PERFORMANCE, CHARACTERIZATION AND EVALUATION OF AXIAL FLOW TURBINE ENGINE

Abstract

This research paper mainly focuses on the performance, characterization and evaluation of the axial flow gas turbine engine used for aircraft applications.  Attempt from previous researches were to increase the efficiency and work output of the turbine. To achieve further improvement in the efficiency, the turbine blades were subjected to a higher temperature. With the knowledge from material science and engineering, suitable materials were selected for the design of suitable blades that can withstand higher temperature without failure. To achieve the efficient performance of the turbine, the hot gases from the combustor, are to be directed at a suitable angle at the entry to the turbine as well as exit from the turbine. This research work thoroughly focuses on how the blade configuration are designed to achieve the desired output. Development of the axial flow gas turbine was hindered by the need to obtain both a high-enough flow rate and compression ratio from a compressor to maintain the air requirement for the combustion process and subsequent expansion of the exhaust gases. Design specifications were given, to provide a detailed understanding of axial flow turbine design. Values obtained were used to produce a graph that explained how turbine parameters vary.