冲压发动机进气道/燃烧室/尾喷管耦合流场计算

推进技术 ›› 2008, Vol. 29 ›› Issue (5): 557-561.

冲压发动机进气道/燃烧室/尾喷管耦合流场计算

石喜勤,陈兵,徐旭,蔡国飙

北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院

发布日期:2021-08-15

Inlet/combustor/nozzle coupled flow field calculation for ramjet

School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 采用耦合求解的方法进行了冲压发动机进气道/燃烧室/尾喷管流场一体化计算,进气道采用单一气体、变比热比模型,燃烧室和尾喷管采用多组分化学动力学模型,湍流模型为k-g湍流模型。进气道与燃烧室界面通过流量、静压等参数实现耦合。结果表明,通过合理设计参数的传递方式,可以快速实现进气道/燃烧室/尾喷管流场的耦合求解,流场分布合理。

关键词: 进气道;燃烧室;冲压喷气发动机;一体化流场+;数值仿真

Abstract: An efficient multi-code CFD solver was designed to simulate the integrated flowfields in a ramjet engine in a loosely coupled manner.The multiblock,multigrid,single-species,turbulence flow solver was used to simulate the flows in the inlet,while a multi-species one to simulate the flows in the combustor and nozzle.The k-g turbulence model was used in the calculations.By means of carefully designed message feedback of mass flow rate,static pressure,etc.,on the inlet-combustor interface,the flowfield of inlet and combustor can be solved efficiently.The turbulent flowfields obtained are reasonable.

Key words: Inlet;Combustor;Ramjet engine;Coupled flowfield;Numerical simulation

石喜勤,陈兵,徐旭,蔡国飙. 冲压发动机进气道/燃烧室/尾喷管耦合流场计算[J]. 推进技术, 2008, 29(5): 557-561.