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.

In one example embodiment, a filter condition measurement device features an engine data repository, one or more sensor units, and a measurement unit. The measurement system is configured to identify a first flow value corresponding to a sensed engine power value from the engine data repository, determine a filter coefficient for the filter as a function of the first flow value and the sensed delta-pressure value; identify a second engine power value from the plurality of stored engine power values and a second flow value corresponding to the second engine power value; and determine a second delta-pressure value for the air filter as a function of the filter coefficient and the second flow value.

A double-action pusher centrifuge separates a mixture into solid cake and liquid. The pusher centrifuge includes a screen drum rotatable about an axis and in which a pusher base device is arranged to be movable along the axis of rotation. The solid cake is displaced by an outer ring region of the pusher base device. A plurality of axial passage openings are disposed in the outer ring region and connect front and rear regions of the screen drum. A feed unit is arranged at an inflow disk such that the mixture can be introduced via the feed unit and the inflow disk into empty space on the screen drum on displacement of the solid cake. An inflow gap applies the mixture into the empty space, and is between an inflow edge of the inflow disk and a pusher base plate of the pusher base device with an inflow region.

An inertial particle separator for an aircraft engine inlet, including inlet, intermediate and bypass ducts. The intermediate duct extends generally transversally from the inlet duct to the engine inlet, and communicates with the inlet duct adjacent its downstream end. The bypass duct extends downstream from the inlet duct and intermediate duct, and defines an outlet communicating with the environment of the engine. A wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct. The engine side of the wall of the inlet duct defines an engine-side inlet air flow line of the inertial particle separator. A wall of the bypass duct intersects the wall of the intermediate duct closer to a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct.

A filtering assembly that receives an inlet air includes a modulation panel subassembly, an air filter subassembly downstream of the modulation panel subassembly, wherein the air filter subassembly is configured to discharge the inlet air from the filtering assembly, and an arm subassembly configured to move the modulation panel subassembly and to move the air filter subassembly. The air filter subassembly moves into and out of a flow of the inlet air.

An air filtering system having: an air box, which has at least one inlet opening and at least one outlet opening; and an air filter, which is arranged inside the air box. The air box has two opposite twin mounting openings, which are obtained in two parallel and opposite walls of the air box and are shaped to allow the air filter to be inserted and removed through each one of them. Two removable doors are provided, each having an outer panel configured to overlap a respective mounting opening to close the mounting opening and two inner appendages, which project perpendicularly from two opposite ends of the outer panel so as to be arranged on the two opposite sides of the air filter, when the door is coupled to the respective mounting opening.

An adaptive inertial particle separation system may include an active configuration and a passive configuration. The system may comprise an air-intake duct including an outer wall spaced apart from a central axis, an inner wall located between the outer wall and the engine rotation axis, an intake passage defined in part by the inner wall and the outer wall, and a splitter located between the outer wall and the inner wall. The system may further include a sensor operatively connected to the air-intake duct and operative to initiate at least one of the active configuration and passive configuration.

A fluid intake including first and second ducts and a particle separation spinner defining an interface between the first and second ducts is disclosed. Spinner includes flow passages passing from first duct side of the spinner to second duct side of the spinner and splitter bodies separating the flow passages. Flow passages and splitter bodies are arranged in thread-like screw manner about spinner. In use, the spinner is spun about an axis of rotation, axis and direction of rotation being such that, from static frame of reference with respect to first duct, splitter bodies and flow passages have a component of movement towards a main travel direction of a fluid flow incident towards spinner from first duct. Splitter bodies are arranged such that they oblige fluid in the fluid flow to follow a convoluted path if it is to pass from first duct to second duct via the flow passages.

Embodiments described herein provide for a compartment based inlet barrier for foreign object debris to an auxiliary power unit of an aircraft or watercraft. The apparatus is configured to fit within an inlet compartment of an auxiliary power unit and provides a particulate separator for fluid flow to the auxiliary power units using a porous pleated filter media having a corrosion resistant exterior frame and enables a minimal pressure differential throughout the apparatus while in use. The apparatus may further be releasably secured/unsecured using a plurality of fasteners which enable a user to readily assemble and disassemble.

A flow management system for delivering air to a heat load of an aircraft includes a cover having an opening for receiving and directing an airflow, and a duct defining a non-linear fluid flow path. The fluid flow path operably couples the opening and the heat load. A configuration of the fluid flow path reduces a velocity of the airflow therein while minimizing a pressure drop of the airflow.