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A Design Feasibility Study of a Turbine Blade Disc Interface (Dovetail) Made By Four-Directional Braided Ceramic Matrix Composite (Sic/Sic)

A Design Feasibility Study of a Turbine Blade Disc Interface (Dovetail) Made By Four-Directional... The blade and disc's interface region (dovetail) is an integral part that plays an essential role in advanced flight machines. In this region, the major source of stress arising is the rotation of an engine shaft. Concerning this, geometry, material selection, and stress calculation need to perform at the predesign phase. This paper proposes four-directional braided ceramic matrix composites (CMCs) for the dovetail region because of its high transverse and shear strength, with less weight and thermal resistance. Due to the heterogeneous characteristics of proposed four-directional CMCs, homogenized mechanical properties are calculated for dovetail under non-isotropic conditions using multi-scale modeling and mechanics of structure genome method (MSG) for homogenization. After optimizing the dimensions for shape and minimizing the mass in the design study, the estimated homogenized mechanical properties are used to conduct a three-dimensional non-linear finite element (FE) analysis of the disc-dovetail assembly to check the feasibility of braided CMC’s dovetail over conventional dovetail. A comparative study between conventional and proposed dovetail material is made for the first time using the FE analysis results. Four-directional braided CMC (SiC/SiC) fits the blade disc interface region from a strength point of view because it shows less deformation, stress, and high stability than conventional Ti-alloy. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

A Design Feasibility Study of a Turbine Blade Disc Interface (Dovetail) Made By Four-Directional Braided Ceramic Matrix Composite (Sic/Sic)

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References (51)

Publisher
Springer Journals
Copyright
Copyright © The Korean Society for Aeronautical & Space Sciences 2021
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-021-00421-8
Publisher site
See Article on Publisher Site

Abstract

The blade and disc's interface region (dovetail) is an integral part that plays an essential role in advanced flight machines. In this region, the major source of stress arising is the rotation of an engine shaft. Concerning this, geometry, material selection, and stress calculation need to perform at the predesign phase. This paper proposes four-directional braided ceramic matrix composites (CMCs) for the dovetail region because of its high transverse and shear strength, with less weight and thermal resistance. Due to the heterogeneous characteristics of proposed four-directional CMCs, homogenized mechanical properties are calculated for dovetail under non-isotropic conditions using multi-scale modeling and mechanics of structure genome method (MSG) for homogenization. After optimizing the dimensions for shape and minimizing the mass in the design study, the estimated homogenized mechanical properties are used to conduct a three-dimensional non-linear finite element (FE) analysis of the disc-dovetail assembly to check the feasibility of braided CMC’s dovetail over conventional dovetail. A comparative study between conventional and proposed dovetail material is made for the first time using the FE analysis results. Four-directional braided CMC (SiC/SiC) fits the blade disc interface region from a strength point of view because it shows less deformation, stress, and high stability than conventional Ti-alloy.

Journal

International Journal of Aeronautical and Space Sciences – Springer Journals

Published: Feb 1, 2022

Keywords: Braided four-directional CMCs; Material properties; Blade and disc interface (Dovetail); Design study; Finite element analysis; Contact analysis; Stress behavior

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