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Konstantinos G. Kyprianidis Towards the optimal 2020 ducted turbofan 7.3 Sensitivity analysis of optimal designs The study presented in this section aims to deliver averaged exchange rates which can be used to investigate the effect of technology parameter deviations on block fuel. Information on how these perturbations were introduced in the TERA2020 calculations is given in Appendix B. The sensitivity parameters compiled allow for system level quantification of the importance of research on specific component technologies i.e. they can be used to assess the importance of progress in specific component technologies for each engine configuration in a similar manner to the assessment presented in Chap- ter 5. Inversely, these exchange factors also help quantify the impact of technol- ogy shortcomings. The exchange rates presented should be perceived as fractional percentage variations from the technology target value that was assumed when deriving the fuel optimal designs presented in Section 7.2.2. 7.3.1 Conventional core The sensitivity analysis for the conventional core configuration is illustrated in Fig. 7.18. As expected for a low specific thrust engine, the low pressure system component technology has the greatest influence on performance; significant fuel benefits are expected by improving fan and LPT efficiency. Inversely, shortcom- ings in meeting projected technology targets for the low pressure system will have a major impact on overall engine/aircraft performance. As fan tip pressure ratio reduces, pressure losses in the bypass duct tend to have an increasingly dominant effect on transmission efficiency and, therefore, on the impact of propulsive efficiency improvements on SFC. By combining Fig. 7.3 and Fig. 7.18 it can be observed that a 10% increase in bypass duct pressure losses will halve the projected block fuel benefits from a 10 [in] increase in fan diameter and the consequent reduction in specific thrust. Failure to deliver the expected efficiency levels for the compressor components will increase combustor inlet temperatures resulting in higher NOx levels and reduced component life; combustor designs are highly sensitive to inlet conditions and it is highly likely that a significant shortcoming in compressor efficiency would result in a re-design of the combustor. 171PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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