Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil an electrical coil operatively associated with a non-rotating forward assembly of the gas turbine engine; a magnet operatively associated with a rotating surface of the fan, the magnet and the electrical coil producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.

Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.

Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil an electrical coil operatively associated with a non-rotating forward assembly of the gas turbine engine; a magnet operatively associated with a rotating surface of the fan, the magnet and the electrical coil producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.

Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.

Abstract: A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base. A forward section is disposed between the leading edge and the base and has a radius at any axial location defined by a first equation. A transition section is disposed between the forward section and the base and has a radius at any axial location defined by a second equation. The first equation is different than the second equation.

Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.

Abstract: A system includes a first heater located at the leading edge of a gas turbine structural member, a second heater located aft of the first heater, and a third heater located aft of the second heater. The first, second and third heaters are electrically-powered to prevent icing of the gas turbine structural member. Each of the heaters has a Watt density, and the Watt densities of the heaters differ from one another as a function of a magnitude of a cooling coefficient for airflow passing the vicinity of each heater.

Abstract: A system includes a first heater located at the leading edge of a gas turbine structural member, a second heater located aft of the first heater, and a third heater located aft of the second heater. The first, second and third heaters are electrically-powered to prevent icing of the gas turbine structural member. Each of the heaters has a Watt density, and the Watt densities of the heaters differ from one another as a function of a magnitude of a cooling coefficient for airflow passing the vicinity of each heater.

Abstract: A system includes a first heater located at the leading edge of a gas turbine structural member, a second heater located aft of the first heater, and a third heater located aft of the second heater. The first, second and third heaters are electrically-powered to prevent icing of the gas turbine structural member. Each of the heaters has a Watt density, and the Watt densities of the heaters differ from one another as a function of a magnitude of a cooling coefficient for airflow passing the vicinity of each heater.

Abstract: A system includes a first anti-icing electrothermal heater located at tip of a gas turbine engine nosecone, and a plurality of anti-icing electrothermal heater strips extending rearward from the first anti-icing electrothermal heater along the nosecone.

Abstract: A system includes a first anti-icing electrothermal heater located at tip of a gas turbine engine nosecone, and a plurality of anti-icing electrothermal heater strips extending rearward from the first anti-icing electrothermal heater along the nosecone.

Abstract: An engine inlet ice protection system and method for ice protection includes a plurality of grouped structural elements having electrical components that provide ice protection where power is cycled to the groups of structural elements so that at a given time the ice protection elements receiving power are generally distributed throughout the engine inlet.

Abstract: A system includes a first heater located at the leading edge of a gas turbine structural member, a second heater located aft of the first heater, and a third heater located aft of the second heater. The first, second and third heaters are electrically-powered to prevent icing of the gas turbine structural member. Each of the heaters has a Watt density, and the Watt densities of the heaters differ from one another as a function of a magnitude of a cooling coefficient for airflow passing the vicinity of each heater.

Abstract: A gas turbine engine is disclosed that includes an inlet case having circumferentially spaced, radially extending inlet struts. Each inlet strut has a leading and trailing end. Spaced apart sidewalls adjoin the leading and trailing ends. A first heating element is arranged on the leading end. A second heating element is arranged on at least one of the sidewalls. The first heating element is configured to provide a different amount of energy per unit of time than the second heating element.