A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.

A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.

The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2),
wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).

The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2),
wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).

An aircraft engine air inlet lip takes an annular form about a longitudinal axis and delimits an air inlet stream, and includes: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards interior of the air inlet lip, an inner wall extending inside the wall between two zones of the inner face, so as to close an inner chamber delimited between the wall and the inner wall and filled with a gas, the inner wall having an upstream face oriented towards and a downstream face oriented away from the inner chamber, a fan configured to move the gas contained in the inner chamber, and at least one pipeline fixed to the upstream face and extending all around the air inlet lip and configured to be fed with a heat transfer fluid heated by a heat source.

A method for precise control of movement of a motive phase on a lubricant-impregnated surface includes providing a lubricant-impregnated surface, introducing the motive phase onto the lubricant-impregnated surface, and exposing the droplets to an electric and/or magnetic field to induce controlled movement of the droplets on the surface. The lubricant-impregnated surface includes a matrix of solid features spaced sufficiently close to stably contain the impregnating lubricant therebetween or therewithin. The motive phase is immiscible or scarcely miscible with the impregnating lubricant.

A method for precise control of movement of a motive phase on a lubricant-impregnated surface includes providing a lubricant-impregnated surface, introducing the motive phase onto the lubricant-impregnated surface, and exposing the droplets to an electric and/or magnetic field to induce controlled movement of the droplets on the surface. The lubricant-impregnated surface includes a matrix of solid features spaced sufficiently close to stably contain the impregnating lubricant therebetween or therewithin. The motive phase is immiscible or scarcely miscible with the impregnating lubricant.

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.

Embodiments, described herein relate generally to devices, systems, and methods for producing lubricious surfaces with enhanced durability and which increase the ease of communication of viscous liquids across the same. The system can include a liquid-encapsulated surface including a substrate, a member coupled to the substrate, and an encapsulating liquid disposed on a surface of the member. In some embodiments, the surface of the member can have a chemistry such that the encapsulating liquid preferentially wets the surface and maintains lubricity in the presence of a contacting phase. In some embodiments, the encapsulating liquid can be substantially immiscible with the contacting phase, and/or can have a thickness of less than about 200 microns and/or can have a receding contact angle of less than 20 degrees in the presence of the contacting phase. In some embodiments, a liquid delivery mechanism can be configured to transfer the encapsulating liquid to the member.

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.