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中文摘要: 当发动机在非设计点工作时，由于离心力和气动力的差异，风扇叶片的真实热态叶型将与设计状态的热态 叶型产生偏差。本文以某型民机大涵道比风扇叶片为基础，针对换算工况与物理工况的热态叶型形变偏差，以及部 分转速与设计转速热态叶型的形变偏差，分析两种偏差下热态叶型的变化，并对形变带来的特性和流场变化开展数 值模拟分析，量化形变对风扇叶片性能的影响，进而为风扇叶片数值分析结果的修正提供了依据。
Abstract:When the actual operating state of the engine deviates from the design state，due to the difference of centrifugal force and
aerodynamic force，the fan's true hot blade profile will deviate from the designed hot blade profile. Accordingly， based on the fan
blades of a civil turbofan engine with high bypass ratio，this article analyzes the hot blade profile differences between the corrected operating conditions and the physical operating conditions，as well as the deviations of the hot blade profile at partial rotating speeds from the designed rotating speed. In addition，the numerical simulation analysis of the characteristic changes caused by the deviation is
carried out to quantify the influence of tlie deviation on the performance of the fan blade，and then provide basis for the correction of the numerical simulation result of the fan blades.
文章编号： 中图分类号：TK472 文献标志码：
基金项目:
| Author Name | Affiliation |
| Yang Xiaohe | AECC Commercial Aircraft Engine Co.，Ltd.， |
| Cao Bo | AECC Commercial Aircraft Engine Co.，Ltd.， |
| Liu Shiwen | AECC Commercial Aircraft Engine Co.，Ltd.， |
引用文本：
作者.题名[J].刊名,出版年份,卷号(期号):起止页码.
[2]KIM K M, PARK J S, DONG H L, et al. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages[J]. Engineering Failure Analysis, 2011, 18(4):1212-1222.
作者.题名[J].刊名,出版年份,卷号(期号):起止页码.
[2]KIM K M, PARK J S, DONG H L, et al. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages[J]. Engineering Failure Analysis, 2011, 18(4):1212-1222.