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System uncertainty due to thermo-fluid modelling Konstantinos G. Kyprianidis fast local chilling of reactions – for example due to contact with the cooling air – will result in full chemical equilibrium not being reached in the combustor and dissociated species still being present in the final mixture in the turbine outlet (i.e. frozen composition). It can therefore be concluded that even when full chemical equilibrium is assumed, there is still significant thermo-fluid modelling induced uncertainty in the performance calculations; determining the level of this uncertainty experimentally for a particular engine design is not a trivial task, if possible at all. 4.8 Uncertainty at engine system level In this section, an attempt was made to study how the choice of the fluid model affects engine design point performance calculations. For the purpose of this work, various technical models were used - utilising the flexibility of the devel- oped fluid component for TERA2020. All engine technology parameters were kept constant including component efficiencies, pressure losses and maximum permissible T4 levels. The differences encountered in the engine performance predictions are discussed. If dissociation effects are ignored, variability in the calculated values of corrected mass flow, total pressure and total temperature throughout the gas path is con- fined to 1%, 1.3%, and 2 [K] band, respectively. This is illustrated in Fig. 4.13 and Fig. 4.14. If dissociation effects are taken into account then the calculated values of corrected mass flow, total pressure and total temperature can vary from the “no dissociation” values as much as 3%, 4%, and 12 [K], respectively. These large deviations originate mainly from the performance calculations in the high pressure turbine and should not be ignored. They can be attributed to the differ- ent working medium composition (and hence, different caloric properties) when dissociation effects are taken into account. For major performance parameters the induced uncertainty from the various technical models is 0.3% and is of the same order of magnitude as with the uncertainty in the calculation of isobaric heat capacity presented earlier in this chapter. An exception to this is the hot nozzle effective area which can vary by as much as 1%, as illustrated in Fig. 4.14. If dissociation effects are taken into account then the calculated values of fuel mass flow and net thrust can vary by 98PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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