A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.
B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
B64D 35/06 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
F02K 3/072 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with counter-rotating rotors
F02K 3/08 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluidControl thereof
F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
Examples provide electric propulsion systems; such a system comprising: a. a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, b. at least one fan stage comprising a fan bearing a plurality of aerodynamic surfaces/blades to generate thrust mounted within a fan shroud, and c. a powertrain comprising at least one electric motor to drive the fan shroud and at least one electrical power source to power the electric motor; and d, wherein i. the fan shroud is disposed within the inner duct, ii. at least part of the powertrain is disposed within the internal annular volume, iii. the at least one electric motor is disposed within the central hub and iv. the hub-to-tip ratio is between 0.1 and 0.4, preferably, between 0.2 and 0.3.
Examples provide an electric propulsion system; the system comprising a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, only a single one fan stage comprising a fan bearing a plurality of aerodynamic surfaces/blades to generate thrust, and a powertrain comprising at least one electric motor to drive the fan and at least one electrical power source to power the electric motor; and wherein the fan is disposed within the inner duct and the powertrain is disposed within the internal annular volume.
Examples relate to a ducted and shrouded propeller rotatable having an axis of rotation and being optionally rim driven; the shrouded propeller having: at least one, or both, of: the radially inwardly and outwardly directed shroud surface bearing a plurality of spaced apart structures adapted to reduce the acoustic energy generated by the propeller while interacting with a medium, the radially inwardly directed shroud surface bearing blades of the propeller.
B64D 35/026 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants the electric power plant being integral with the propeller or rotor
A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.
B64C 11/48 - Units of two or more coaxial propellers
B64C 11/00 - Propellers, e.g. of ducted typeFeatures common to propellers and rotors for rotorcraft
B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 35/06 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
F02K 3/072 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with counter-rotating rotors
F02K 3/08 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluidControl thereof
F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
Examples provide an electric propulsion system; the system comprising a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, only a single one fan stage comprising a fan bearing a plurality of aerodynamic surfaces/blades to generate thrust, and a powertrain comprising at least one electric motor to drive the fan and at least one electrical power source to power the electric motor; and wherein the fan is disposed within the inner duct and the powertrain is disposed within the internal annular volume.
Examples provide electric propulsion systems; such a system comprising: a. a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, b. at least one fan stage comprising a fan bearing a plurality of aerodynamic surfaces/blades to generate thrust mounted within a fan shroud, and c. a powertrain comprising at least one electric motor to drive the fan shroud and at least one electrical power source to power the electric motor; and d. wherein i. the fan shroud is disposed within the inner duct, ii. at least part of the powertrain is disposed within the internal annular volume, iii. the at least one electric motor is disposed within the central hub and iv. the hub-to-tip ratio is between 0.1 and 0.4, preferably, between 0.2 and 0.3.
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