A method for supplying air to an engine of an aircraft via an air supply system of the aircraft. A dynamic air intake vent of the system can be closed by a closure member that is movable between a closed position and an open position. A static air intake vent is equipped with a filter medium. During flight, the method comprises an unfiltered operating mode that comprises the following steps: positioning of the closure member in the open position, and, during a phase of forward travel of the aircraft, dynamic intake of a flow of air, then transfer of a first portion of the flow of air to the engine and a second portion of the flow of air to the filter medium in order to clean the filter medium.

An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.

A method for supplying air to an engine of an aircraft via an air supply system of the aircraft. A dynamic air intake vent of the system can be closed by a closure member that is movable between a closed position and an open position. A static air intake vent is equipped with a filter medium. During flight, the method comprises an unfiltered operating mode that comprises the following steps: positioning of the closure member in the open position, and, during a phase of forward travel of the aircraft, dynamic intake of a flow of air, then transfer of a first portion of the flow of air to the engine and a second portion of the flow of air to the filter medium in order to clean the filter medium.

A control system for controlling a shut-off valve of an aircraft. The shut-off valve is configured to open a bypass circuit that is initially closed. This circuit makes it possible to feed air to an aircraft engine without going via an air filter associated with an air intake. The control system comprises: a manual control member for controlling the shut-off valve, this member being actuatable manually so as to cause the bypass circuit to open; and a computer configured to compute a current value of a level of clogging TC of an air filter. The control system further comprises a comparator for comparing the current value of the level of clogging TC with a first threshold value TC1 and with a second threshold value TC2, and an alerter for generating a first sensory signal and a second sensory signal.

A gas turbine engine includes an intake device. The intake device includes a snorkel and a filter case. The snorkel includes a tubular body and an inlet aperture. The tubular body extends between a closed end and an open end opposite the closed end. The inlet aperture is formed through the tubular body proximate the closed end. The tubular body forms a first portion of a gas flow path for a bleed gas from the inlet aperture to the open end. The filter case is connected to the tubular body. The filter case extends between a first end and a second end. The filter case includes a sidewall extending from the first end to the second end. The sidewall surrounds a filter cavity. The filter case is configured to receive the bleed gas from the open end of the tubular body. The filter case and the snorkel form a unitary component.

An inertial particle separator (IPS) has: a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side; two inlet ducts extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; and a bypass duct communicating with the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another.

An air intake unit for an engine of an aircraft; the intake unit has: a tubular housing; a first inlet opening which is obtained through an outer wall of the tubular housing and through which external air can be taken in; an air filter which engages the first inlet opening; a second inlet opening which is obtained through the outer wall of the tubular housing and through which external air can be taken in; a shutter device which is coupled to the second inlet opening and is movable between a closed position, in which it closes the second inlet opening, and an open position, in which it sets the passage through the second inlet opening free; and an actuator, which moves the shutter device.

A particle separator includes a housing through which a flow stream is directed. A number of guide vanes are disposed in the housing. The guide vanes have a profile wherein the flow stream is guided to follow the profile. The guide vanes have a wall surrounding an open interior that defines a vane plenum. A plurality of through-holes extend through the wall of the guide vane. The through-holes are open to the flow stream and to the vane plenum. A duct connects with the vane plenum and is configured to discharge particles collected in the vane plenum.

An ejector driven scavenge system for a particle separator having a scavenge branch associated with a gas turbine engine includes at least one anti-icing circuit to receive an anti-icing fluid. The at least one anti-icing circuit is to be coupled to the particle separator. The ejector driven scavenge system includes at least one flow ejector bank to be coupled to the scavenge branch and fluidly coupled to the anti-icing fluid to direct the anti-icing fluid through the scavenge branch to drive air with entrained particles and water droplets from the particle separator.

An air intake system for an aircraft engine includes an air duct having an inlet port to provide fluid communication between the inlet port and the engine and a removable air filter assembly configured to interface with the inlet port of the air duct and a skin of the aircraft. The air filter assembly includes an air filter frame having an outer wall and an inner wall, the outer wall of the air filter frame forming an air filter slot. The air filter assembly also includes a bypass door forward of the air filter slot and an air filter insertable into the air filter slot. The bypass door is movable between a closed door position and an open door position, air flowing to the inlet port of the air duct via the air filter in the closed door position and bypassing the air filter in the open door position.