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Konstantinos G. Kyprianidis Introduction aero engine conceptual design process, was further developed in this project in order to be successfully utilised for exploring the three research questions pre- sented in Section 1.1. The tool is based on a modular design and features a sophisticated explicit conceptual design algorithm. TERA2020 considers a large number of disciplines typically encountered in conceptual design, such as: en- gine performance, engine aerodynamic and mechanical design, aircraft design and aerodynamic performance, emissions prediction and environmental impact, engine and airframe noise, as well as production, maintenance and direct operat- ing costs. Individually developed modules are integrated together in an optimiser environment; a large amount of information is available after every design itera- tion and can be used for many purposes such as technology impact assessment, sensitivity and parametric studies and multi-objective optimisation. In a nutshell, the work described in this thesis attempts to: 1. Present important aspects of the development of a sophisticated explicit algorithm that can help automate part of the aero engine conceptual design process. 2. Discuss the derivation of new models – and the further development of ex- isting ones – that are suitable for optimising the novel engine configurations studied under the NEWAC project. 3. Present system numerical improvements with respect to improving compu- tational speed, reducing non-convergence cases, and eliminating numerical noise problems hindering TERA2020 optimisation capability in the VITAL project. 4. Assess the impact of fluid modelling uncertainty on performance calcula- tions and emissions predictions at aircraft system level and identify ac- curacy limitations in assessing novel engine core concepts as imposed by current practice in thermo-fluid modelling. 5. Quantify potential benefits from novel technologies for three low pressure spool turbofan architectures, as developed under the VITAL project. 6. Quantify potential benefits from the introduction of heat-exchanged cores with variable geometry features in future aero engine designs, as developed under the NEWAC project. 5PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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