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Konstantinos G. Kyprianidis Introduction Reducing engine weight results in a lower aircraft maximum take-off weight, which in turn leads to reduced thrust requirements for a given aircraft lift to drag ratio. Reducing engine size – predominantly engine nacelle diameter and length – reduces nacelle drag and therefore also leads to reduced thrust requirements. For a given engine SFC, a reduction in thrust requirements essentially results in lower fuel consumption. Lower engine SFC can be achieved by improving propulsive efficiency and thermal efficiency. Improving component efficiencies, as well as reducing other losses in the cycle, such as duct pressure losses and cooling flows, is another way of improving engine SFC. Modern CFD-assisted 3D blade designs however, are already quite aggressive and limited benefit may be envisaged by such future advancements in terms of loss reduction [5]. In the following sections, three important research questions will be set with respect to improving engine thermal and propulsive efficiency, and simultaneously reducing CO2 and NOx emissions. 1.2.1 Propulsive efficiency Improvements in propulsive efficiency – and hence engine SFC at a given thermal efficiency – can be achieved by designing an engine at a lower specific thrust (i.e. net thrust divided by fan inlet mass flow). This results in a larger fan diameter, at a given thrust, and therefore in increased engine weight, which can partially, or even fully, negate any SFC benefits. Propulsive efficiency improvements at a constant weight are directly dependent on weight reduction technologies such as light weight fan designs and new shaft materials. Increasing engine bypass ratio aggravates the speed mismatch between the fan and the low pressure turbine. Introduction of a gearbox can relieve this issue by permitting the design of these two components at their optimal speeds, and can hence reduce engine weight, as well as improve component efficiency. The first research question therefore rises: How low can we really go on specific thrust? 3PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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