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AssigneeGeneral Electric Company
InventorsDaniel A. Niergarth, Giridhar Jothiprasad, Rodrigo Rodriguez Erdmenger, Adam Joseph Wangler
Estimating the term…
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 P O W = P p u m p ( c p_pump c p_water ) ( ρ w a t e r ρ p u m p ) 2 , F F R = ( P e n g i n e N H C f u e l ) ( c p_fuel c p_pump ) 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.
An aircraft comprising:
A gas turbine engine comprising:
A method for operating a gas turbine engine used in an aircraft, the method comprising:
Dependencies are inferred from the claim text.