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3.2 Methods for Sizing and Performance of Hybrid-Electric Aircraft 29 in Figure 3.6. The weight of the engines was predicted according to geometric component dimensions and performance parameters based on conceptual design methods developed by Seitz et al. [104]. Figure 3.7 represents the evolution of the total propulsion system weight (including the nacelle weight) versus the 𝑇𝑑𝑒𝑠,𝑇𝐹 for a geared turbofan sized at a 𝐹𝑃𝑅𝑑𝑒𝑠,𝑇𝐹 of 1.41. The nacelle reference diameter and length, illustrated in Figure 3.7, were estimated based on a typical slenderness ratio of a generic turbofan nacelle. For each of the engines, the maximum thrust and fuel flow characteristics were provided in form of multi-dimensional tables in order to interface the conventional powerplant character- istics at aircraft level. In the approach adopted, the thrust and fuel flow tables are a function of the design thrust. The integration of these tables within the aircraft sizing environment is illustrated in Figure A.1. The maximum thrust characteristics at MCL rating are illustrated in Figure 3.8 for a geared turbofan sized at a 𝑇𝑑𝑒𝑠,𝑇𝐹 of 21 kN. The design at ISA, FL 350, 𝑀 0.78 conditions and at a MCL thrust setting yielded to a thrust specific fuel consumption (𝑇𝑆𝐹𝐶) of 13.24 g/kN/s for the engine designed at a 𝑇𝑑𝑒𝑠,𝑇𝐹 of 35 kN, and, of 13.30 g/kN/s for the engine designed at a 𝑇𝑑𝑒𝑠,𝑇𝐹 of 15 kN. This demonstrates the relatively small scale effect on the engine efficiency. The 𝑇𝑆𝐹𝐶 characteristics of the geared turbofan models are represented in Figure 3.9 at cruise condition ISA+10°C, FL 350 and 𝑀0.76 against the thrust setting for each design thrust. It can be observed that the scale effect has also a small influence on the 𝑇 𝑆𝐹 𝐶 characteristics. The so-called 𝑇 𝑆𝐹 𝐶 bucket extends in these models from around 70% to 100% of the maximum thrust. This characteristic is important as it determines the efficiency evolution of the geared turbofan in part load operation during cruise. Within the bucket, the geared turbofan runs close to its maximal efficiency under the given flight conditions. 14.05 13.95 13.85 13.75 13.65 13.55 13.45 13.35 13.25 13.15 13.05 12.95 12.85 D D D D esign t hrust = 15 kN esign t esign t esign t hrust = hrust = hrust = 21 kN 28 kN 35 kN Study Settin gs: ISA+1 0°C, F 350, M ach0.7 6 L 12.75 50 55 60 65 70 75 80 85 90 95 100 T / T [%] max Figure 3.8: Thrust characteristics un- der MCL rating. Geared turbofan sized for a design thrust of 21 kN and a design FPR of 1.41 [31]. Figure 3.9: TSFC characteristics of the geared turbofans sized for a design FPR of 1.41 at cruise condition ISA+10°C, FL 350 and M 0.76 [31]. TSFC [g/s/kN]PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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