Patent ID: 11898489
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 7:
8. The gas turbine engine according claim 1, wherein a fan tip radius of the fan is defined between a centreline of the engine and an outermost tip of each fan blade at its leading edge and a fan hub radius of the fan is defined between the centreline of the engine and an outer surface of the hub at the radial position of the leading edge of each fan blade, wherein a fan hub to tip ratio of:, the
   ⁢
      
   fan
   ⁢
      
   hub
   ⁢
      
   radius
  
  
   the
   ⁢
      
   fan
   ⁢
      
   tip
   ⁢
      
   radius, is in the range from 0.2 to 0.285.