An engine bleed control system for a gas turbine engine of an aircraft is provided. The engine bleed control system includes an engine bleed tap coupled to a fan-air source or a compressor source of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine and a motorized compressor in fluid communication with the engine bleed tap. The engine bleed control system also includes a controller operable to selectively drive the motorized compressor to boost a bleed air pressure as pressure augmented bleed air and control delivery of the pressure augmented bleed air to an aircraft use.

In manufacturing an electrothermal heater mat, there is provided a preform which comprises a laminated stack of dielectric layers which are made of thermoplastic material and include a central layer or group of layers which include(s) reinforcement and first and second outer groups of layers which do not include reinforcement. The preform includes a heater element and the preform has a first configuration. The preform is then heated to a temperature (e.g. 180° C.) between the glass-transition temperature of the thermoplastic material and the melting point of the thermoplastic material, and the heated preform is formed into a second configuration which is different to the first configuration so as to produce the heater mat.

An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

A number of devices are provided for detecting presence of ice in an airstream. In some examples such device includes a housing defining a first chamber and a second chamber, and a partition wall separating the first chamber and the second chamber. The first chamber has at least one inlet opening on a front housing wall facing the airstream, and at least one outlet opening, smaller than the at least one inlet opening. The second chamber is configured for being operatively coupled to at least one electromagnetic (EM) system that is configured for transmitting EM energy to the first chamber at least via the partition wall, which is transparent and/or translucent with respect to the EM energy, the EM energy being configured for melting ice that can accrete with respect to the inlet opening. The device is configured for being operatively coupled to at least one air pressure sensor in fluid communication with the first chamber for detecting at least pressure changes in the first chamber responsive to ice accretion on the inlet opening.

A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular inner wall defining a radially outer boundary of a compressor flow path defined through a compressor section of the gas turbine engine, an annular outer wall spaced apart from the annular inner wall along the radial direction, the annular outer wall adjacent to the annular inner wall at a forward end, the forward end defining an inlet to the compressor flow path, an annular bulkhead spanning between the annular inner wall and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port, and a passageway defined within the annular outer wall, the passageway extending from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the inlet defined by the forward end.

A method of making an adhesive for an ice protection assembly includes mixing ferrous nanoparticles into the adhesive. Removal of the adhesive for ice protection assembly inspection or repair includes heating the ferrous nanoparticles in the adhesive to soften the adhesive and allow for easy removal or repositioning of the ice protection assembly.

A valve assembly for an anti-ice system of an aircraft. The valve assembly comprises: a valve body; a first piston; and a regulating piston. The valve body defines a valve inlet, a valve outlet, a fluid passage between the valve inlet and the valve outlet, and a core portion defining a first chamber by cooperation with the first piston and a regulating chamber by cooperation with the regulating piston. The first piston is moveable between a first position and a second position, and the regulating piston is movable between a first position and a second position. The first piston overlaps the regulating piston when the first piston is its first position and the regulating piston is in its second position.

A method for manufacturing an electrified air filter for an intake system of an engine of a vehicle; the manufacturing method comprises the steps of: manufacturing an outer reinforcement mesh and an inner reinforcement mesh; manufacturing a filtering material panel; placing the reinforcement meshes on opposite surfaces of the filtering material panel so as to form a unit; bending the unit in a wave shape; and coupling the wave-shaped unit to a peripheral frame; externally coating the wires of said outer reinforcement mesh with an outer insulation; placing two strips of conductive metal material at the opposite ends of the outer reinforcement mesh; welding the two strips to the ends of the warp wires; and cutting each strip by means of through cuts so as to create spaces and hence obtain from the strip a succession of collectors that are separate from one another.

Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.

An optimized protection against ice on the inner and outer faces of an aircraft engine nacelle air intake with the air intake including an outer face and an inner face meeting at a line at the longitudinally extreme, called extremum line, an acoustic panel being installed on the inner surface of a part of the inner face. An elimination system based on vibration of the ice formed is put in place on at least a part of the outer face and an ice formation prevention system using a hot fluid is put in place on at least a part of the inner face and either an ice elimination system or an ice formation prevention system using a hot fluid is installed on the inner face and on the outer face, a marking line marking the boundary between the two systems.