Cooling System Design for a Fully Superconducting Machine Used in Future Aircrafts
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Considering developments in superconducting machines (motors and generators), modern methods and innovations required for optimization in this field like any other energy-based systems. Meanwhile, some improvements in superconducting technologies has been drawn to flying sciences such as future turbo-electric aircrafts. Thus, companies and pioneers in this industry like NASA have been investing many resources on the aim of future aircrafts working based upon Turboelectric distributed propulsion (TeDP), Hybrid and/or electric propulsion systems. Based on the fact that superconducting machines could make gigantic saves in energy waste, they came into spotlight. This promising technology also requires demanding attentions in the area of ahead obstacles such as novel cooling methods; there have been some analyzes in this area, though. Regarding to this issue, this study is aimed to design cooling systems for superconducting machines working with liquid hydrogen (LH2) as coolant. The indirect cooling system, which is based on both convection and conduction, has been employed. Having all sort of designs and ideas, a meander and helical shape design is recommended for rotor and stator, respectively. The results should comprise two important goals: 1) providing cryogenic temperature for system 2) evaluating pressure and outlet phase of LH2 working in a loop. Hence, different conventional materials in cryogenic sciences have been analyzed and compared to the famous metallic mate like aluminum.