DEVELOPMENT OF ARTIFICIAL NEURAL NETWORK BASED DESIGN TOOL FOR AIRCRAFT ENGINE BOLTED FLANGE CONNECTION SUBJECT TO COMBINED AXIAL AND MOMENT LOAD

Date

2017-11-09

Author

Sanli, T. Volkan
Gürses, Ercan
Çöker, Demirkan
Kayran, Altan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

75
views

0
downloads

Bolted flange connections are one of the most commonly used joint types in aircraft structures. Typically, bolted flange connections are used in aircraft engines. The main duty of a bolted flange connection in an aircraft engine is to serve as the load transfer interface from one part of the engine to the other part of the engine. In aircraft structures, weight is a very critical parameter which has to be minimized while having the required margin of safety for the structural integrity. Therefore, optimum design of the bolted flange connection is crucial to minimize the weight. In the preliminary design stage of the bolted flange connection, many repetitive analyses have to be made in order to decide on the optimum design parameters of the bolted flange connection. Two main methods used for analyzing bolted flange connections are the hand calculations based on simplified approaches and finite element analysis (FEA). While hand calculations lack achieving optimum weight as they tend to give over safe results, finite element analysis is computationally expensive because of the non-linear feature of the problem due to contact definitions between the mating parts.

URI

https://hdl.handle.net/11511/55594

Conference Name

ASME International Mechanical Engineering Congress and Exposition

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Development of bolted flange design tool based on finite element analysis and artificial neural network Yıldırım, Alper; Kayran, Altan; Department of Aerospace Engineering (2015) In bolted flange connections, commonly utilized in aircraft engine designs, structural integrity and minimization of the weight are achieved by the optimum combination of the design parameters utilizing the outcome of many structural analyses. Bolt size, number of bolts, bolt locations, casing thickness, flange thickness, bolt preload, and axial external force are some of the critical design parameters in bolted flange connections. Theoretical analysis and finite element analysis (FEA) are two main approach...
DEVELOPMENT OF BOLTED FLANGE DESIGN TOOL BASED ON FINITE ELEMENT ANALYSIS AND ARTIFICIAL NEURAL NETWORK Yildirim, Alper; Kayran, Altan; Gulasik, Hasan; Çöker, Demirkan; Gürses, Ercan (2015-11-19) In bolted flange connections, commonly utilized in aircraft engine designs, structural integrity and minimization of the weight are achieved by the optimum combination of the design parameters utilizing the outcome of Many structural analyses. Bolt size, the number of bolts, bolt locations, casing thickness, flange thickness, bolt preload, and axial external force are some of the critical design parameters in bolted flange connections. Theoretical analysis and finite element analysis (FEA) are two main appr...
Development of structural optimization and neural network design tool for buckling behaviour of skin stringer structures under combined compression and shear loading Okul, Aydın; Gürses, Ercan; Department of Aerospace Engineering (2019) Stiffened panels are commonly used in aircraft structures in order to resist high compression and shear forces with minimum total weight. Minimization of the weight is obtained by combining the optimum design parameters. The skin panel dimensions, the stringer spacing and the stringer dimensions are some of the critical parameters which affect the global buckling behaviour of the stiffened panel. The aim of this thesis is to develop a neural network design tool and to carry out a geometric optimization for ...
Development of Structural Neural Network Design Tool for Buckling Behaviour of Skin-Stringer Structures Under Combined Compression and Shear Loading Okul, Aydın; Gürses, Ercan (2018-11-15) Stiffened panels are commonly used in aircraft structures in order to resist high compression and shear forces with minimum total weight. Minimization of the weight is obtained by combining the optimum design parameters. The panel length, the stringer spacing, the skin thickness, the stringer section type and the stringer dimensions are some of the critical parameters which affect the global buckling allowable of the stiffened panel. The aim of this study is to develop a design tool and carry out a geometri...
Investigation of fretting fatigue failure mechanism of lug-bush connection members Özen, Emine Burçin; Çöker, Demirkan (Elsevier BV; 2019-01-01) Lug-bush connection members are widely used in aerospace industry, specifically in the connection of rotor to helicopter main body. Under small amplitude cyclic loadings, a fraction of the contact area experiences relative motion which causes fretting on the contacting surfaces. In this study, failure mechanisms of four different lug-bush members subjected to high cycle tensile fatigue loading are investigated. The contact surfaces are inspected using a digital microscope and a scanning electron microscope ...

Citation Formats

T. V. Sanli, E. Gürses, D. Çöker, and A. Kayran, “DEVELOPMENT OF ARTIFICIAL NEURAL NETWORK BASED DESIGN TOOL FOR AIRCRAFT ENGINE BOLTED FLANGE CONNECTION SUBJECT TO COMBINED AXIAL AND MOMENT LOAD,” presented at the ASME International Mechanical Engineering Congress and Exposition, Tampa, FL, 2017, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/55594.