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Conclusion Konstantinos G. Kyprianidis European collaborative projects VITAL and NEWAC. It is recognized that such correlations have a limited range of validity and are dependent on supporting engineering science base. As an appropriate design space is defined, a more rig- orous iterative design procedure would typically be set involving a large number of company specialists. The major findings of the presented research effort are: • The tool developed can assist in the transition from the traditional, human- based aero engine conceptual design procedure to a partially-automated process. The explicit algorithm proposed minimises internal iterations, reduces system complexity and improves computational speed; through a good set of constraints, such an algorithm will give an optimal aero engine conceptual design that will be feasible in terms of engine certification and customer requirements. • The semi-empirical correlation derived can predict with sufficient accuracy - for conceptual design - the NOx emissions for modern rich-burn single- annular combustors. The correlation may be extrapolated with sufficient confidence for year 2020 entry into service conventional core turbofan en- gines. • The improved gradient-based algorithm - used for solving non-linear equa- tion systems - significantly improved the computational speed of the differ- ent codes it was utilised with, confirming expectations from the literature reviewed. Furthermore, the algorithm fully alleviates the computational penalty associated with the use of central differences. • In general, dissociation becomes first noticed at 1500 [K], and significant at 1800 [K]. The effects of dissociation on major performance parameters during design-point and off-design performance calculations are significant. For accurate block fuel predictions dissociation effects should not be ignored as this introduces a systematic error in the calculations. • Where radical design space exploration is concerned, improving the accu- racy of the fluid model needs to be carefully balanced with the computa- tional time penalties involved. For an intercooled cycle with a high overall pressure ratio the ideal gas assumption does not hold very well; if the ideal 176PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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