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Investigation of Exhaust Plume Radiation of Lox/Kerosene Rocket Engine

机译：熏氧/煤油火箭发动机尾气辐射的研究

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During the rocket launch or engine trial, launch pad or test bench will be heated intensely by high temperature gas exhausted from the engine nozzle. Because of the low oxygen-fuel equivalence ratio in thrust chamber of the engine, the combustion product is fuel-rich hot gas. Combustion occurs after the fuel-rich hot gas exhausting from engine nozzle and mixing with surrounding air. High temperature flame generates in the gas-air mixing layer. This phenomenon is called afterburning. Radiant heat holds a great quantity and convection holds a less, because the plume do not scour the launch pad directly. In this paper, research on exhaust plume radiative heat transfer of LOX/Kerosene rocket engine is presented. Firstly, nozzle and plume flow field is obtained via solving Reynolds Averaged Navier-Stokes equations with k-e turbulent model. Finite-rate combustion model is employed to describe the equilibrium flow and afterburning. Secondly, the radiative heat transfer is investigated based on the temperature, pressure and species fraction of the plume flow field calculated previously. Discrete ordinates model (DOM) is used to simulate radiative heat transfer, and weighted sum of grey gases model is used to simulate absorption coefficient of gas. Furthermore, the accuracy and reliability of simulation model are verified through comparison with the radiation measurement in engine trial run. Analysis and simulation results show that afterburning effects lead to a much higher heat flux than expected. Thermal protection method of launch pad will be suggested according to the result of this research.
机译：在火箭发射或发动机试验期间，发射垫或测试台将被从发动机喷嘴排出的高温气体强烈加热。由于发动机推力室内的氧-燃料当量比低，燃烧产物是富含燃料的热气。富燃料的热气从发动机喷嘴排出并与周围的空气混合后，就会发生燃烧。燃气混合层中产生高温火焰。这种现象称为加力燃烧。辐射热占有大量热量，而对流占有较少的热量，因为烟羽不会直接冲刷发射台。本文对LOX /煤油火箭发动机的尾羽辐射热传递进行了研究。首先，通过用k-e湍流模型求解雷诺平均Navier-Stokes方程来获得喷嘴和羽流流场。采用有限速率燃烧模型来描述平衡流和后燃。其次，根据先前计算的羽流场的温度，压力和种类分数研究了辐射传热。离散坐标模型（DOM）用于模拟辐射传热，灰气体的加权总和模型用于模拟气体的吸收系数。此外，通过与发动机试运行中的辐射测量结果进行比较，验证了仿真模型的准确性和可靠性。分析和模拟结果表明，后燃效应导致比预期高得多的热通量。根据这项研究的结果，将提出发射台的热保护方法。

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