A helicopter has an air inlet barrier filter (IBF) system including a guide rail extending axially along one side of a nacelle housing a helicopter engine. A filter panel is slidable along the guide rail for movement between a filtered position in which the filter panel covers an air inlet of the nacelle and an unfiltered position in which the filter panel uncovers a total surface area of the air inlet to provide for a fully unobstructed air flow to the engine.

An air inlet for an aircraft propulsion system nacelle includes an outer skin, an inner skin, a lip skin, and a forward bulkhead. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The forward bulkhead includes a first bulkhead portion and a second bulkhead portion. The first bulkhead portion and the second bulkhead portion are mounted to the outer skin. The first bulkhead portion and the second bulkhead portion are mounted to the inner skin. The first bulkhead portion includes a rigid body material and the second bulkhead portion includes a flexible body material.

A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis and axially from the front wall to the rear wall, and a second screen radially outward of the first screen and axially overlapping the first screen. An actuator is operable to move the first screen and the second screen relative to one another in one or more of a radial, axial and circumferential direction to shed ice from the inlet guard.

A screen for an air intake portion of a machine is provided. The screen includes an assembly of screen members that form a plurality of screen cells, wherein at least a portion of the screen cells define an irregular configuration.

A method of protecting aviation equipment. An aircraft is provided having an engine attached thereto. The engine has an engine inlet, a nose cone and a nozzle. The nose cone is operably mounted to the engine. The nozzle is mounted to the nose cone. An object in proximity to the engine inlet is sensed with a sensor. In response to sensing the object, the nose cone is moved from a retracted position to an extended position. In response to sensing the object, tubing provides a liquid to the nozzle and the liquid is emitted from the nozzle.

A fan blade airfoil and nose cone with leading edge fillet for debris deflection including a fillet formed in the nose cone and inserted into a pocket formed in the fan blade, the filet configured to create a deflection air stream; the deflection air stream being configured to manipulate a fan inlet air flow such that any debris entrained in a fan inlet air flow has a trajectory line directed away from a core flow of a gas turbine engine and toward a bypass flow of the gas turbine engine.

An example booster splitter includes an inner cylindrical structure; an outer cylindrical structure concentric with the inner cylindrical structure; an annular lip having an arc extending between the inner cylindrical structure and the outer cylindrical structure; a first protrusion at a first circumferential position on the annular lip, the first protrusion protruding axially from the annular lip and extending from the outer cylindrical structure to the inner cylindrical structure along the arc of the annular lip; and a second protrusion at a second circumferential position on the annular lip.

A method of directing particles entrained within an airflow disposed to enter a gas turbine engine of an aircraft is provided. The gas turbine engine includes a nose cone, a fan section, a compressor inlet, a compressor section, and a turbine section. The nose cone is fixed for rotation with the fan section. The method includes: providing an entrained particle removal (EPR) system configured to inject a fluid outward from the nose cone from a plurality of nozzles engaged with the nose cone, wherein the nozzles are spaced apart from one another around a circumference of the nose cone; and controlling the EPR system to inject the fluid from the plurality of nozzles into the airflow. The particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet.

An aircraft propulsion system includes an air intake and an air intake control system. The air intake includes an intake body forming an air passage. The air intake control system includes a flow control member disposed within the air intake, a blockage sensor having a sensing area directed to the flow control member, and a controller. The blockage sensor is configured to produce a signal indicative of an accumulation of foreign matter on the flow control member. The controller is configured to identify a presence or an absence of an obstruction condition of the flow control member and remove the foreign matter from the flow control member, in response to identifying the presence of the obstruction condition, by changing a state of the flow control member.

An example booster splitter includes an inner cylindrical structure; an outer cylindrical structure concentric with the inner cylindrical structure; an annular lip having an arc extending between the inner cylindrical structure and the outer cylindrical structure; a first protrusion at a first circumferential position on the annular lip, the first protrusion protruding axially from the annular lip and extending from the outer cylindrical structure to the inner cylindrical structure along the arc of the annular lip; and a second protrusion at a second circumferential position on the annular lip.