United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Isaac Jon Hogate

Scot Adams Webb

Thomas W Ward

Steven D Roberts

George Alan Salisbury

Scot A Webb

David E Gottschalk

Christina M Williams

Shane C Hilton

Kenneth F Tosi

Neill E Brown

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes an aircraft propulsion system component with a leading edge. The aircraft propulsion system assembly also includes artificial ice attached to the aircraft propulsion system component. The artificial ice at least partially covers and extends longitudinally along the leading edge.

Artificial ice for an aircraft component

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.

De-icing by integral electric heat generation

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.

An assembly for a turbine engine includes an inner platform, and outer platform and a plurality of structural inlet guide vanes. The outer platform circumscribes the inner platform. The structural inlet guide vanes are arranged around an axis, and extend radially between and are connected to the inner platform and the outer platform. A first of the structural inlet guide vanes includes a structural vane body that is configured from or otherwise includes an organic matrix composite.

Organic matrix composite structural inlet guide vane for a turbine engine

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.

Engine inlet ice protection system having embedded variable watt density heaters

Engine inlet ice protection system with power control by zone

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.

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Meriden, CT, United States of America

Isaac Jon Hogate