| 大涵道比涡扇发动机滑油流量中断 |
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| 引用本文： | 雷友锋,王 海,宣建光.大涵道比涡扇发动机滑油流量中断[J].航空发动机,2013,39(6):19-23. |
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| 作者姓名： | 雷友锋 王 海 宣建光 |
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| 作者单位： | 复杂航空系统仿真重点实验室，北京 100076 |
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| 摘 要： | 基于GJB 241A-2010、JSSG-2007B等国内外军用标准规范,分析了航空发动机滑油流量中断工作能力通用要求以及试验验证通用要求.针对大涵道比涡扇发动机,分析指出其使用特点与战斗机发动机有明显差异,其滑油流量中断工作能力要求不能直接照搬军用标准的相关规定.根据运输机发动机的使用特点分析,借鉴国外航空发动机的相关技术经验,提出了大涵道比涡扇发动机的滑油流量中断工作能力要求以及滑油流量中断试验的程序与方法.
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| 关 键 词： | 航空发动机 大涵道比涡扇发动机 滑油流量中断 |
Analysis of Working Requirements and Test Methods for High Bypass Ratio Turbofan Engine during Oil Flow Interruption |
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| Authors: | LEI You-feng WANG Hai XUAN Jian-guang |
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| Institution: | Science and Technology on Complex Aviation Systems Simulation Laboratory, Beijing 100076, China |
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| Abstract: | The general working capacities and test requirements of aeroengine during oil flow interruption were analyzed based on GJB241A-2010 and JSSG-2007B etc. Aiming at the high bypass ratio turbofan engine, its working capacities during oil flow interruption can not be copied from the military specifications because its features are different from the fighter engine＇s. After analysing the features of high bypass ratio turbofan and referring to the technology experiences of foreign engines, the working capacities and test methods of high bypass ratio turbofan engine during oil flow interruption were put up. |
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| Keywords: | aeroengine high bypass ratio turbofan engine oil flow interruption |
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