| 摘要: |
| 对塞锥流场采用七组元八反应模型,对内喷管流场采用六组元八反应模型,数值模拟了氢氧塞式喷管的流动参数、组分质量分数和热力学参数的分布,并把化学反应非平衡流动和冻结流动的流场进行了比较。在边界层和底部回流区内,燃气流速低、温度高,组分O2,H2,O,H,OH的含量比主流内高,而H2O的含量比主流内低。绝热指数随温度的降低而增大,气体常数随温度的降低而减小。外界空气对塞锥流场的影响只限于流动剪切层,对塞锥主流的影响不大。 |
| 关键词: 火箭发动机 塞式喷管 流场 化学反应 热力学参数 数值仿真 |
| DOI： |
| 分类号:V430 |
| 基金项目:国家"八六三"资助项目(863 2 3 4 10)。 |
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| Numerical simulation on aerospike nozzle flowfieldwith chemical non-equilibrium reaction |
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WANG Chang-hui, LIU Yu
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School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China
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| Abstract: |
| Based on 7-species, 8-reaction and 6-species, 8-reaction finite-rate chemical models for plug and cell combustion process, the distribution of H2/O2 aerospike nozzle flow parameters, mass fractions and thermo-dynamical parameters were numerically simulated. Chemical non-equilibrium and frozen flowfields were compared.It is shown that for low velocity and high temperature in boundary layer and base region, mass density of O2,H2,O,H,OH is higher but H2O lower compared with that in main stream. Adiabatic exponent is raised and gas contant is fallen when temperature is decreased. It is found that ambient air affects plug flowfield within the range of shear layer and has no great influence on the main stream. |
| Key words: Rocket engine Aerospike nozzle Flow field Chemical reaction Thermodynamic parameter Numerical simulation |
