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.