涡扇发动机性能参数指标论证方法
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(1. 海军航空工程学院研究生管理大队,山东 烟台 264001;2.海军航空工程学院飞行器工程系,山东 烟台 264001;3. 91883部队,山西 长治 046000;4. 海军航空兵学院飞行理论系,辽宁 葫芦岛 125001)

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V235

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Index Parameters Demonstration Method Turbofan Engine Performence
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(1. Naval Aeronautical and Astronautical University, Graduate Students’ Brigade, Yantai Shandong 264001, China;2. Naval Aeronautical and Astronautical University, Department of Airborne Vehicle Engineering, Yantai Shandong 264001, China;3. The 91883rd Unit of PLA, Changzhi Shanxi 046000, China;4. Department of Flight Theory, Naval Aviation Academy, Huludao Liaoning 125001, China)

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    摘要:

    针对舰载战斗机用涡扇发动机在概念设计阶段,其总体性能和部件循环参数指标的选取与确定等难点问题进行了研究。通过分析舰载机的典型作战任务剖面,提出了发动机需要具备的性能要求;结合目前世界战斗机用涡扇发动机的发展趋势,给出了先进涡扇发动机性能与参数指标的范围;基于L-M算法神经网络模型,预测了涡扇发动机主要循环参数指标。经验证,预测的循环参数及提出的性能指标具有一定的有效性,为发动机概念设计时性能参数指标的选取与确定,提供了一种新的论证方法。

    Abstract:

    Aimed at the overall performance and cycle parameters of carrier-based fighter’s turbofan engine in the conceptual stage, a preliminary research was given. Some requirements for the overall performance of the engine were put forward after the analysis of the fighter typical mission profile. Combined with the present development trend of the military turbofan engine, the overall performance and main cycle parameters scopes of the advanced turbofan engine were presented. Based on the neural network of L-M algorithm, the main cycle parameters were predicted. The experimental results showed that the predicted cycle parameters and the suggested performance had a certain effectiveness. This method provided a feasible demonstration method for the choose of the performance and cycle parameters in the engine conceptual design.

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王团结,李本威,于复磊,李冬.涡扇发动机性能参数指标论证方法[J].海军航空大学学报,2014,29(6):511-516, 534
WANG Tuan-jie, LI Ben-wei, YU Fu-lei, LI Dong. Index Parameters Demonstration Method Turbofan Engine Performence[J]. JOURNAL OF NAVAL AVIATION UNIVERSITY,2014,29(6):511-516, 534

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  • 在线发布日期: 2015-04-08
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