Modified Three-Parameter Model to Predict Compressor Blade Fatigue Life under Vibration Loading

Zhang Yakui; Guo Shuxiang; Zhang Zhongping; Shang Bolin

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Modified Three-Parameter Model to Predict Compressor Blade Fatigue Life under Vibration Loading

机译：修改的三参数模型预测压缩机叶片疲劳寿命下的振动载荷

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This paper investigates steel alloy stator blade flexural vibration characteristics and fatigue properties analytically using flexural fatigue tests. First, fatigue life data reliability is analyzed and theoretical strain endurance limit Delta epsilon(C) deficiencies are assessed. A model from the literature is used to predict fatigue life using fatigue test data for four steel alloys to derive an extended estimation expression for the strain endurance limit. The proposed three-parameter fatigue life models can be applied to estimate steel alloy blade fatigue life in practical working environments. (c) 2019 American Society of Civil Engineers.

机译：本文通过抗弯疲劳试验调查了分析钢合金定子叶片弯曲振动特性和疲劳性能。首先，分析了疲劳寿命数据可靠性，评估理论应变耐久性限制δε（c）缺陷。来自文献的模型用于预测使用四钢合金的疲劳试验数据来预测疲劳寿命，从而导出应变耐久极限的延长估计表达。所提出的三参数疲劳寿命模型可用于估算实际工作环境中的钢合金叶片疲劳寿命。（c）2019年美国土木工程学会。

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来源
《Journal of aerospace engineering》 |2019年第4期|04019034.1-04019034.12|共12页
作者
Zhang Yakui; Guo Shuxiang; Zhang Zhongping; Shang Bolin;
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作者单位

Air Force Engn Univ Aeronaut & Astronaut Sci & Technol Sch Xian 710038 Shaanxi Peoples R China;

Air Force Engn Univ Aeronaut & Astronaut Sci & Technol Sch Xian 710038 Shaanxi Peoples R China;

Air Force Engn Univ Aeronaut & Astronaut Sci & Technol Sch Xian 710038 Shaanxi Peoples R China;

Northwestern Polytech Univ Aeronaut & Astronaut Sci & Technol Sch Aeronaut Xian 710072 Shaanxi Peoples R China;

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原文格式 PDF
正文语种 eng
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关键词
Life estimation; Vibration fatigue; Fatigue reliability; Three-parameter model; Theoretical strain endurance limit;

机译：寿命估算;振动疲劳;疲劳可靠性;三参数模型;理论应变耐力极限;

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专利

1. Modified Three-Parameter Model to Predict Compressor Blade Fatigue Life under Vibration Loading [J] . Zhang Yakui, Guo Shuxiang, Zhang Zhongping, Journal of aerospace engineering . 2019,第4期

机译：修正的三参数模型预测振动载荷下的压气机叶片疲劳寿命
2. A Three-Parameter Model for Predicting Fatigue Life of Ductile Metals Under Constant Amplitude Multiaxial Loading [J] . Jia Liu, Jing Li, Zhong-ping Zhang Journal of Materials Engineering and Performance . 2013,第4期

机译：恒振幅多轴载荷下预测球墨金属疲劳寿命的三参数模型
3. Dynamic and fatigue compressor blade characteristics during fluid-structure interaction: Part I-Blade modelling and vibration analysis [J] . Kou Hai-jun, Lin Jian-sheng, Zhang Jun-hong, Engineering failure analysis . 2017,第期

机译：流体结构相互作用期间动态和疲劳压缩机叶片特性：第一部分I叶片建模与振动分析
4. An Equivalent and Accelerated Life Test Method for Compressor Blades under Combined Loads Based on Equal Fatigue Life [C] . Shouqing Huang, Zemin Yao, Yong’en Du, International Conference on Prognostics and System Health Management . 2020

机译：基于平等疲劳寿命的组合负载下压缩机叶片的等效和加速寿命试验方法
5. The development of a phase locked wind turbine blade finite element model to predict loads and deflections during fatigue testing. [D] . Freeman, Kyle Andrew. 2010

机译：开发了用于预测疲劳测试过程中的载荷和挠度的锁相风轮机叶片有限元模型。
6. Assessment of the Impact of Shot-Peening on the Fatigue Life of a Compressor Blade Subjected to Resonance Vibrations [O] . Arkadiusz Bednarz, Wojciech Z. Misiolek 2020

机译：评估射击喷丸对压缩机叶片疲劳寿命的影响经受共振振动
7. Influence of the Amplitude of Resonance Vibrations on Fatigue Life of a Compressor Blade with Simulated FOD Damage [O] . Arkadiusz Bednarz 2020

机译：共振振动幅度对压缩机叶片疲劳寿命的影响
8. Space Shuttle Main Engine Powerhead Structural Modeling, Stress and Fatigue Life Analysis. Volume 3: Stress Summay of Blades and Nozzles at FPL and 115 Percent RPL Loads. SSME HPFTP and HPOTP Blades and Nozzles [R] . Hammett, J. C., Hayes, C. H., Price, J. M., 1983

机译：航天飞机主机动力头结构建模，应力和疲劳寿命分析。第3卷：FpL刀片和喷嘴的应力总和以及115％的RpL载荷。 ssmE HpFTp和HpOTp刀片和喷嘴

Modified Three-Parameter Model to Predict Compressor Blade Fatigue Life under Vibration Loading

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