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30 3 Methods for Sizing and Performance of Hybrid-Electric Aircraft 3.2.3.2 Methods for Propulsive Device Integration The relevant design parameters of the propulsive device can be determined by using gas- turbine performance software. The characteristics of the propulsive device implemented in this thesis are discussed based on a zero-dimensional performance model of a ducted fan developed by Steiner et al. [106]. The model relies on classical gas dynamic theory and standard compressor theory. Based on this model, a design deck of the propulsive device was created to determine the main design parameters with respect to the design thrust of the propulsive device (𝑇𝑑𝑒𝑠,𝑃𝐷) and the design fan pressure ratio of the propulsive device (𝐹𝑃𝑅𝑑𝑒𝑠,𝑃𝐷). The flow path sizing was performed at TOC design conditions ISA, FL 350, 𝑀 0.78. According to the design thrust and the 𝐹𝑃𝑅𝑑𝑒𝑠,𝑃𝐷, the geometry of the propulsive device is generated. The evolution of fan diameter represented as a contour plot in Figure 3.10. of the e e 15 propulsive W device (𝐷𝐹 𝑎𝑛,𝑃 𝐷 ) is 4.5 4 3.5 3 2.5 2 35 30 25 20 15 10 1.15 1.2 1.25 4 3.5 3 2.5 2 1.5 Fan dia meter [m] 1.3 1.35 1.4 1.45 1.5 Design Fan Pressure Ratio [−] 3000 2500 2000 1500 1000 500 0 10 =4 Total Nac Nac Ducted Fan lle Reference lle Reference eight [kg] Diameter [m] Length [m] Study S ISA, FL Total Du ettings: 350, M 0.78, cted Fan Weig FPR = 1. desPD ht (including Na 1 celle Weight) Figure 3.10: Ducted versus design thrust and design fan pressure ratio. Ducted fan sized at ISA, FL 350, M 0.78. Figure 3.11: 1.5 20 25 30 35 Design Thrust [kN] Ducted fan weight and geometry versus design thrust. Ducted fan sized at ISA, FL 350, M 0.78 and design FPR 1.41. fan diameter For the integration of a ducted propulsive device, the nacelle reference length and diameter are determined and interfaced with the geometric module of the aircraft environment. These parameters can be determined by correlations developed in [107, 108] or by using scaling methods of a known reference nacelle geometry. For sake of consistency the correlations used for the sizing of the short-duct fan cowling of the turbofan were also implemented for the sizing of the ducted-fan nacelle geometrical properties. The nacelle geometrical reference parameters are represented in Figure 3.11 versus 𝑇𝑑𝑒𝑠,𝑃𝐷. The geometry of the ducted propulsive device is also interfaced at aircraft level with drag component build-up functions to determine profile drag generated by the nacelle. Based upon the geometrical properties of the propulsor and nacelle, the weight of the system can be predicted using weight correlations as published in [107, 109], or, on conceptual design methods as developed by Seitz et al. [104] which were used for the prediction of the ducted fan weight as represented in Figure 3.11. Besides geometrical dimensions and weight modelling, the determination of the design and off- Design Thrust [kN] Weight [kg] Length [m]PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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