摘要
在推进剂燃烧的建模上,传统的热力计算方法一般基于总焓守恒求解定压绝热燃烧温度和平衡组分,不能考虑壁面传热;在燃气流动的建模上,通常采用的冻结流模型认为本地的组分及热物理性质与燃烧室瞬时一致,忽略了这些参数因来流气体与本网格滞留气体掺混带来的随时间的缓变效应。提出了一种新颖的可以考虑壁面传热的基于总能量守恒的化学平衡流计算方法,运用Fortran2008语言,采用面向对象编程方法建立了化学平衡流燃气发生器管道的模块化仿真模型,并将该模型应用到一个包含42个组件的涡轮试验台气路系统的建模与仿真中。与早期模型仿真结果及试验数据的对比发现,新模型的仿真结果有一定改进,更加接近试验数据。
As for the modeling of propellant combustion, the traditional thermodynamic algorithms generally use the total enthalpy conservation to solve constant-pressure adiabatic combustion temperature and equilibrium compositions, which can not consider the wall heat transfer. As for the modeling of combustion-gas flow, the frozen-flow model is usually employed with the assumption that local compositions and the thermophysical properties are instantaneous consistent with those in the combustion chamber, which ignores the slowly-varying effect of these parameters caused by the mixing process of the incoming flow and the residual gas in local grid. In view of the abovementioned weaknesses, a novel chemical equilibrium flow algorithm based on total energy conservation is proposed, which can consider the wall heat transfer. By usifig Fortran 2008 language and object-oriented programming method, a modular simulation model of chemical equilibrium flow gas generator pipe is established, and is applied to the modeling and simulation of a turbine test rig gassystem with 42 components. In comparison with the earlier simulation results and experimental data, the simulation results of the new model make a certain improvement and are closer to the experimental data.
出处
《火箭推进》
CAS
2017年第1期24-31,7,共9页
Journal of Rocket Propulsion
基金
国家自然科学基金(11101023)
关键词
热力计算
化学平衡流
总能量守恒
涡轮试验台系统
数值仿真
thermodynamic calculation
chemical equilibrium flow
total energy conservation
turbine test rig system
numerical simulation
