检索结果-内蒙古大学图书馆

SSRN 2022年

作者： Nikolaidis, Theoklis Jafari, Soheil Sibilli, Thierry Kipouros, Timoleon Ayat, Sabrina Isikveren, Askin Centre for Propulsion and Thermal Power Engineering Cranfield University BedfordMK43 0AL United Kingdom Airbus Operations GmbH Kreetslag 10 HamburgD-21129 Germany Formerly Company Expert on Thermal Systems SAFRAN Tech Safran Paris Saclay France SAFRAN Paris Saclay Châteaufort CS 80112 Magny-les-Hameaux78772 France SAFRAN S.A. c/o Aerospace Embedded Solutions GmbH Munich80639 Germany Reader in Gas Turbine Performance and Numerical Simulation Centre for Propulsion Engineering and Power United Kingdom Lecturer in Gas Turbine Thermal Management and Control Centre for Propulsion Engineering and Power United Kingdom Hydrogen Fuel System Development Engineer Airbus Operations GmbH Kreetslag 10 HamburgD-21129 Germany Formerly Company Expert on Thermal Systems SAFRAN Tech Safran Paris France Senior Lecturer in Computational Engineering Design Optimisation Centre for Propulsion Engineering and Power United Kingdom Research Engineer Electrical & Electronic Systems Group Safran Tech SAFRAN Paris Saclay France Advanced Aircraft Concepts and Energy Systems Senior Group Expert Integrated Aircraft Systems and Operations SAFRAN Tech France

New generation of propulsion systems are increasingly complex with higher requirements on engines for efficiency, thrust and power generation. As a side effect, the produced thermal loads are higher, imposing limitations on the air vehicle performance. The current paper offers a novel methodology for thermal management system architecture design for high power hybrid electric propulsion systems. Four cases are investigated including state-of-the-art conventional thermal management system, pre-heated two-phase thermal management system, utilizing thermally neutral heat transfer fluids in a two-phase cooling mechanism, and a combination of single- and two-phase thermal management system architectures. For this purpose, a Vertical Take-Off and Landing multi-mission aircraft is selected as the case study in which the existing mechanically driven lift fan is replaced by an electric fan to replicate a high-power hybrid electric propulsion system of the future generation. The results confirm that the performance of the pre-heated two-phase thermal management system surpasses the other cases without exceeding the temperature limit. On the contrary, the state-of-the-art conventional system can operate only for 70 seconds. So, the results confirm the effectiveness of the proposed thermal management system architecture in dealing with MW scale thermal loads generated by next generation high power hybrid electric propulsion systems. © 2022, The Authors. All rights reserved.

关键词： Temperature control

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：