Analysis of Chosen Fuels Influence on Turboprop Engine Work Performance

Abstract

The analysis of work parameters of a turboprop engine fuelled by various fuels was done in the paper. The turboprop engine model was presented in the beginning. The main feature of this model is description of the flow in the engine as semi-perfect gas model. By the way, the change of fumes chemical composition influence the gas properties as heat constant and isentropic index are determined. Next energy balance of a compressor and turbine was analysed and turbine pressure drop was evaluated. Finally, engine output power was determined. It was done for selected fuels, which could be applied in the aero engines. The results of analyse were presented in the tables and charts and discussed. Summary of the test results with the results for contemporary applied fuel allows drawing the conclusions about the turboprop engine performance change by various fuel application. Main of them refers to the point that higher combustion heat value of fuel and higher heat constant of fumes cause better engine work conditions By this way the hydrogen seems to be perspective fuel of future, because its combustion heat value is three times JET A-1 and by this way it is possible the engine fuel consumption will be lower.

Performance analysis of turbofan engine with additional combustion chamber fueled by alternative fuel

“…The working gas was modeled using a semi-perfect gas model. Properties of the exhaust gases were modeled based on the reference [5]. The turbine cooling process was not taken into consideration.…”

“…1. The thermodynamic model was elaborate based on the equation describing the work of main engine components, based on the reference [4,5,9].…”

Single engine turboprop aeroplane class in small air transport

“…This example, having more powerful propulsion and flying faster justifies the modification, despite decreased range and increased fuel consumption as well. However, concerning other types of fuel would be a solution for this class (Jakubowski, 2016). The performance analysis of representative aeroplane that could be considered as LSET class showed they are characterised by similar cruise performance but much better climb profile compared to analogous SEP class aeroplanes.…”

“…This example, having more powerful propulsion and flying faster, justifies the modification, despite decreased range and increased fuel consumption as well. However, concerning other types of fuel would be a solution for this class (Jakubowski, 2016).…”