The present disclosure provides a tape comprising: a) a single layer comprising a crosslinked polymer, selected from the group consisting of crosslinked polyurethane, crosslinked polyurea, and crosslinked mixed polyurethane/polyurea polymer, and b) an adhesive layer. In another embodiment, the tape comprises at least one layer comprising a semi-interpenetrating polymer network of a crosslinked acrylate and an uncrosslinked polymer selected from the group consisting of polyurethane, polyurea, and mixed polyurethane/polyurea polymer.

There is provided a heat management system for a hybrid electrical aircraft comprising electric propulsors powered by a power plant. The heat management system comprises a heat exchanger integrated to a nacelle of at least one of the electric propulsors for dissipating heat withdrawn from the power components of the power plant into ambient air.

There is provided a heat management system for a hybrid electrical aircraft comprising electric propulsors powered by a power plant. The heat management system comprises a heat exchanger integrated to a nacelle of at least one of the electric propulsors for dissipating heat withdrawn from the power components of the power plant into ambient air.

A method and apparatus combining an aircraft wing and engine ice protection system with an aircraft electronic cooling system

A method and apparatus combining an aircraft wing and engine ice protection system with an aircraft electronic cooling system

A wing comprising a leading edge forming a caisson delimited by a wall and an electrically conductive skin forming a lower surface and an upper surface and pierced with holes. A pump is provided to suck the air present in the caisson and/or to inject air into the caisson. The wing includes a voltage generator. Each hole is equipped with an anti-clogging system which comprises an electrically conductive electrode, an electrically insulating body having a stem which lodges in the hole and which has a central orifice in which the electrode lodges. The outer face of the stem has at least one tooth, where each tooth protrudes from the outer face of the stem and extends over the height of the stem. The at least one tooth is distributed around the stem so as to create at least one channel.

In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.

A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

A combination of liquid-to-air and air-to-liquid heat exchangers is employed in an aircraft anti-icing system configured to avoid ice buildup on exterior leading edges of wings and engine inlets of aircraft during flight under known or anticipated icing conditions. The anti-icing system may be utilized in lieu of traditionally employed air-to-air heat exchangers. In one embodiment, a heated anti-icing liquid is conveyed through tubes juxtaposed against interior surfaces of the leading edges of the wings and engine inlets. The liquid is heated by engine core bleed air, and the tubes are arranged to optimize heat flux directly from the tubes into the leading edges of the wings and the engine inlets, respectively, to avoid ice accumulation. In one configuration, spring clips retain the tubes directly against the leading edge interiors of the wings and engine inlets, and thermal grease and insulation are used to enhance heat flux.

An aircraft component assembly has a structural body and a thermal management de-icing system for minimizing or preventing ice build-up on leading edges of the body. The system includes a supply line for flowing heated fluid to the leading edges and a cooling device that interposes the supply line to prevent overheating of the leading edges thus protecting bodies that may be made of composite materials that are more susceptible to heat.