航空学报2025，Vol.46Issue(8)：128-143,16.DOI:10.7527/S1000-6893.2024.31009
两级膨胀喷管设计方法及数值模拟
Two-stage expansion nozzle design method and numerical simulation
摘要
Abstract
To enhance the performance of the nozzle in a wide airspace(0-24 km)and wide speed domain(Mach number 0-5),a two-stage expansion nozzle design methodology is investigated by utilizing altitude compen-sation and inverse design concepts.Firstly,the design method and steps of the two-stage expansion nozzle are intro-duced.The two-stage expansion nozzle profiles are divided into the base section and extension section profiles.The base section profiles are generated by the reverse design method based on the wall pressure,which is used to shorten the negative thrust surface of the nozzle by changing the position and strength of the shock wave and to im-prove the thrust performance of the nozzle under the low-speed flight condition.The nozzle extension profile adopts the maximum thrust nozzle design method based on strong geometric constraints to meet the purpose of hypersonic vehicle afterbody integration design.Secondly,the validity of the proposed design methodology is verified using nu-merical simulation,in which the numerical calculation methodology is introduced and verified,and the grid resolution is determined.Further,the design method for the reverse design of nozzle base profile for controlling wall pressure distri-bution is validated,and the goal of forward/backward shifting of the shock wave is achieved.At the same time,a study is conducted on the influence of the two key design parameters,i.e.,the position control factor and the pressure control factor,on the the performance of the nozzle.Finally,comparative analysis of the proposed method and the maximum thrust nozzle design method with full geometric constraints is performed to verify the effectiveness and supe-riority of the new method.The results show that compared to the fully geometrically constrained maximum-thrust nozzle,the nozzle designed with the proposed method improves the thrust performance by 7.86%in the over-expansion state and decreases the thrust performance by only 0.75%in the under-expansion state under typical de-sign conditions,which provides a theoretical basis for the design of the exhaust system of hypersonic vehicles.关键词
两级膨胀/正反设计/特征线法/全几何约束/最大推力理论Key words
two-stage expansion/forward and reverse design/method of characteristics/full geometric constraint/maximum thrust theory分类
航空航天引用本文复制引用
裴文倩,俞凯凯,刘增旭,宁琪月,徐惊雷..两级膨胀喷管设计方法及数值模拟[J].航空学报,2025,46(8):128-143,16.基金项目
航空发动机及燃气轮机基础科学中心项目(P2022-B-I-006-001) （P2022-B-I-006-001）
