某型大涵道比涡扇发动机飞行推力确定方法研究 |
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引用本文: | 高扬,王朝蓬,屈霁云,寿圣德.某型大涵道比涡扇发动机飞行推力确定方法研究[J].航空发动机,2011,37(3):47-49. |
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作者姓名: | 高扬 王朝蓬 屈霁云 寿圣德 |
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作者单位: | 中航工业飞行试验研究院,西安,710089 |
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摘 要: | 以某型大涵道比涡扇发动机为研究对象,结合动力装置适航取证"飞行推力确定"试验科目,对该型发动机飞行推力确定方法进行了分析,并开发了该型发动机飞行推力确定计算分析软件。结合发动机设计单位给出的设计值,对该计算方法进行了验证。结果表明,采用飞行推力确定计算方法得到的计算值与设计值间吻合程度较高。
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关 键 词: | 飞行推力确定 大涵道比涡扇发动机 性能 飞行试验 |
Study of In-flight Thrust Determination Method for a High Bypass Turbofan Engine |
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Authors: | GAO Yang WANG Zhao-peng QU Ji-yun SHOU Sheng-de |
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Institution: | GAO Yang,WANG Zhao-peng,QU Ji-yun,SHOU Sheng-de(AVIC Flight Test Establishment,Xi'an 710089,China) |
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Abstract: | The in-flight thrust determination method of a high bypass-ratio turbofan engine was analyzed by combining with the power plant airworthiness In-Flight Thrust Determination flight test item,and the analysis software of the engine in-flight thrust determination was developed.Combined with design value provided by engine company,the calculation method was verified.The results show that the calculation data and design data is highly closed. |
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Keywords: | in-flight thrust determination high bypass ratio turbofan engine performance flight test |
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