Open AccessNumerical Simulation of Cascade Flow: Vortex Element Method for Inviscid Flow Analysis and Axial Turbine Blade Design
Author(s) -
o Suprayetno,
Priyono Sutikno,
Nathanael P. Tandian,
Firman Hartono
Publication year - 2021
Publication title -
journal of advanced research in fluid mechanics and thermal sciences
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.247
H-Index - 13
ISSN - 2289-7879
DOI - 10.37934/arfmts.85.2.1423
Subject(s) - turbine , airfoil , turbine blade , inviscid flow , vortex , cascade , lift coefficient , wells turbine , rotor (electric) , blade element momentum theory , blade (archaeology) , structural engineering , flow (mathematics) , lift (data mining) , camber (aerodynamics) , axial compressor , mechanics , mechanical engineering , engineering , aerospace engineering , turbulence , physics , computer science , reynolds number , chemical engineering , gas compressor , data mining
This study aims to design an axial turbine rotor blade and predict the turbine performance at preliminary design stage. Quasi three dimensional method was applied to design including blade to blade flow analysis. The blade profile uses a NACA 0015 airfoil by varying the profile thickness from hub to tip. The profile is divided into eleven segments which has different parameters. The profile was analysed using blade to blade flow/cascade flow analysis called vortex panel method to obtain lift coefficient. The analysis of cascade flow was performed in potential flow and prediction of turbine perfomance is carried out involving common best practice to give drag effect on the blade. The design of the turbine was applied on three different rotors, which also have a different discharge, head, and design rotation. The outer diameter of turbine 1 is 0.65 m, while turbine 2 and turbine 3 have an outer diameter of 0,60 m. The calculation result show that the efficiency of turbines 1, 2, and 3 were 88,32%, 89,67%, and 89,04%, respectively.