Abstract
Turbine blade thickness is limited by blockage and trailing edge losses, and are damaged due to high aerodynamic loadings. Safe turbine blade design needs a comprehensive knowledge of the exciting forces. This work investigates a mixed flow turbocharger turbine to study the effects of blade thickness distribution on the aero-structural performance. Three-dimensional flow field of the turbine was calculated using a CFD model in ANSYS CFX V.17. The blade structural responses are determined using an FEA model in ANSYS static structural module. Validation is performed by reference to experimental data carried out in Imperial College London on a dual turbocharger turbine. The results are presented to describe how and why the turbine aerodynamic and structural behavior varies with thickness under transonic conditions. On higher spans shock is more distributed to the passage but it has lower intensity. Thicker leading edge leads to more drop in Mach number through the bow shock. Higher distance of maximum thickness location from the leading edge caused the smaller separation bubble on the suction surface. DOI: http://dx.doi.org/10.5755/j01.mech.25.2.22151
Highlights
Loaded turbocharger turbine blades are damaged by alternating stresses resulting from the excitation forces due to inlet charge stroke and unsteady effects of the stator blade in vast operating points of different load and speed [1]
Chaochen et al [6] investigated the forced response mechanisms based on a fluid structure interaction (FSI) method
Near the trailing edge there is a weak shock which caused another drop in Mach number
Summary
Loaded turbocharger turbine blades are damaged by alternating stresses resulting from the excitation forces due to inlet charge stroke and unsteady effects of the stator blade in vast operating points of different load and speed [1]. Chaochen et al [6] investigated the forced response mechanisms based on a fluid structure interaction (FSI) method They found that the maximum dynamic stresses induced by the first two harmonic pressures both are located on the leading edges of the rotor blades. Dai et al [8] presented a coupled CFD-CSD method for aeroelastic analysis of HAWTs rotor blades and investigated the effects of yaw angle on aerodynamic performance of rotor blades and the effects of FSI on aerodynamic performance of rotor blades They found that maximum deflection and stress of rotor blades in yaw conditions increased. Root Mean Radius at Trailing Edge, mm Length of Axial Chord, mm Number of Blades Inlet cone angle Exit cone angle Number of nozzle blades Nozzle vane angle Total pressure ratio (Design point) Design rotor speed, rpm Nozzle throat diameter
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
