Material Optimizations on UAV’s axial flow compressor blade by using FSI Approach

Abstract

Small Gas Turbine (SGT) Engine has become a modern technology in Unmanned Aerial Vehicles (UAVs). The focus of this study is on the SGT compressor, more specifically, the axial flow compressor blades. In this study, the structural analysis of an axial flow compressor blade in a Small Gas Turbine Engine for UAV is investigated. The conceptional design of compressor blade is completed using CATIA, in which the fundamental information about the design blades is obtained from liter survey [1]. Firstly, the Computational Fluid Dynamic (CFD) analyses are completed over the blade of the axial flow compressor, which has been fit for UAVs. The aerodynamic pressure and velocity distributions over the compressor blade are captured and that has been as input to FSI simulation. Using Fluid Structure Interaction (FSI) approach, the structural integrity of the compressor blade with different composite materials is analyzed and compared. Structural analysis has been done for different materials such as Aluminum Alloy, Epoxy based Carbon Fiber Reinforced Polymer (CFRP), and Epoxy based Glass Fiber Reinforced Polymer (GFRP). The outcomes of this analysis form a strong base for further development of axial flow compressor with alternative materials.