Patent ID: 11952944
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. 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 including a thermal transport bus 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 transport bus including a pump configured to generate a pump power (Ppump) to pressurize the working fluid in the thermal transport bus, 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
     
    
   
  
  ,
  
   FFR
   =
   
    
     (
     
      
       P
       
        e
        ⁢
        n
        ⁢
        g
        ⁢
        i
        ⁢
        n
        ⁢
        e
       
      
      
       NHC
       fuel
      
     
     )
    
    ⁢
    
     (
     
      
       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 are the density and specific heat capacity of water, respectively.