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Konstantinos G. Kyprianidis System uncertainty due to thermo-fluid modelling in this chart: • It is only within a small region of low temperatures and high pressures (upper left corner) that the discrepancies are seriously high. The ideal gas law holds well for aero engines currently in service. • For an intercooled cycle with a high OPR the discrepancies cannot be ignored for rigorous performance calculations. • Increasing OPR - which is the current technological trend in aero engine design - diminishes the validity of the ideal gas assumption. • Increasing the compression polytropic efficiency - which is the current tech- nological trend in component design - diminishes the validity of the ideal gas assumption. • An increase in intercooler hot stream temperature drop (i.e. effectiveness) will diminish the validity of the ideal gas assumption. This is especially true at lower IPC pressure ratios if an intercooled turbofan design is considered. • If the ideal isothermal compression process is to be considered - perhaps within a novel cycle assessment - then the ideal gas assumption will not hold and significant calculation errors will be induced. Finally, if dissociation effects are considered, the errors induced by assuming an ideal gas instead of a real gas are still negligible for turbine calculations since expansion is done at generally high temperatures. It can be concluded that real gas behavior is not negligible at high pressures and low temperatures and particularly when approaching the condensation point of water. 4.11 Conclusion The research effort presented in this chapter mainly focused on a comprehensive analysis of typical thermo-fluid modelling for gas turbine performance codes and the potential induced uncertainty in the calculations. The fluid model devel- oped for the engine performance module of TERA2020 was described and the assumptions made and the uncertainties induced were examined. Several anal- yses, which demonstrate the effects of composition, temperature and pressure 103PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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