超音速喷嘴叶栅造型设计及数值分析  

STUDY ON AERODYNAMIC DESIGN AND ANALYSIS OF SUPERSONIC NOZZLE FOR LIQUID ROCKET TURBO-PUMP TURBINES

作　　者：杨佃亮[1] 李颖晨[1] 丰镇平[1] 

机构地区：[1]西安交通大学叶轮机械研究所,陕西西安710049

出　　处：《工程热物理学报》2006年第2期217-219,共3页Journal of Engineering Thermophysics

摘　　要：分析了超音速喷嘴内部的流动机理并研究了超音速喷嘴的设计方法,对某液体火箭发动机用氢涡轮超音速喷嘴叶栅进行了改型设计。设计采用尖边喉部和光滑过渡喉部两种方法,其中光滑过渡喉部喷嘴型线设计采用具有局部修改能力的三次非均匀B样条曲线。对超音速喷嘴叶栅复杂内流的全三维数值模拟结果表明:改型叶栅流动性能明显改善,效率提高,光滑过渡喉部喷嘴性能优于尖边喉部喷嘴。Study on internal flow mechanism of supersonic nozzle and its aerodynamic design methods for modern liquid rocket engine turbines is conducted in this paper. Non-Uniform B-Spline is used in the design to construct the nozzle profile due to its good adaptability of shape and ability of local modification. Two kinds of nozzle throat design schemes for supersonic nozzle are discussed, including sharp-edged throat nozzle and slick transition throat nozzle. A supersonic nozzle for liquid rocket turbo-pump hydrogen turbines is analyzed and redesigned as a design case. The numerical simulation using commercial CFD software is then applied to predict the internal flow characteristics and overall performance of the nozzles. The results indicate that the aerodynamic performance of the redesigned supersonic nozzle is improved clearly. And it is found that the slick transition throat is much .better than the sharp-angled throat as it is not easy to cause separation when airflows accelerate and turn at the throat.

关 键 词：超音速叶栅 造型设计 非均匀B样条 

分 类 号：TK474[动力工程及工程热物理—动力机械及工程]