| 摘要: |
| 针对以空气、煤油为反应物的涡轮试验台燃烧装置及其出口段建立了一种系统层次上的可以处理燃烧和流动耦合效应的模块化数值模型,并提出了一种基于混合物分数的热力计算方案和混合物分数方程,与基于质量流量混合比模型的仿真结果以及试验结果的对比表明,基于混合物分数的模型解决了以往研究中存在的瞬态仿真稳定性问题,并具有与试验结果一致的仿真精度。 |
| 关键词: 液体推进剂火箭发动机 涡轮试验台 燃烧装置 混合物分数 数值仿真 |
| DOI： |
| 分类号: |
| 基金项目:国家自然科学基金(11101023)；北京航空航天大学“唯实”人才培育基金。 |
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| Numerical Modeling and Simulation of Turbine Test Rig Combustion Device()Partition Model Based on Mixture Fraction |
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CHEN Yang1, TANG Zhen-yu1, CAI Guo-biao1, HUANG Yu-long2
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1.School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;2.Beijing Aerospace Measurement & Control Corporation, Beijing 100041,China
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| Abstract: |
| A system-level modularization numerical model which can deal with the coupling effect of combustion and flow was established for combustion device, with air and kerosene as reactants, of a turbine test rig and its outlet section, and a thermodynamic calculation scheme based on mixture fraction and a mixture fraction equation were put forward. Comparison with simulation results of the model based on mass-flow-rate mixture ratio and experimental results indicates that the mixture fraction-based model can solve the problem of transient simulation stability in the previous research, and reach the accuracy of simulation consistent with experimental results. |
| Key words: Liquid propellant rocket engine Turbine test rig Combustion device Mixture fraction Numerical simulation |
