Performance of Laminated Composite Turbomachinery Blades Using Finite Element Method with Delamination

被引：1

作者：

Makineni, Sai Mouli ^{[1
]}

Yalamachili, P. V. Satyanarayana ^{[1
]}

Prasanthi, P. Phani ^{[1
]}

Babu, K. Sivaji ^{[1
]}

Mounika, M. ^{[1
]}

机构：

[1] Prasad V Potluri Siddhartha Inst Technol, Dept Mech Engn, Vijayawada, Kanuru, India

来源：

ADVANCES IN MATERIALS AND MANUFACTURING ENGINEERING, ICAMME 2019 | 2020年

关键词：

Composite blades; Finite element method; Normal and shear stresses; ANSYS; FLUID-STRUCTURE INTERACTION; STABILITY; DESIGN; DAMAGE;

D O I：

10.1007/978-981-15-1307-7_2

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

The aim of the present study is to analyze the composite twisted blades with pre-existed cracks as these are the key parts in the power unit such as turbomachinery. The composite 16-layered twisted blade is analyzed by varying the twisting angle (theta), stacking sequence [0/90/90/0](2s,) [0/45/-45/0](2s), [0/60/-60/0](2s) and type of composite lamina (glass/epoxy, Kevlar/epoxy and carbon AS4/epoxy) in the laminate. The structural performance of the composite twisted blade with the presence of debond at the center of the composite laminate is explored with finite element method. The changes in the structural response of the composite blade in terms of deformations, and normal and shear stresses are evaluated. The FE models are validated with published results. The present work is used for the effective design of turbomachinery blades with pre-existed cracks.

引用

页码：17 / 28

页数：12

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