Patent ID: 9476654
Filing Date: 2016-10-25
CPC Classification: B64G,F02C,F02K,F05D,F28D,F28F

Claim Text:
1. An aircraft/spacecraft fluid cooling system comprising: a first feed pipe that feeds a fluid that is a cryogenic fluid from a storage tank to a pump, the cryogenic fluid from the storage tank being used for combustion in a combustor; a second feed pipe that feeds the fluid from the pump to the combustor; a cooling section that expands the fluid having traveled through the pump, feeds the fluid to an outer periphery of at least one of the first feed pipe and the second feed pipe so as to cool the fluid in at least one of the first feed pipe and the second feed pipe, and discharges the fluid that was expanded outside; a cooling section inlet pipe that feeds the fluid from the pump to the cooling section; and an on-off valve that is provided at the cooling section inlet pipe, the on-off valve being configured to be open in a state in which the fluid is allowed to travel to the cooling section, the on-off valve being configured to be closed in a state in which the fluid is not allowed to travel to the cooling section, wherein the on-off valve is configured to be open before ignition of the combustor, wherein the cooling section inlet pipe feeds the fluid to the cooling section before ignition of the combustor, and wherein the cooling section discharges the fluid that was expanded outside before ignition of the combustor without supplying the fluid to the combustor.