Multi-disciplinary conceptual design of future jet engine systems

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Multi-disciplinary conceptual design of future jet engine systems ( multi-disciplinary-conceptual-design-future-jet-engine-syste )

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Konstantinos G. Kyprianidis System uncertainty due to thermo-fluid modelling Figure 4.9: Percentage deviation of total to static pressure ratio (left) and ve- locity (right) for values calculated for chemical equilibrium from no dissociation values. Figure 4.10: Percentage deviation of static temperature (left) and effective flow area (right) for values calculated for chemical equilibrium from no dissociation values. conditions, and nearly 4% for supersonic conditions. As Mach number increases in the supersonic range of values, dissociation effects become more and more sensitive to total temperature. The effects of dissociation in calculating the static temperature are also highly sensitive to total temperature and Mach number, as illustrated in Fig. 4.10. For high temperatures, the discrepancy can be as much as 5% for subsonic conditions, and well over 9% for supersonic conditions. It was concluded earlier in this work, that dissociation effects in evaluating caloric properties for relatively cold components (i.e. T ≤ 1500 [K]) can be negligibly small. It can easily be observed in the same figure that the uncertainty in estimating the effective flow area for cold components of gas turbines, such as bypass ducts and compressors, is also negligibly small; and it is certainly smaller than the uncertainty induced by ignoring real gas effects. The same conclusion however cannot be drawn for relatively hot components. The errors induced by ignoring dissociation effects during the calculation of the effective flow area of a military afterburner running at nearly stoichiometric conditions as well as the exit area of the con-di nozzle 95

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