Preliminary Design of a Radial Turbine for Methane Expander Rocket-Engine
Preliminary Design of a Radial Turbine for Methane Expander Rocket-Engine
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DOI：
10.1016/j.egypro.2017.08.221
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发表时间：
2017-09
期刊：
影响因子：
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通讯作者：
Angelo Leto-;A. Bonfiglioli
中科院分区：
文献类型：
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作者：
Angelo Leto-;A. Bonfiglioli
本文件概述了意大利航空航天研究中心（CIRA）最近为在现代火箭推进系统中使用径流式涡轮机而进行的研究工作。在过去的几年里，CIRA一直参与由意大利研究部（MIUR）资助的HYPROB计划。HYPROB的目的是发展能力，以巩固国家在火箭发动机系统方面的背景，用于未来的空间应用。由于目前液态甲烷是航空航天推进中的一种创新燃料，HYPROB的目标之一是开发一种模拟工具，用于径向涡轮机的初步设计，该涡轮机用于驱动以甲烷运行的膨胀循环火箭发动机中的涡轮泵。
The present paper summarizes recent research efforts carried out at the Italian Aerospace Research Centre, CIRA, aimed at using radial turbines in modern rocket-propulsion systems. Over the last few years, CIRA has been involved in the HYPROB program, funded by the Italian Ministry of Research (MIUR). HYPROB aims at developing competences to consolidate the national background on rocket-engine systems for future space applications. Since nowadays liquid methane represents an innovative fuel in aerospace propulsion, one of HYPROB's objectives is the development of a simulation tool for the preliminary design of the radial turbines used to drive the turbo-pumps in expander-cycle rocket-engines operating with methane.