A control method for controlling an air intake system for an engine of a vehicle; the intake system has a main air intake coupled to an air filter provided with a heating device. The control method comprises the steps of: determining a pressure difference between upstream and downstream of the air filter; determining a variation speed of the pressure difference between upstream and downstream of the air filter by calculating the first derivative in time of the pressure difference between upstream and downstream of the air filter; and turning on and/or turning off the heating device based on the variation speed of the pressure difference between upstream and downstream of the air filter.

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.

An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.

A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.

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.

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.

A particle separator system for use with a turbomachine is provided. The particle separator system includes a first end, a second end opposite the first end, a main separator body extending between the first and second ends, the main separator body including at least one step configured to cause a fluid flow to turn up to 180 degrees, and at least one transversely oriented cyclone separator disposed within the main separator body and defining at least one of a swirling cylinder, a bent cylinder, and a conical volume.

A rotatable nacelle includes an engine inlet configured to receive air and an inlet air management system (IAMS). The IAMS includes a primary inlet configured to selectively allow air to flow into a duct associated with the engine air inlet via the primary inlet and a secondary inlet configured to selectively allow air to flow into the duct associated with the engine air inlet via the secondary inlet. The secondary inlet is configured to receive an air filter.

The invention relates to at least one air intake (2) in a cylindrical form extending outwardly from the engine (M) and providing air supply to the engine (M) in air vehicles, an inlet port (3) through which air supply takes place to the air gap (2), at least one first aperture (4) situated on the surface of the air intake (2), providing an uninterrupted air supply to the air intake (2) when the inlet port (3) is blocked, at least one rotary cylinder (5) having a radius larger than that of the air intake (2) and a nested configuration with the air intake (2) and mounted so as to be rotatable around the air intake (2), at least one second aperture (6) on the surface of the rotary cylinder (5), an open position (I) in which the first aperture (4) and the second opening (6) are opposed each other so that air is introduced into the air intake (2), a closed position (II) to which the rotary cylinder (5) is rotated from the open position (I) and in which air supply to the air intake (2) is prevented through the first aperture (4) and the second aperture (6), at least one first gear (7) situated on the rotary cylinder (5), an actuator (8) that triggers the first gear (7) and rotates it around the air intake (2) of the rotary cylinder (5), at least one second gear (9) which provides motion transmission between the actuator (8) and the first gear (7) and which is situated opposite the first gear (7), and at least one sensor unit (10) measuring the temperature, pressure, humidity and/or flow values of the air passing through the air intake (2).

The invention relates to a turbomachine (24) of the open rotor type or a turboprop engine comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake section (32) surrounding the central hub (30) and opening into a air supply main section (34), with the central hub (30) comprising a central trap (36) having an aperture (38) for trapping the foreign objects in an air flow entering the turbomachine (24), and an air recovery channel (48) having a discharge end (48a), through which said air recovery channel (48) opens into the main section (34), provided on the central hub (30).