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微型涡喷发动机顶层设计研究
引用本文:黄国平,温泉,李博,梁德旺.微型涡喷发动机顶层设计研究[J].航空动力学报,2003,18(6):832-838.
作者姓名:黄国平  温泉  李博  梁德旺
作者单位:南京航空航天大学,能源与动力学院,江苏,南京,210016
摘    要:对微型涡轮喷气发动机的顶层设计问题进行了研究。首先分析了发动机尺寸对性能的影响,揭示了微型发动机推重比具有与尺寸成反比提高的潜力。基于各相关学科近期能达到的技术水平,选择了微型发动机尺寸并提出了初步设计方案。对微型涡喷发动机的压比、燃烧室出口温度和各部件效率等设计参数进行了单变量和双变量分析,得到了这些参数对推力、耗油率等性能的影响规律。提出了一个能简便准确地判断微型发动机顶层设计方案是否能产生推力的判别准则,并得出了高、中、低性能的三种气动热力参数顶层设计方案。

关 键 词:航空、航天推进系统  微型涡轮发动机  顶层设计  参数分析  推重比
文章编号:1000-8055(2003)06-0832-07
收稿时间:2003/3/29 0:00:00
修稿时间:2003年3月29日

Top Level Design of Micro Turbine Jet Engine
HUANG Guo-ping,LI Bo,WEN Quan and LIANG De-wang.Top Level Design of Micro Turbine Jet Engine[J].Journal of Aerospace Power,2003,18(6):832-838.
Authors:HUANG Guo-ping  LI Bo  WEN Quan and LIANG De-wang
Institution:Nanjing University of Aeronautics and Astronautics,Nanjing210016,China;Nanjing University of Aeronautics and Astronautics,Nanjing210016,China;Nanjing University of Aeronautics and Astronautics,Nanjing210016,China;Nanjing University of Aeronautics and Astronautics,Nanjing210016,China
Abstract:The top-level design of micro turbine jet-engine is presented in the paper.Firstly,the relationship between dimensions and performance of micro turbine engine is analysed.Results show that micro turbine engines have potential larger ratio of thrust to weight than conventional engines.A preliminary design of a micro turbine engine is illustrated on the basis of the related technologies that can be achieved recently.Parametric analysis of performance,such as:thrust,specific fuel consumption,energy efficiency,exhaust gas temperature,was performed by changing one or two of 7 variables.In order to assess if the design of the micro turbine engine is capable of generating the reguired thrust when put into practice,a convenient criterion is formulated,and three designs of micro turbine engine are obtained for high,moderate and low performance.
Keywords:aerospace propulsion system  micro turbine engine  top level design  parametric analysis  ratio of thrust to weight  
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