chosen ap propriately, the totalpressure recovery coefficient of the vortexcontrolled serpentine inlet is 0. 9667 under design conditions, the distortion index is 0. 245 1, and the inlet performance has been significantly improved.

关 键 词：涡控蛇形进气道 受控旋涡 低能流 NURBS(non-uniformrational B-spline) 凸起角 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]