S弯喷管喷口内切流动特性数值模拟
Numerical Simulation of Flow Characteristics in S-shaped Nozzle With a Inscribed Exit
王明新 1周莉 2史经纬 1王占学1
作者信息
- 1. 西北工业大学动力与能源学院,西安市 710072
- 2. 西北工业大学动力与能源学院,西安市 710072;先进航空发动机协同创新中心,北京市 100191
- 折叠
摘要
为了研究采用喷口内切修型方式的S弯喷管的流动特性,数值模拟了S弯基准喷管和内切角度为10°、20°、30°、40°、45°的S弯喷口内切喷管.研究表明,相对于S弯基准喷管,喷口内切会使喷管内第一弯之后的流动参数变化更加剧烈,降低喷管出口最大马赫数与波系强度,使喷流中心产生两对流向涡牵引喷流,改变尾喷流的结构,增加喷流高速核心区的长度.随着内切角度增加,喷流发生轴转换的现象更加明显,角涡对喷流的影响增大,喷流高速核心区的长度先增加后随着轴转换过程加快又缩短,喷管推力性能随内切角度的增加逐渐降低.
Abstract
In order to study the flow characteristics of the S-shaped nozzle with a inscribed exit,numerical simulations were performed for the S-shaped reference nozzle and the S-shaped nozzle with different inscribed angles of 10°,20°,30°,40°,and 45°.It is shown that,compared with the S-shaped reference nozzle,the nozzle with a inscribed exit will make the flow parameters change more drastically after the first bend in the nozzle,reduce the maximum Mach number and the wave system strength at the nozzle exit,generate two pairs of flow vortices in the center of the jet to traction the jet,change the structure of the wake jet,and increase the length of the high-speed core region of the jet.With the increase of the inscribed angle,the more obvious phenomenon of the jet axial conversion,the influence of angular vortices on the jet increases.The length of the high-speed core region of the jet first increases and then shortens with the acceleration of the axial transition process.The nozzle thrust performance gradually decreases with the increase of the inscribed angle.
关键词
S弯喷管/喷口内切/内切角度/流动特性Key words
S-shaped nozzle/inscribed exit/inscribed angle/flow characteristics引用本文复制引用
基金项目
国家自然科学基金项目(52076180)
陕西省杰出青年科学基金项目(2021JC-10)
国家科技重大专项(J2019-Ⅱ-0015-0036)
航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅰ-002-001)
航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅱ-010-001)
中央高校基本科研业务费专项资金资助(501XTCX2023146001)
出版年
2024
NETL
NSTL
万方数据