Fatigue of Aircraft Structures最新文献

Development of Diffraction Research Methodologies for Mediloy S-CO Alloy Speciments Made Using LPBF Additive Manufacturing 针对使用 LPBF 快速成型技术制造的 Mediloy S-CO 合金试样开发衍射研究方法

Fatigue of Aircraft Structures Pub Date : 2024-05-13 DOI: 10.2478/fas-2023-0006

Elżbieta Gadalińska, Maciej Malicki, Anna Trykowska, G. Moneta

{"title":"Development of Diffraction Research Methodologies for Mediloy S-CO Alloy Speciments Made Using LPBF Additive Manufacturing","authors":"Elżbieta Gadalińska, Maciej Malicki, Anna Trykowska, G. Moneta","doi":"10.2478/fas-2023-0006","DOIUrl":"https://doi.org/10.2478/fas-2023-0006","url":null,"abstract":"\u0000 This study focuses on the application and improvement of diffraction measurement methodologies for the optimization of manufacturing parameters of CoCr alloy components made by additive manufacturing (AM) – particularly for Mediloy S-Co alloy specimens made using Laser Powder Bed Fusion (LPBF) additive manufacturing. We measured the phase composition of specimens obtained in AM processes, the measurement of residual stresses resulting from the manufacture of these printed parts, as well as the effectiveness of stress relaxation through the use of heat treatments dedicated to this type of material. Findings reveal several insights into how printing strategies affect the porosity and residual stresses in additive manufacturing. Specimens with higher porosity, particularly those created using specific strategies that resulted in lower energy densities, exhibited lower residual stresses. Notably, printing direction and energy density were found to significantly affect the mechanical stresses within the specimens, with directional choices playing a critical role in the final properties of the parts. Additionally, our findings underscore the complex relationship between various printing parameters and the development of mechanical stresses, highlighting the impact of adjustments in printing strategy on the properties of printed components.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-05-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140984602","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Insight into Damping Sources in Turbines 对汽轮机阻尼源的深入了解

Fatigue of Aircraft Structures Pub Date : 2023-06-05 DOI: 10.2478/fas-2022-0006

G. Moneta

引用次数: 0

Checking the Correctness of the Process of Brazing of the Honeycomb Seal to the Base by Ultrasonic Method 用超声波法检验蜂窝密封件与底座钎焊工艺的正确性

Fatigue of Aircraft Structures Pub Date : 2023-04-20 DOI: 10.2478/fas-2022-0005

Agata Świerek, J. Krysztofik, Wojciech Matczak, A. Niepokólczycki

{"title":"Checking the Correctness of the Process of Brazing of the Honeycomb Seal to the Base by Ultrasonic Method","authors":"Agata Świerek, J. Krysztofik, Wojciech Matczak, A. Niepokólczycki","doi":"10.2478/fas-2022-0005","DOIUrl":"https://doi.org/10.2478/fas-2022-0005","url":null,"abstract":"Abstract This work is focused on the checking of the correctness of the brazing process of honeycomb seals to stationary elements of aircraft turbine engines. It describes this process, paying attention to the aspects that have a fundamental impact on whether the seal will be brazed to the base as required, or whether unacceptable areas of non-brazing will appear. The aim of the study was to check the possibility of using the ultrasonic method to check the correctness of the brazing process of honeycomb seals and to compare the tests carried out using this method with the mostly used visual tests. The research carried out as part of the work showed very well that there are reasons to use the ultrasonic defectoscopy method to test the correctness of the brazing process of honeycomb seals in the elements of aircraft engines. This method also makes it possible to automate the checking process, fully document it and objectively assess the correctness of the connection. The results obtained in the study provide a very good starting point for further research, the aim of which will be to implement the ultrasonic defectoscopy method for testing the correctness of brazing honeycomb seals into practice in industrial conditions.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-04-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43049673","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Prediction of Fatigue Cracks Using Gamma Function 利用伽玛函数预测疲劳裂纹

Fatigue of Aircraft Structures Pub Date : 2023-04-20 DOI: 10.2478/fas-2022-0004

Abdelfetah Moussouni, M. Benachour, N. Benachour

引用次数: 0

Sensitivity Analysis of the Nasgro Equation Based on the PZL-130 TC-II Orlik Trainer Aircraft Full Scale Fatigue Test 基于PZL-130 TC-II Orlik教练机全尺寸疲劳试验的Nasgro方程灵敏度分析

Fatigue of Aircraft Structures Pub Date : 2023-02-13 DOI: 10.2478/fas-2022-0002

P. Reymer, A. Leski, M. Kurdelski

引用次数: 0

The Influence of Material Configuration of Fibre-Metal Laminates with Alumina Core on Flexural Strength 氧化铝芯纤维金属层压板材料结构对抗弯强度的影响

Fatigue of Aircraft Structures Pub Date : 2023-02-13 DOI: 10.2478/fas-2022-0003

Mariusz Frankiewicz, M. Karoluk, R. Dziedzic, Tristan Timmel, P. Scholz

{"title":"The Influence of Material Configuration of Fibre-Metal Laminates with Alumina Core on Flexural Strength","authors":"Mariusz Frankiewicz, M. Karoluk, R. Dziedzic, Tristan Timmel, P. Scholz","doi":"10.2478/fas-2022-0003","DOIUrl":"https://doi.org/10.2478/fas-2022-0003","url":null,"abstract":"Abstract Fibre metal laminates (FMLs) consisting of layers made of PA6 polyamide prepregs reinforced with glass and carbon fibres and an aluminium alloy core are the new variant of the other types used by aerospace FML materials such as GLARE or CARALL. By using a thermoplastic matrix, they can be shaped by stamping processes, which allows for a more efficient production process than classical laminating methods such as vacuum bagging. In addition to the improved impact energy absorption efficiency, the metallic core can be utilised to effectively bond the composite part to adjacent metallic structures. This article presents the influence of the material configuration of fibre-metal laminates consisting of continuous fibre-reinforced thermoplastic outer layers integrated with a layer of metallic aluminium alloy inserts—a number of layers, type and direction of reinforcing fibres—on the static and fatigue flexural properties. In this study, eight laminate configurations were prepared using a one-step variothermal consolidation process. The results showed that in the three-point flexural fatigue test, the samples exceeded 106 cycles at stresses <30% of the static bending strength. Laminates with predominantly longitudinally reinforced layers showed the highest fatigue strength among the FML samples analysed. The type of reinforcing fibres and the number of layers were less affected on the analysed mechanical properties.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45690967","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Effect of Strain Range and Hold Time on High Temperature Fatigue Life of G17CrMoV5-10 Cast Alloy Steel 应变范围和保温时间对G17CrMoV5-10铸合金钢高温疲劳寿命的影响

Fatigue of Aircraft Structures Pub Date : 2023-02-13 DOI: 10.2478/fas-2022-0001

Anna Polnik, H. Matysiak, Sławomir Czarnewicz, Z. Pakieła

引用次数: 0

Detection of Sub-Surface Defects in Semi-Finished Products from Aluminum Alloys by the Eddy Current Method 用涡流法检测铝合金半成品亚表面缺陷

Fatigue of Aircraft Structures Pub Date : 2021-12-01 DOI: 10.2478/fas-2021-0004

J. Krysztofik, Maciej Malicki

引用次数: 0

A FCG Model and the Graphical User Interface Under Matlab for Predicting Fatigue Life: Parametric Studies 基于Matlab的疲劳寿命预测的FCG模型和图形用户界面:参数化研究

Fatigue of Aircraft Structures Pub Date : 2021-12-01 DOI: 10.2478/fas-2021-0011

Tayeb Kebir, J. Correia, M. Benguediab, A. Imad

引用次数: 0

Application of Laboratory Diffraction Methods in Characterization of Elements Made By Additive SLM Methods – State of the Art 实验室衍射方法在添加剂SLM方法制备的元素表征中的应用——最新技术

Fatigue of Aircraft Structures Pub Date : 2021-12-01 DOI: 10.2478/fas-2021-0007

Elżbieta Gadalińska, Łukasz Pawliszak, G. Moneta

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引用次数: 1