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Conceptual Design of a Supersonic Jet Engine

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Conceptual Design of a Supersonic Jet Engine ( conceptual-design-supersonic-jet-engine )

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𝒅𝑷/π‘·π’Šπ’ π‘Ήπ’†π’”π’Šπ’…π’†π’π’„π’† π’•π’Šπ’Žπ’† π‘³π’π’‚π’…π’Šπ’π’ˆ 𝒂𝒕 π‘ͺπ’“π’–π’Šπ’”π’† π‘³π’π’‚π’…π’Šπ’π’ˆ 𝒂𝒕 π‘Ύπ’Šπ’π’…π’Žπ’Šπ’π’π’Šπ’π’ˆ 𝑷𝒂𝒕𝒕𝒆𝒓𝒏 𝑭𝒂𝒄𝒕𝒐𝒓 𝑽𝒄𝒄 π‘½π’π’Šπ’π’†π’“ 𝑺𝒍𝒐𝒑𝒆 π’‚π’π’ˆπ’π’† 4,11 𝑴𝒂𝒙 0,04 4π‘šπ‘  𝑷𝑳𝑭 23 1,15 π‘³π’π’Šπ’π’†π’“/π‘«π’π’Šπ’π’†π’“ 2 231 𝑳𝒄𝒄/𝑫𝒄𝒄 1,75 0,35 𝑽𝒄𝒄/π‘½π’π’Šπ’π’†π’“ 0,5 0,059π‘š3 π‘¬π’‡π’‡π’Šπ’„π’Šπ’†π’π’„π’š 0,029π‘š3 π‘Ίπ’•π’π’„π’‰π’Šπ’π’Žπ’†π’•π’“π’Šπ’„ π‘»π’†π’Žπ’‘. 8Β° 𝑻𝒐𝒕𝒂𝒍 π’π’†π’π’ˆπ’•π’‰ Table 10: Key combustor data 0,999 2300𝐾 0,195π‘š 4.3.5 Turbines A constant hub design was chosen for the turbines. This configuration allows for a higher blade speed due to the increasing blade tip radius, which reduces the stage loading. The loss coefficient πœ†π‘ was set to 0,05, at this value the stator blades are convergent, which allows for good performance over a variety of power conditions [19]. To avoid choking the turbines, the angle 𝛼3,π‘šπ‘’π‘Žπ‘› has been adjusted to satisfy the condition (𝑃01) < π‘ƒπ‘π‘Ÿπ‘–π‘‘π‘–π‘π‘Žπ‘™. The highest relative Mach number occurs at the inlet hub. 𝑃2 This value needs to be kept below 0,75 [19] to avoid high pressure losses due to shock waves. The tip clearance has been set to 1% of the blade length. The blade spacing was set to 20% of the upstream chord [11]. The two turbines can be seen on a smith chart [30], based on the average stage load and flow coefficient for the LPT, in figure 23. Figure 23: Stage load over flow coefficient for the HPT and LPT 4.3.5.1 HPT A highly loaded one stage HPT was chosen to minimize the required cooling flow. The HPT inlet area is derived from 𝐴𝑁2 to maintain stress levels based on material technology for 2025. π‘€π‘Žπ‘₯,𝑖𝑛 was then derived from the area. To avoid high pressure losses in the upstream ducting and to assure that the Figure 24: HPT component 39

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