全几何约束下的非对称喷管伴随优化设计研究  

Asymmetric nozzle design method under full geometric constraints based on adjoint optimization method

作　　者：付珂欣 徐惊雷[1] 刘增旭 俞凯凯[1] FU Kexin;XU Jinglei;LIU Zengxu;YU Kaikai(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2025年第3期51-60,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(12332018);航空发动机及燃气轮机基础科学中心项目(P2022-B-I-006-001)。

摘　　要：为了实现高超声速排气系统与飞行器后体一体化,非对称喷管需要在有限的空间内、严格的几何约束下完成对高温高压气体的高效膨胀,并达到高性能的需求。然而在实际非对称喷管设计中,往往面临着强几何约束、设计变量规模较大等问题,造成现有方法难以完全实现非对称喷管的高效设计。为此,本文采用伴随优化方法针对非对称喷管开展气动设计,分别展开了全几何约束下的推力最优和升力最优两类设计研究。在推力最优设计结果中可得到,优化后的非对称喷管内部压力场分布显著改变,从而使得推力系数相对于初始直壁面喷管增加了5.966%。在升力最优设计中,喷管内下壁面会产生一道弱激波,该道弱激波在喷管上壁面的反射显著提升了上壁面局部的压力,进而使得升力相对于直壁面喷管增加了44.921%。从两类优化结果中可以看到相比初始构型,伴随优化方法可以在实现全几何约束下的非对称喷管设计同时,能够有效保持喷管所需的推力及升力性能。In order to achieve the integration of hypersonic exhaust systems and aircraft afterbodies,asym⁃metric nozzles need to efficiently expand high-temperature and high-pressure gases within limited space and strict geometric constraints,and meet the requirements of high performance.However,in actual asymmetric noz⁃zle design,there are often problems such as strong geometric constraints and large design variables,which make it difficult for existing methods to fully achieve efficient design of asymmetric nozzles.Therefore,this article adopts the adjoint optimization method to carry out aerodynamic design for asymmetric nozzles,and conducts two types of design studies:thrust optimization and lift optimization under full geometric constraints.In the optimal thrust design results,it can be observed that the pressure distribution inside the optimized asymmetric nozzle sig⁃nificantly changes,resulting in a 5.966%increase in thrust coefficient relative to the initial straight wall nozzle.In the optimal lift design,a weak shock wave is generated from the lower wall inside the nozzle.The reflection of this weak shock wave on the upper wall of the nozzle significantly increases the local pressure on the upper wall,resulting in a 44.921%increase in lift compared to a straight wall nozzle.From the two types of optimization re⁃sults,it can be seen that compared to the initial configuration,the adjoint optimization method can effectively maintain the required thrust and lift performance of the nozzle while achieving asymmetric nozzle design under full geometric constraints.

关 键 词：超燃冲压发动机 非对称喷管 气动优化 离散伴随 几何约束 

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]