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首页> 外文期刊>International Journal of Heat and Mass Transfer >Multidisciplinary simulation of a regeneratively cooled thrust chamber of liquid rocket engine: Turbulent combustion and nozzle flow
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Multidisciplinary simulation of a regeneratively cooled thrust chamber of liquid rocket engine: Turbulent combustion and nozzle flow

机译：液体火箭发动机蓄冷式推力室的多学科模拟：湍流燃烧和喷嘴流

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摘要

The present study proposed a unified framework to simulate multi-physical processes which are crucial for trade-off design of liquid rocket thrust chambers among propulsive performance, regenerative cooling, and pressure budget. As the first part, a turbulent combustion model based on the flamelet approach was developed to effectively incorporate detailed chemistry of high hydrocarbon fuel, turbulent mixing, enthalpy loss, and pressure variations within the nonadiabatic nozzle flow. In order to correctly capture the convective heat transfer and viscous friction in the turbulent boundary layer at the chamber wall, an advanced low-Reynolds number turbulence model is adopted in an axisymmetric compressible RANS solver, which is interactively coupled with a cooling analysis module for the conjugate heat transfer and hydraulics through the regenerative cooling channels. The present method has been applied to an actual regeneratively cooled thrust chamber and compared with measurement of hot-firing tests in terms of specific impulse, characteristic velocity, and thrust coefficient. Based on the numerical results, the effects of additional fuel cooling injection and wall friction on the propulsive parameters are discussed.
机译：本研究提出了一个统一的框架来模拟多种物理过程，这对于液体火箭推进室的推进性能，再生冷却和压力预算之间的折衷设计至关重要。作为第一部分，开发了基于小火焰方法的湍流燃烧模型，以有效地结合高碳氢燃料的详细化学组成，湍流混合，焓损失以及非绝热喷嘴流内的压力变化。为了正确捕获腔室壁湍流边界层中的对流传热和粘滞摩擦，在轴对称可压缩RANS求解器中采用了先进的低雷诺数湍流模型，该模型与冷却分析模块交互耦合。通过再生冷却通道将传热和水力结合起来。本方法已经应用于实际的再生冷却推力室，并且在比冲，特征速度和推力系数方面与热点火测试的测量结果进行了比较。基于数值结果，讨论了额外的燃料冷却喷射和壁摩擦对推进参数的影响。

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