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轴流压气机流道设计方法研究

Investigation on Axial Compressor Flow Path Design Methods
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摘要 在航空发动机研制过程中,当选定发动机设计状态并确定出热力循环参数后,就可以通过1维流道尺寸设计来预估发动机尺寸和质量。以轴流压气机为对象,研究了1种新的轴流压气机流道设计方法,并开发了相应的计算机程序(CEFP)。该方法采用"1维平均中径法",基于流量连续方程,通过确定压气机各级中径处的气流参数,迭代计算出压气机各级进、出口截面的内外径尺寸及轴向位置,从而确定整台压气机的流道。使用编制的计算机程序对GE公司的E3发动机10级高压压气机进行了模拟计算,其计算结果与原始尺寸数据对比最大误差不超过8%,足以验证该方法的工程实用价值。 In the engine design process, the size and weight of engine were estimated by one-dimensional flow path dimension design after selected the design conditions and thermodynamic cycle parameters. A new method to design axial compressor flow path was stduied and the computer program (CEFP) was developed. The method named "one-dimensional mean line design" which was based on flow conservation rule, only considers the pitch line flow parameters of each stage. It was an iterative process to calculate each stage tip and hub radius as well as axial position,and then the whole flow path is defined. Finally, the 10 stage high pressure compressors of E3 engine in GE were simulated by computer program. The maximum error between the calculation result and original dimensional data is less than 8%, it is enough to verify the engineering value of the method.
出处 《航空发动机》 2015年第5期53-57,共5页 Aeroengine
关键词 流道设计 轴流压气机 平均中径 航空发动机 flow path design axial compressor mean line aeroengine
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