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Module Development Konstantinos G. Kyprianidis 3.1.3 Engine models 3.1.3.1 Deck description Within the NEWAC project, the developed performance code is used to generate TERA2020 compatible engine performance rubber decks for: i) the short and long range applications of the direct drive fan intercooled core configuration, ii) the long range application of the geared fan intercooled recuperated core configuration, and iii) the long range application of the baseline direct drive fan conventional core configuration. The developed engine performance models are illustrated in Fig. 3.2, Fig. 3.3, and Fig. 3.4, respectively. For each configuration, two models are created; a design point cycle model and an off-design one. No component maps are used and no iterations are performed in the former; in the latter suitable component maps are used and a mathematical model needs to be set and solved. The code initially carries out a design point calculation at top of climb conditions (Alt = 35000 [ft], Mcr, ISA +10 [K]) to determine the scaling factors for the different component maps and the cross sectional areas of the bypass and core nozzles - a dual-nozzle system is used for the heat-exchanged configurations. The various off-design points can then be simulated and all the necessary engine performance data required by other TERA modules are produced. More details about the off-design cases simulated have already been given in Section 2.3.3.1. For defining a particular engine operating point, different parameters can be selected such as combustor outlet temperature, fuel flow rate, net thrust, and fan rotational speed. Variable geometry features in the Low Pressure Turbine (LPT) and the dual-nozzle system are addressed using secondary control parameters such as Variable Guide Vanes (VGV) angle and nozzle throat areas. Where the model’s mathematical description is concerned, the necessary independent variables and residuals are selected automatically by the code. The user may intervene in this process and select the parameters manually but this is not a trivial task; wrong choices can lead to mathematical models that have multiple or even no solutions. Methods from the LISIS library are used for solving the mathematical model formed (i.e. system of non-linear equations) and these are discussed in detail in Section 3.5. An example of such a mathematical model is given in Table 3.1. 36PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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