US 12,351,331 B2
Refueling system for hydrogen fuel cell-powered aircraft
Valery Miftakhov, San Carlos, CA (US); and Sergey Kiselev, London (GB)
Assigned to ZeroAvia, Ltd., Cirencester (GB)
Filed by ZeroAvia, Ltd., Cirencester (GB)
Filed on Mar. 28, 2022, as Appl. No. 17/656,877.
Claims priority of provisional application 63/168,683, filed on Mar. 31, 2021.
Prior Publication US 2022/0336829 A1, Oct. 20, 2022
Int. Cl. B64D 37/16 (2006.01); B64D 37/30 (2006.01); H01M 8/04007 (2016.01); H01M 8/04082 (2016.01); H01M 8/04111 (2016.01); B64D 27/355 (2024.01); B64F 1/28 (2006.01); H01M 8/04089 (2016.01)
CPC B64D 37/16 (2013.01) [B64D 37/30 (2013.01); H01M 8/04007 (2013.01); H01M 8/04111 (2013.01); H01M 8/04201 (2013.01); B64D 27/355 (2024.01); B64F 1/28 (2013.01); H01M 8/04089 (2013.01); H01M 2250/20 (2013.01); Y02T 90/40 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A system comprising:
a source of low temperature, high pressure hydrogen gas;
a compressor adapted to fluidly couple with said source of low temperature, high pressure hydrogen gas, said compressor comprising:
an intake manifold configured to receive said low temperature, high pressure hydrogen gas from said source and direct said low temperature, high pressure hydrogen gas through a plurality of compression blades;
said plurality of compression blades configured to compress said low temperature, high pressure hydrogen gas into a higher temperature, higher pressure hydrogen gas as said low temperature, high pressure hydrogen gas passes therethrough; and
a compression chamber defined within said compressor, said compression chamber to receive said higher temperature, higher pressure hydrogen gas from said plurality of compression blades;
a valve operably coupled with said compression chamber, said valve configured to reduce said pressure of said higher temperature, higher pressure hydrogen gas to a higher temperature, lower pressure hydrogen gas;
a storage container on an aircraft, said storage container to receive said higher temperature, lower pressure hydrogen gas via said valve; and
a heat exchanger disposed in thermal cooperation with said compression chamber and configured to absorb excess heat from said compression chamber and convert said excess heat into storable energy to power at least one other component of said aircraft.