Active superhydrophobic surface structures are actively-controlled surface structures exhibiting a superhydrophobic state and an ordinary state. Active superhydrophobic surface structures comprise an outer elastomeric covering defining an exposed surface, a controlled group of MEMS (micro-electro-mechanical system) actuators at least covered by the elastomeric covering, and, a controlled region of the exposed surface corresponding to the controlled group. The controlled region has a superhydrophobic state in which the controlled region is textured. The controlled region also has an ordinary state in which the controlled region is smooth (i.e., less textured than in the superhydrophobic state). Active superhydrophobic surface structures may be part of an apparatus that includes a controller and/or one or more sensors. The controller, sensors, and the controlled region may form a feedback loop in which the active superhydrophobic surface is actively controlled.

In order to maintain a surface region of an aircraft free of ice in a particularly energy-efficient manner, a device for deicing and/or for preventing ice formation is provided on an aircraft. The device includes a heat emitting device for emitting heat at a surface region of the aircraft, the heat emitting device is designed to dissipate heat along a line in order to produce a predetermined breaking point or a predetermined breaking line or parting line in ice accumulating on the surface region.

A system and method for monitoring icing conditions that are suitable ice formation on an aircraft and propulsion system. The system includes instrumentation that instantaneously detects ambient humidity, ambient temperature and ambient pressure. The sensed information is transmitted to a controller that evaluates the information to determine whether certain pressure, temperature and humidity criteria are favorable for icing and, declaring icing conditions. The system also includes an aircraft engine-mounted ice mitigation system. When conditions for ice formation are favorable, the controller either informs the pilot that conditions for ice formation are favorable or automatically activates the ice mitigation system, or both. The pilot optionally may inactivate the ice mitigation system. When sensed conditions indicate that conditions for ice formation are not favorable, the controller determines whether the ice mitigation system is activated and inactivates the system if activated.

The invention deals with a splitter nose delimiting the inlet of a low-pressure compressor of an axial turbine engine. The splitter nose comprises a separation surface with an upstream circular edge suitable for separating a flow entering into the turbine engine into a primary flow and a secondary flow, and a plasma de-icing device. The device comprises two annular layers of dielectric material (42; 44) partially forming the separation surface, an electrode forming the upstream edge, an electrode forming an outer wall of the splitter nose, an electrode forming an outer shroud which supports blades, an electrode delimiting the primary flow. The device generates plasmas (46; 48; 50) opposing the presence of ice on the partitions of the splitter nose. The invention also deals with a turbine engine with a splitter nose that is provided with a de-icing system downstream of the fan.

A cooling system including a heat load; a supply line supplying a cold coolant to the heat load, wherein the cold coolant receives heat from the heat load and becomes a hot coolant, a return line receiving the hot coolant from the heat load, a transducer generating elliptical ultrasonic waves, and a horn coupled to the receiving line and receiving the hot coolant, wherein the horn conveys the elliptical ultrasonic waves to the hot coolant. The hot coolant, in response to the horn conveying the elliptical ultrasonic waves, undergoes heat loss through convection. Elliptical ultrasonic waves are provided by a transducer combining a longitudinal actuator and a bending actuator.

The invention concerns an aircraft propulsion system comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a stream (F), characterised in that said member is covered, at least partially, by a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a series of grooves, in contact with the flow of the stream, the grooves extending in the direction of flow of the stream, the grooved structure comprising at least one geometric parameter (h, s, w) configured to adapt depending on at least one parameter of the flow of the stream and/or an operating point of the propulsion system and/or an engine speed of the propulsion system.

An ice removal apparatus for an aircraft is provided comprising a laminate structure encapsulating an electrically operable heater. The laminate structure comprises a plurality of layers and at least two layers are configured to be selectively movable relative to each other to increase the separation of the two layers, thereby removing ice.

An airfoil comprises a skin, comprising an external surface and an internal surface. The skin has a controlled region. The airfoil also comprises an interior space, formed by the skin. The airfoil additionally comprises a hybrid acoustic induction-heating system, configured to impede formation of ice on the external surface. The hybrid acoustic induction-heating system comprises induction coils and a control system. Each one of the induction coils has a portion, arranged sufficiently close to the internal surface to produce an eddy current within the controlled region. The control system is configured to generate inductive heat and traveling-wave acoustic pressure in the controlled region by supplying different phases of the alternating electrical current to the induction coils based, at least in part, on an ambient temperature of a layer of fluid flowing over the external surface.

An actuator mounting method for mounting at least one actuator involves providing a skin structure and at least one actuator, and fixing the at least one actuator to the inner surface of the skin structure.

A method of impeding formation of ice on an exterior surface of airfoil is disclosed. The method comprises detecting first ambient conditions known to cause the ice to form on exterior surface. The method also comprises supplying inductive heat and acoustic pressure to exterior surface when the first ambient conditions are detected. The method additionally comprises detecting second ambient conditions known to impede the ice from forming on exterior surface. The method further comprises discontinuing to supply the inductive heat and the acoustic pressure to exterior surface when the second ambient conditions are detected.