Regenerative cooling of graphite nozzle for hybrid rockets using nitrous oxide as oxidant

在本项目的框架内，开发了实验和数值装置，用于研究在混合动力火箭发动机中实现喷嘴侵蚀抑制的再生冷却系统。研究人员在今年上半年证明了这种新技术是可行的，并改善了推进系统的性能。进行了许多实验测试，在测试中没有观察到喷嘴侵蚀，尽管在不实施主动冷却时，所考虑的配置受到这种现象的极大影响。此外，还建立了精确的数值模型，用于电机运行工况的研究和预测。这些模型提供了对发生在冷却通道内的多相物理的见解。这些模型允许喷嘴温度的预测，因此，喷嘴侵蚀的发生。最后，将数值计算结果与实验结果进行了比较，以评价其有效性。在此框架下，获得两篇论文并投稿至两本高质量Q1期刊。

In the framework of the project, experimental and numerical apparatus have been developed for the study of the implementation of a regenerative cooling system in hybrid rocket engines for the nozzle erosion suppression. The investigators demonstrated in this first half year that this novel technology is possible and improves the performance of the propulsion system. Many experimental tests have been carried out and no nozzle erosion was observed in the tests, despite the considered configuration is extremely affected by this phenomenon when active cooling is not implemented. In addition, accurate numerical models have been developed for the study and the prediction of the motor operating conditions. These models give an insight in the multiphase physics occurring inside the cooling channels. These models allow the prediction of the nozzle temperature and hence, the occurrence of the nozzle erosion. Finally, the numerical results have been compared with the experimental ones in order to assess their validity. In this framework, two papers were obtained and submitted to two high quality Q1 journals.