A particle separator system for a turbine engine having an engine inlet. The particle separator system includes an inlet particle separator located within the engine inlet and configured to remove particles from an incoming airflow. The particle separator system also includes a barrier filter located within an enclosure of the turbine engine downstream of the inlet particle separator, the barrier filter being configured to intercept particles not scavenged by the inlet particle separator.

Air filtration assemblies configured to provide instant detection of particles and/or improve particle filtration are disclosed. The assemblies may include an air inlet duct in fluid communication with a compressor of a gas turbine system. The air inlet duct may include an inlet for receiving intake air including intake air particles, and an outlet positioned opposite the inlet. The assembly may also include a plurality of vane filters at the inlet, an array of fabric filters positioned in the air inlet duct, downstream of the vane filters, and a silencer assembly positioned in the air inlet duct, downstream of the fabric filters. Additionally, the assembly may include an electrostatic component positioned in the air inlet duct, downstream of the fabric filters. The electrostatic component may be configured to charge the intake air particles that pass through the vane filters and the fabric filters.

An air intake including an air duct inside an aircraft, an inlet at one end of the air duct, a flap door and driving mechanism that moves the flap door between closed and open positions. The flap door includes a barrier filter configured to filter an incoming airflow into the air duct, and wherein the driving mechanism is configured to pivot the flap door about a first end of the door.

A system that filters airborne particles when the aircraft is in a dusty environment and is disengaged when the aircraft is flying up and away from the dusty environment.

A checking method for checking a power plant of an aircraft, the power plant comprising at least one engine and an air inlet for feeding said at least one engine with air, the power plant including a cloggable filter filtering the air upstream from the engine. An aircraft power check is performed by: determining, in flight or on the ground, the current power actually being developed by the engine without making any allowance for any power losses resulting from the engine being installed in the aircraft or from a level of clogging of the filter, the aircraft power check being considered as being successful when the current power is greater than or equal to a guaranteed minimum power.

An inertial particle separator (IPS) for a gas turbine engine, has: inner and outer walls extending about a central axis, an inlet defined between the inner and outer walls and oriented axially; swirling vanes extending at least radially between the inner and outer walls and circumferentially distributed around the central axis, the swirling vanes configured for inducing a circumferential component in an airflow flowing between the swirling vanes; a plenum between the inner and outer walls downstream of the swirling vanes, the plenum circumferentially extending about the central axis, the outer wall converging toward the central axis in a direction of the airflow; and a splitter radially between the inner and outer walls downstream of the plenum and circumferentially extending around the central axis, a particle outlet radially between the splitter and the outer wall, an air outlet radially between the inner wall and the splitter.

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.

A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC).

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 inlet particle separator system includes a shroud section and a hub section that is at least partly surrounded by the shroud section. The hub section is spaced apart from the shroud section. The inlet particle separator system also includes a flow passageway with an air inlet defined between the hub section and the shroud section. The flow passageway branches downstream of the air inlet into a main passage and a pre-cleaner passage. The main passage is defined between the hub section and the shroud section. The pre-cleaner passage includes a pre-cleaner inlet and extends at least partially through the hub section. Furthermore, the system includes a splitter that divides the main passage into scavenge and engine flow paths. The pre-cleaner inlet is partly defined by a first surface of the hub section. The first surface faces substantially in an upstream direction toward the air inlet.