The invention relates to a cradle (10) for an aircraft turbopropeller engine (12) of a substantially axial orientation, comprising a front arch (16) and a rear arch (18) extending transversely relative to said axial direction (A), said arches (16, 18) being open at their lower ends and connected to each other by at least one axial longeron (34) extending between said arches (16, 18), characterised in that the longeron (34) is arranged in an upper portion of the cradle (10) and is formed in a single piece with the front arch (16).

An air inlet system for an auxiliary power unit (APU) has an intake duct having a wall defining an inlet plenum and forming an inlet opening configured to direct air into the inlet plenum. The system further comprising a load compressor passage in fluid communication with the inlet plenum and leading to a load compressor of the APU; and a core compressor passage in fluid communication with the inlet plenum and leading to a core compressor of the APU. A deflector is provided in the inlet plenum between the inlet opening and the core compressor inlet to deflect at least part of particles carried by an incoming airflow away from the core compressor inlet toward the load compressor inlet.

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.

An aircraft includes a fuselage, an engine exhaust port extending through the fuselage, an air intake extending through the fuselage forward from, and adjacent to, the engine exhaust port, and an air cleaning assembly positioned over the air intake. The aircraft also includes a pressure recovery device including an outer wall positioned above the air cleaning assembly. A distance from a forward edge of the outer wall to the air cleaning assembly is greater than a distance from an aft edge of the outer wall to the air cleaning assembly. An inlet flow axis is defined normal to a cross-sectional flow area of the pressure recovery device at the forward edge, and is oriented upward at an acute angle relative to a longitudinal axis of the aircraft.

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.

An asymmetric inlet particle separator system (AIPS) includes a bifurcated duct system that defines an inlet for receiving inlet air. The bifurcated duct system includes a core air channel and a scavenge air channel and is configured to separate the inlet air into core air and scavenge air. The scavenge air channel includes a first plurality of turning vanes configured to turn the scavenge air in a first direction and a second plurality of turning vanes configured to turn the scavenge air in a second direction. The AIPS also includes an asymmetric scroll coupled to the scavenge air channel. The asymmetric scroll includes a first arm having a first arm length and a second arm having a second arm length that is different than the first arm length.

An inlet assembly for an auxiliary power unit for an aircraft, including a particle separator and a plenum having first and second inlets. A first duct configured to deliver air to an engine of the auxiliary power unit is in fluid communication with an outlet of the plenum. A second duct configured to deliver air to a compartment containing the auxiliary power unit is in fluid communication with the outlet of the plenum. The assembly is selectively configurable between a first configuration where the plenum is in fluid communication with the environment of the aircraft through the second inlet and through the particle separator, and a second configuration where the plenum is in fluid communication with the environment of the aircraft through the first inlet independently of the particle separator. An auxiliary power unit assembly and a method of feeding air to an auxiliary power unit assembly are also discussed.

An inlet assembly for an auxiliary power unit for an aircraft, including a duct configured to provide fluid communication from an environment of the aircraft to an inlet of an engine of the auxiliary power unit, and a filter received in and extending across the duct. The filter includes a first filter portion permeable to air, positioned across only part of the duct and defining a transverse edge in the duct; a second filter portion permeable to air and extending from the transverse edge to an end downstream of the transverse edge, and a collection member impermeable to water. The collection member extends between the downstream end and a duct wall. The first and second filter portions are non-parallel and the second filter portion and the collection member are non-parallel. An auxiliary power unit assembly and a method of feeding air to an internal combustion engine are also discussed.

An intertial particle seperator (IPS) including an intake air duct, a scavenge duct that shares an interior common wall with the intake air duct, a clean air duct, and a splitter. The splitter is configured to split a flow of intake air into a flow of scavenge air to pass through the scavenge duct and a flow of clean air to pass through the clean air duct. The IPS also includes a plurality of valleys on the intake air duct. The plurality of valleys includes a plurality of troughs and peaks along the interior common wall. In addition, each trough of the plurality of valleys extends along a direction of the flow of intake air.

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.