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Assessment of core technologies and concepts Konstantinos G. Kyprianidis 6.1 Enabling core technologies For conventional cores, increasing OPR and T41 depends on future advancements in material and cooling technology. Assuming that only mild further improve- ments can be achieved in these research fields in the near future, the design focus for more aggressive thermal efficiency improvements could well be redirected to the introduction of heat-exchanged cores in future turbofan designs. A common textbook misconception about intercooling is that the thermal ef- ficiency of an intercooled core will always be lower than a conventional core’s for a fixed OPR and specific thrust. The argument behind this is that the heat removed by the intercooler will largely need to be reintroduced in the combustor by burning more fuel, while the reduction in compression work will only par- tially compensate for the loss in cycle efficiency, at a fixed specific thrust and T41. Adding the expected intercooler pressure losses in the cycle calculations would further worsen the SFC deficit and make the increase in specific thrust less marked. However, cycle calculations based on half-ideal gas properties and no dissociation (i.e. isobaric heat capacity dependent on temperature), presented by Walsh and Fletcher [88], give a slightly different picture on intercooling. For a given T41, the optimal OPR for an intercooled core will be much higher than that for a conventional core. Comparing the two concepts at their optimal OPR levels, for a given technology level, can make the intercooled core more attractive with respect to thermal efficiency and not just specific thrust. Cani`ere et al. [207] and da Cunha Alves et al. [208] also reached the same conclusion about the thermal efficiency of the intercooled cycle while studying this concept for gas turbines used in power generation. Papadopoulos and Pilidis [209] worked on the introduction of intercooling, by means of heat pipes, in an aero engine design for long haul applications. Xu et al. [210] performed a mission optimization to assess the potential of a tubular intercooler. Recent work by Xu and Gro ̈nstedt [211] presents a refined tubu- lar configuration estimating a potential block fuel benefit of 3.4%. The work addresses the limitation that short high pressure compressor blade lengths and related low compression efficiencies may impose on engines designed for short range missions, and suggest a novel gas path layout as a remedy to this con- 130PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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