基于超声速进气道原理的Ram-Rotor隔板中弧线造型数值研究  

Numerical investigation of camber line layout in the Ram-Rotor

作　　者：管健 韩吉昂 Guan Jian;Han Ji'ang(Shanghai Aircraft Design and Research Institute, Shanghai, 201210, China;Naval Architecture and Ocean Engineering College,Dalian Maritime University, Liaoning Dalian, 116026, China)

机构地区：[1]中国商飞上海飞机设计研究院,上海201210 [2]大连海事大学船舶与海洋工程学院,辽宁大连116026

出　　处：《机械设计与制造工程》2022年第6期70-74,共5页Machine Design and Manufacturing Engineering

摘　　要：为了进一步提高旋转冲压压缩转子增压比,对不同S1流面造型进行数值研究,通过调整隔板型面中弧线分别形成了4种扩张型的流道造型。结果表明,4种造型方案流道内部激波系强度增大,均能有效提升转子增压比,但转子绝热效率有所降低。其中,中弧线为直线和二次曲线的组合造型方案在绝热效率降低不多的同时拥有最大的增压比。改型方案通过改变激波串位置和子串数目来提升转子增压能力,然而增强的激波串一定程度上恶化了隔板顶部间隙流场,并增大了泄漏流和激波系相互作用引起的流动损失,近隔板压力面附近的低能流体聚集,造成转子流道内部较高的流动损失。For the purpose of obtaining the prospective benefit of improving the total pressure ratio,numerical investigation is made on ram-rotors with different blade to blade profiles.The blade to blade profile is changed by adjusting the curve type of strake camber line to form the expansive flow path,and four modified schemes are formed.The results show that all four layout schemes show an increase in terms of total pressure ratio due to strengthened shock systems but with a sacrifice of lowering adiabatic efficiency.The modified scheme with combination camber curve of straight and quadratic curves has the largest total pressure ratio with a relatively small flow loss.The expanded flow path in modified schemes can improve pressure rising capacity by changing the position and number of shock trains.The enhanced shock train aggravates strake tip leakage loss and the flow interferes between leakage flow and shocks,and near the strake pressure side there accumulates a low momentum fluid group.The deprivation of flow in the flow path leads to a relatively high flow loss among four modified ram-rotors.

关 键 词：增压比 S1流面 中弧线 旋转冲压压缩转子 激波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]