Development of liquid hydrogen cooling system for a rotor of superconducting generator

2021 ◽  
pp. 1-1
Author(s):  
Shintaro Hara ◽  
Yoshiki Iwami ◽  
Rikako Kawasaki ◽  
Taito Matsumoto ◽  
Yasuyuki Shirai ◽  
...  
Keyword(s):  
Cooling System ◽  
Liquid Hydrogen ◽  
Hydrogen Cooling

scholarly journals Development of fully superconducting 5 MW aviation generator with liquid hydrogen cooling

2022 ◽  
pp. 62-73
Author(s):  
Dmitry Dezhin ◽  
Roman Ilyasov
Keyword(s):  
Electric Propulsion ◽  
Fem Simulation ◽  
Synchronous Generator ◽  
Liquid Hydrogen ◽  
Propulsion System ◽  
Moscow Aviation Institute ◽  
Cross Sectional ◽  
Electric Propulsion System ◽  
The Future ◽  
Hydrogen Cooling

The use of liquid hydrogen as a fuel will be inevitable in the aviation of the future. This statement means that manufacturers will also implement liquid hydrogen for cooling all superconducting aviation equipment of an electric propulsion system. The development of fully electric aircraft is the most promising solution in this case. Scientists from the Department of electrical machines and power electronics of Moscow aviation institute have conducted calculations and theoretical researches of critical specific mass-dimensional parameters (MW/ton and MW/m3 at 21 K) of fully superconducting aviation synchronous generator of the electric propulsion system. The results are in this article. The article discusses the results 3D finite element modeling (FEM) simulation of a 5 MW fully superconducting synchronous generator with combined excitation. Superconducting armature and axial excitation windings based on second generation high temperature superconductors (HTS-2G) are located on the stator, which makes it possible to contactlessness and the absence of sliding seals. A dry gap will reduce gas-dynamic losses and increase the nominal peripheral speed of the rotor. The use of liquid hydrogen as a coolant makes it possible to significantly increase the linear load of the generator, and high current densities to reduce the cross-sectional area of the coils, which will make it possible to place them in individual cryostats in the future. Individual cryostats will allow to remove the heat release of magnetic losses from the cryogenic zone and reduce the consumption of refrigerant. For the purpose of internal redundancy of the HTS coils, the machine has a complete set of reserve winding made of ultrapure aluminum, also cooled by liquid hydrogen. If the superconducting coils get out of the stand, the generator will provide 15 % power on standby

Safety Design and Mock-Up Tests on the Combustion of Hydrogen-Air Mixture in the Vertical CNS Channel of the CARR-CNS

2006 ◽  
Author(s):  
Qingfeng Yu ◽  
Quanke Feng
Keyword(s):  
Cooling System ◽  
Characteristic Point ◽  
Liquid Hydrogen ◽  
Hydrogen Gas ◽  
Outer Diameter ◽  
Two Phase ◽  
Design Strength ◽  
Transfer Tube ◽  
Combustion Tests ◽  
Moderator Cell

A two-phase thermo-siphon loop is applied to the Cold Neutron Source (CNS) of China Advanced Research Reactor (CARR). The moderator is liquid hydrogen. The two-phase thermo-siphon consists of the crescent-shape moderator cell, the moderator transfer tube, and the condenser. The hydrogen is supplied from the buffer tank to the condenser. The most characteristic point is that the cold helium gas is introduced into the helium sub-cooling system covering the moderator cell and then flows up through the tube covering the moderator transfer tube into the condenser. The helium sub-cooling system also reduces the void fraction of the liquid hydrogen and takes a role of the helium barrier for preventing air from intruding into the hydrogen system. We call the two-phase thermo-siphon the hydrogen cold system. The main part of this system is installed in the CNS channel made of 6061 aluminum alloy (6061A) of 6 mm in thickness, 270 mm in outer diameter and about 6 m in height. For confirming the safety of the CNS, the combustion tests were carried out using the hydrogen-air mixture under the conditions in which air is introduced into the tube at 1 atmosphere, and then hydrogen gas is supplied from the gas cylinder up to the test pressures. And maximum test pressure is 0.140 MPa Gauge (G). This condition includes the design accident of the CNS. The peak pressure due to combustion is 1.09 MPa, and the design strength of the CNS channel is 3 MPa. The safety of the CNS was thus verified even if the design basis accident occurs. The pressure distribution, the stress, and the displacement of the tube were also measured.

Zero Boil-Off Cryogenic Liquid Hydrogen Storage Tank With Axial Cold-Spray System

2006 ◽  
Author(s):  
Son H. Ho ◽  
Muhammad M. Rahman
Keyword(s):  
Fluid Flow ◽  
Cold Spray ◽  
Storage Tank ◽  
Cooling System ◽  
Liquid Hydrogen ◽  
Front Face ◽  
Bulk Fluid ◽  
External Cooling ◽  
Nozzle Head ◽  
Inlet Opening

This paper presents a steady-state analysis of fluid flow and heat transfer in a zero boil-off cryogenic storage tank for liquid hydrogen. The system includes a tank with cylindrical wall and oblate spheroidal top and bottom, and a cold-spray nozzle head whose face is set perpendicular to the axis of the tank. The nozzle head has many nozzles on its front face. The cold fluid cooled by an external cooling system enters the inlet opening at the top of the tank, follows an axial supply tube to the nozzle head and exits through the nozzles into the bulk fluid inside the tank heated by heat leak from the surroundings. The displaced fluid exits the tank through an annular outlet opening (also at the top of the tank and concentric with the inlet opening) then goes back to the external cooling system. This study considers the transport phenomena in the storage tank only with prescribed fluid flow velocity and temperature at the inlet to represent the external cooling system.

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