Purpose

This paper aims to detail the reactive flow simulations of a LOX/CH4 multi-element rocket engine. The work has been conducted within the framework of the HYPROB-BREAD project whose main objective is the design, manufacture and testing of a LOX/LCH4 regeneratively cooled ground demonstrator.

Design/methodology/approach

Numerical simulations have been carried out with both commercial software and CIRA software developed in house. Two sets of boundary conditions, nominal and experimental, have been applied from which a code-to-code validation has been effected with the former and a code-to-experiment validation with the latter.

Findings

The results presented include both flow data and heat fluxes as well as parameters associated with engine performance, and indicate an excellent agreement with experimental data of a LOX/CH4 multi-element rocket engine.

Originality/value

The research is unique as the CIRA code Numerical Experimental Tool (NExT) has been validated with the commercial software FLUENT as well as with experimental values from the firing of the LOX/CH4 rocket engine demonstrator.

中文翻译：

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LOX / CH4火箭发动机的反应流模拟

目的

本文旨在详细介绍LOX / CH4多元素火箭发动机的反应流模拟。该工作是在HYPROB-BREAD项目的框架内进行的，该项目的主要目标是LOX / LCH4蓄冷式地面演示器的设计，制造和测试。

设计/方法/方法

使用商业软件和内部开发的CIRA软件都可以进行数值模拟。已经应用了两组边界条件，名义条件和实验条件，前者从中进行了代码到代码的验证，而后者则进行了代码到实验的验证。

发现

给出的结果包括流量数据和热通量，以及与发动机性能相关的参数，并表明与LOX / CH4多元素火箭发动机的实验数据非常吻合。

创意/价值

这项研究是独一无二的，因为CIRA代码数值实验工具（NExT）已通过商用软件FLUENT以及LOX / CH4火箭发动机演示器发射的实验值进行了验证。