Non-preloaded bolted ring flange connections subjected to static loads

Stamatopoulos, G.

doi:10.1007/s13296-014-2006-0

Cited by 8 publications

(2 citation statements)

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“…Stamatopoulos [14] studied behavior of the circular bolted flange connections under static compressive and tensile loads, using a segment model of the structure. The methodology used in the study is based on the failure pattern classifications.…”

Section: Couchaux Et Al Investigated a Theoretical Model For The Bolmentioning

confidence: 99%

Development of Artificial Neural Network Based Design Tool for Aircraft Engine Bolted Flange Connection Subject to Combined Axial and Moment Load

Sanli

Gürses

Çöker

et al. 2017

Volume 1: Advances in Aerospace Technology

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iv I hereby declare that all information in this document has been obtained and presented in accordance with academic rules and ethical conduct. I also declare that, as required by these rules and conduct, I have fully cited and referenced all material and results that are not original to this work. Name, Last name : Tahir Volkan SanlıSignature : v ABSTRACT DEVELOPMENT In this thesis, a design tool using artificial neural network (ANN) is developed for the bolted flange connections, which enables the user to analyze typical aircraft engine connections subjected to combined axial and bending moment in a fast yet very accurate way. The neural network trained for the design tool uses the database generated by numerous finite element analyses for different combinations of parametric design variables of the bolted flange connection. The defined parameters are the number of bolts, the bolt size, the shaft thickness, the flange thickness, the pretension load acting on the bolt and the combined external axial force and bending moment. The outputs gathered from total 12000 FE analyses are the bolt reaction force and the average flange stress, which are collected to be used as database for the ANN training process together with the input design parameters. The results of the trained ANN are then compared with the FEA results. The comparison proves that the neural network shows great compliance with the non-linear FEA within the range of design parameters. As the last step, a graphical user interface is developed to turn the neural network into a user-friendly bolted flange design tool. It is believed that the developed design tool can replace the non-linear finite element analysis and be vi used very effectively in an optimization framework for the weight minimization of cylindrical bolted flange connections of aircraft engines.

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Section: Couchaux Et Al Investigated a Theoretical Model For The Bolmentioning

confidence: 99%

Development of Artificial Neural Network Based Design Tool for Aircraft Engine Bolted Flange Connection Subject to Combined Axial and Moment Load

Sanli

Gürses

Çöker

et al. 2017

Volume 1: Advances in Aerospace Technology

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“…In bolted circular flange connections subjected to bending moment and axial force (see Figure 1-a), the compressive stiffness of L-stubs in contact with a rigid foundation [3] have been determined. This L-stub model is derived from the simplified contact pressure distribution proposed by Stamatopoulos & Ermopoulos [4]. For double web angle connection subjected to a bending moment, the position of the centre of rotation depends on the stiffness of the compressive component (see Figure 1-b).…”

Section: Introductionmentioning

confidence: 99%

Stiffness of L‐stubs loaded in compression

SAROU,

COUCHAUX,

HJIAJ

et al. 2023

ce papers

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The stiffness of T‐stubs in compression is generally assumed infinite except for column base plates. For bolted circular flange connections and double web angle connections, the stiffness of L‐stubs and T‐stubs in compression should be determined to accurately calculate the position of the center of compression. Simple expressions have been recently proposed for these components in contact with a rigid foundation. However, the end‐plate can be in contact with a flexible foundation.The objective of the present paper is to propose simple expressions of the compressive stiffness of L‐stubs in contact with rigid or flexible foundations. A refined beam model resting on Winkler foundations is derived and applied to the L‐stub model. To facilitate the practice of engineering, simplifications are proposed for the contact pressure distribution and the compressive stiffness. The analytical results are then compared against finite element calculations performed with ANSYS APDL

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