Customised application of exergy analysis method to PW120A turboprop engine for performance evaluation

Abstract

In this paper, first and second laws of thermodynamics are applied on a turboprop engine of a regional aircraft. Performance parameters of the engine are assessed under take-off conditions and maximum power settings. Energy and exergy rates, exergy destruction rate, improvement potential, fuel depletion rate and productivity rate are proven by using component-based analysis method. Exergy destruction rates are found to be 337.12 kW, 1461.87 kW, 69.74 kW and 269.22 kW in order of air compressor, combustion chamber, gas turbine and free turbine. In addition, exergy efficiencies of the air compressor, combustion chamber, gas turbine and free turbine are calculated to be 86.95%, 82.16%, 97.86% and 85.52%, respectively, whilst energy and exergy efficiencies of the engine are found to be with the values of 27.89% and 26.74%. Obtained results from this study can be useful to improve performance of a turboprop engine still in service.