Patent ID: 11952944

Abstract:
Jet engine thermal transport bus pumps are disclosed. Disclosed herein is an aircraft comprising a gas turbine engine configured to burn fuel at a fuel flow rate to generate an engine power (Pengine), the fuel characterized by a first specific heat capacity (cp_fuel) and a net heat of combustion (NHCfuel); and a thermal management system configured to transfer heat from a working fluid to the fuel, the working fluid characterized by a second specific heat capacity (cp_pump) and a first density (ρpump), the thermal management system including a pump configured to generate a pump power (Ppump) to pressurize the working fluid, and wherein 0.008≤POW/FFR5/3≤12, FFR is between 0.05 pounds-mass per second and 16 pounds-mass per second, and ρwater and cp_water is the density and specific heat capacity of water, respectively.