Methodology Design of an Axial Flow Turbine
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Date
2025
Journal Title
Journal ISSN
Volume Title
Publisher
National Higher School of Technology and Engineering-Annaba
Abstract
The main components of a turboprop engine are the compressor, the combustion gas chambers, and the axial flow turbine for the high-temperature gases exciting the chambers. The present work focuses on the methodology followed to a complete design of an axial flow turbine and the impelmentation of the algorithm written in a code to perform the calculations. to reach this complete design: First of all, a workflow was defined starting by reading and understanding the turbine input and output parameters, defining the optimal number of stages necesssary for the turbine. Secondly the velocity triangles were calculated to obtain a 50 % stage reaction, a methodology was implemented to reach the maximum possible to the 50 % reaction and got close to 10−4 to this value. We also verify the values of Mach Numbers and ensure that the calculated velocity triangle keeps the turbine in a subsonic state at the blade edges. Geometrical construction was also made by defining the blade heights and therefore the hub and shroud radii. Finally, we implemented a methodology to create blade profiles based on the camber-line with respect to the flow field. The turboprop designed has three stages in total, 6 rows of stators and rotor.