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Towards the optimal 2020 ducted turbofan Konstantinos G. Kyprianidis setting a lower limit on the intercooled core size for a given OPR. Increasing the fan diameter at a fixed tip speed inevitably reduces rotational speed, increases torque and hence increases Low Pressure (LP) shaft diameter; this further ag- gravates the problem since the HPC hub to tip ratio needs to increase. As a result, the optimal specific thrust for the intercooled core is higher compared to the conventional core turbofan engine. Although the high OPR intercooled core benefits from a higher core and transmission efficiency, and hence a better ther- mal efficiency, the conventional core benefits from a higher propulsive efficiency. In the next sections, the design space around the proposed fuel optimal designs will be explored and important observations will be made. 7.2.3 Approximating the design space In order to graphically illustrate the design space, a large number of TERA2020 simulations had to be carried out; these simulations focused around the fuel opti- mal designs presented in Section 7.2.2. Polynomial response surface models were derived that interpolate between a given number of known designs. Typical de- sign space discontinuities encountered as a result of turbomachinery stage count changes are inevitably distorted in polynomial approximations. For this reason, an error analysis was carried out to determine the discrepancy levels between the surrogate models and the actual design space; the approximation errors for engine weight and aircraft block fuel were found to be less than 1% and 0.2%, respectively. 7.2.4 Fan and core sizing As discussed earlier, propulsive efficiency benefits from reducing specific thrust (and hence increasing fan diameter) can very well be negated by the resulting combination of: i) increased engine weight, ii) increased nacelle (and interference) drag, and iii) reduced transmission efficiency. This section will discuss various aspects of fan and core sizing for the conventional core and intercooled core configurations. 160PDF Image | Multi-disciplinary conceptual design of future jet engine systems
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