民用航空发动机热负荷开发和热图敏感性分析

IF 1.3 Q2 ENGINEERING, AEROSPACE
Alireza Ebrahimi, S. Jafari, T. Nikolaidis
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引用次数: 0

摘要

新一代民用航空发动机的设计复杂性导致了对发动机部件的更高要求、更高的部件温度、更高的发热量以及最终的关键热管理问题。本文将提出一种方法,为热源产生的热负荷创建基于物理的模型,并进行系统的敏感性分析,以确定设计参数对民用航空发动机热行为的影响。系统地讨论了热源(如附件齿轮箱、轴承、泵等)产生的热负荷范围和水平,以及散热器(如发动机燃料、机油和空气)的吸热能力。然后,将通过对热负荷值和散热片流速的敏感性分析,探讨新一代涡扇发动机热管理系统设计和开发的实际研究挑战。相应地,还将提出并讨论提高推进系统热性能的潜在解决方案。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Heat Load Development and Heat Map Sensitivity Analysis for Civil Aero-Engines
The design complexity of the new generation of civil aero-engines results in higher demands on engines’ components, higher component temperatures, higher heat generation, and, finally, critical thermal management issues. This paper will propose a methodological approach to creating physics-based models for heat loads developed by sources, as well as a systematic sensitivity analysis to identify the effects of design parameters on the thermal behavior of civil aero-engines. The ranges and levels of heat loads generated by heat sources (e.g., accessory gearbox, bearing, pumps, etc.) and the heat absorption capacity of heat sinks (e.g., engine fuel, oil, and air) are discussed systematically. The practical research challenges for thermal management system design and development for the new and next generation of turbofan engines will then be addressed through a sensitivity analysis of the heat load values as well as the heat sink flow rates. The potential solutions for thermal performance enhancements of propulsion systems will be proposed and discussed accordingly.
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来源期刊
CiteScore
2.30
自引率
21.40%
发文量
29
审稿时长
11 weeks
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