Abstract: A deflector for an aircraft engine comprises a screen attached to a base, a connector connecting the base and the engine, a mechanism to limit the movement of the connector and base, a spring that has two ends, one end being attached to the base inside surface, the spring extending past the base, and the spring's other end is positioned proximate the screen; and a shock absorbing means attached to the base, and connects the base with the engine, whereby when a foreign object contacts the deflector with a force sufficient force to move the spring and the shock absorbing means, the screen, the spring and the shock absorbing means are urged towards the engine, the movement of the screen and the spring being controlled by the shock absorbing means and the limiting mechanism, preventing the foreign object, such as a bird, from entering the engine.

Abstract: The system for inertial particle separation removes particulate matter, such as sand, from an air stream, such as that drawn into a turbine engine. The system includes first and second walls spaced apart and positioned within a housing of the turbine engine. The first wall is in the form of an airfoil with variable geometry. An annular air flow path is defined between the first and second walls. The air flow path leads inwardly from an ambient inlet and turns to an outlet. A splitter member is positioned between the first and second walls. A scavenge flow path is defined between the splitter member and the first wall. An inlet thereof is in communication with the ambient inlet, and a filtered flow path is defined between the splitter member and the second wall. The splitter member is also in the form of an airfoil having a variable geometry.

Abstract: A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized. The material may have a surface that will sit with at least a component parallel to an axial centerline of a gas turbine engine that is to receive the collection material. The material surface may also have a component which is generally perpendicular to the axial centerline. The material may be placed in a gas turbine engine upstream of the turbine section, and downstream of the combustion section. Moreover, the collection material may be placed such that there is cleaner air flow radially inwardly of the collection material, and heavier dirt-laden air passing along the collection material such that impurities can be collected.

Abstract: An inlet barrier filter system for mounting on an aircraft to filter air prior to intake into an engine of the aircraft includes a frame having at least two curved frame members defining an opening. A filter element has a curved inward face and is received in the opening of the frame. The filter element includes filter media having pleats. A comb is attached to the frame and includes spaced-apart teeth that support the pleats. The comb is curved to generally conform to the curved inward face of the filter element.

Abstract: A particle separator which broadly includes: an inner wall, an outer wall and a splitter, wherein the inner and outer walls define an air intake passageway, and wherein the splitter is positioned between the inner and outer walls so as to define a scavenge air flow passageway connected to the intake passageway and a main air flow passageway connected to the intake passageway; the inner wall having a humped-shaped portion between the intake passageway and the main air flow passageway; the humped-shaped portion having a peak and a radius of curvature at any point on the hump-shaped portion of the inner wall after the peak corresponding to a degree of curvature of from about 30 to about 60 degrees; and a boundary layer control mechanism for providing active boundary layer control along the inner wall after the peak and within the main air flow passageway. Also provided is a method for providing active boundary layer flow control along the inner wall after the peak and within the main air flow passageway.

Abstract: A system for use with an inlet of a gas turbine through which an airflow toward the gas turbine proceeds is provided and includes a first self-cleaning stage to remove dust, snow and ice from the airflow, a second water tight stage, disposed downstream from the first stage, to prevent aerosol droplets and aqueous solutions of deliquesced particulates, which include at least portions of the dust not removed by the first stage and which are re-released into the airflow from the first stage, from proceeding along the airflow and to remove solid particulates not removed by the first stage from the airflow, and a third water removal stage, disposed downstream from the second stage, to remove from the airflow aerosol droplets leaking from the second stage.

Abstract: ducted air flow vehicle that includes a fuselage having a longitudinal axis, supporting at least one air flow duct and a prime mover arranged to force surrounding air into the duct through an inlet at an upper end of the duct with normally symmetrical airflow streams, thereby creating a lift force directed substantially along a duct axis; a plurality of vanes extending across the inlet, substantially parallel to the longitudinal axis; and wherein one or more groups of the vanes are selectively pivotable to align with adjacent abnormal asymmetrical airflow streams.

Abstract: To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

Abstract: An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes an assembly for filtering air which is mounted in advance of the engine, and a duct for delivering air from the assembly to the engine. A sealing system is provided which prevents entry of unfiltered air while simultaneously permitting movement of the engine relative to adjacent parts of the airframe as engine power setting varies. The seal is protected from high pressures in the duct which can occur in operation of the engine.

Abstract: An inlet plenum for coupling airflow from a radial airflow inlet to an axial compressor inlet for a compressor comprises a perforated inlet (PI) baffle that comprises a generally cylindrical baffle that circumscribes the compressor inlet and a plurality of apertures, each aperture perforating the baffle to pass the airflow from the radial airflow inlet to the compressor inlet and a plurality of stagnation vanes, each stagnation vane comprising a generally arc-shaped vane that extends proximate the PI baffle to establish an approximation of stagnant flow around the entire PI baffle to reduce flow distortion of the airflow between the radial airflow inlet and the axial compressor inlet.

Abstract: The strainer comprises an unitary body having a main section and a collar section located around the main section. The collar section has a substantially outwardly-projecting portion located around the main section and an upstream projecting portion located around the substantially outwardly-projecting portion.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: A particle separator for use in connection with a gas turbine engine is disclosed. The particle separator extends circumferentially less than 360 degrees between a first end and a second end. In one embodiment, an inner scavenge conduit is spaced radially inward from an outer scavenge conduit. An inlet can be located between the outer scavenge conduit and the inner scavenge conduit and adapted to receive airflow. A plurality of separated airflow paths can be located between the inner and outer scavenge conduits. The outer scavenge conduit and the inner scavenge conduit can be adapted to receive particles separated from the inlet airflow as the inlet airflow passes along the curved separating portion.

Abstract: An inlet barrier filter system for an aircraft engine includes a filter panel (35) including filter media for filtering air prior to intake (15) into the engine. The filter panel has a forward edge (F). The system further includes an actuator for selectively pivoting the panel to form an opening around the panel for allowing air to bypass the filter. The opening is rearward of the forward edge of the filter panel.

Abstract: A turbomachine front portion includes an internal support shroud for the fan outlet guide vanes, and a flow splitter fairing from which a primary duct and a secondary duct originate. The front portion includes at least one deflector system configured to prevent/limit the ingress of hailstones inside the primary duct, the system including at least one deflecting surface together with an actuator for moving the surface from a retracted position to a deployed position for deflecting the hailstones, the system being mounted on the shroud such that, in the deployed position, a downstream end of the surface is situated upstream of the splitter fairing.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: An air intake (2) for a turbine engine, and a method implemented by the air intake (2) are disclosed. The air intake (2) is provided with a filter system (10) including foldable filter elements (11), arranged at the inlet section (3) of the air intake (2). In addition, the filter system (10) includes control elements (11) that exert a force along a first direction (Y) on the free end (11?) of the foldable filter elements (11) to adjust the filtering power of the filter system (10), guide members (12) of the filter system (10) serving to guide the movement of the free end (11?) induced by the control elements (13).

Abstract: An air/oil separator for use in a gas turbine engine includes a centrifugal separation stage in fluid communication with a downstream electrostatic separation stage. The centrifugal separation stage rotationally drives an electric generator to power the electrostatic separation stage.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine th'rust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes a filtering unit having barrier filter panels attachable to a mounting frame. The filter panels are interchangeably usable. A juncture between first and second filter panels and the mounting frame is located at a region of relatively lower quantity of intake air flow. The juncture includes lugs on the filter panels which facilitate interchangeability. An opening above the filtering unit permits easy installation and removal of filter panels.

Abstract: An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes a filtering unit having barrier filter panels attachable to a mounting frame. The filter panels are interchangeably usable. A juncture between first and second filter panels and the mounting frame is located at a region of relatively lower quantity of intake air flow. The juncture includes lugs on the filter panels which facilitate interchangeability. An opening above the filtering unit permits easy installation and removal of filter panels.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: A particle separator for separating particles and/or materials entrained in a flow of air is disclosed. The particle separator includes an annular inlet defined by an outer shroud and an inner shroud. An upper forward flow divider and a lower forward flow divider is disposed within the annular inlet. A first and second radially spaced annular flow divider is adapted for directing said flow of air into at least a first, second, third and fourth flow passageway. At least four curved flow splitters are utilized for separating particles and/or materials entrained in the flow of air as it passes through the first, second, third and fourth flow passageways.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: An engine inlet air particulate separator that uses zero mass active flow control devices, and methods of using the same, are provided. The separator has a separator body that has an arcuate portion with a bight region. The separator body may have an angle ? between centerlines in the range from about 115° to about 85°. The separator body separates into a bypass conduit and a primary air conduit, separated from each other by a splitter, downstream from the bight region, which is in fluid communication with the arcuate portion. A zero mass active flow device is in fluid communication with a third region of the separator body which is located proximate a point where the air stream would otherwise have separated from an inner wall of the particle separator.

Abstract: An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes an assembly for filtering air which is mounted in advance of the engine, and a duct for delivering air from the assembly to the engine. A sealing system is provided which prevents entry of unfiltered air while simultaneously permitting movement of the engine relative to adjacent parts of the airframe as engine power setting varies. The seal is protected from high pressures in the duct which can occur in operation of the engine.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement, without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: An adapter for use with a low volume PUF sampler is described. The adapter is affixed over the open end of a PUF (polyurethane foam) sample cartridge. Sample tubing is affixed to an aperture in the adapter, and the free end of the sample tubing is then positioned at a desired sample location such as within an aircraft interior. As a vacuum is applied to the PUF cartridge, the adapter allows air collected at the sample point to pass through the tubing and through the interior of the PUF cartridge while preventing air surrounding the PUF cartridge from being drawn into the PUF cartridge except through the sample tubing. In this manner the sample point of a desired air sample can be selected at a point remote from the PUF cartridge. Additionally, use of multiple PUF cartridges and adapters allows the simultaneous collection of separate air samples.

Abstract: A snow filter for an airplane cabin air supply system is provided with a coned inlet screen which allows some air to pass through and some snow to be retained. The coned configuration diverts much of the air and snow toward a downstream conical retaining and collecting screen positioned toward the outlet of the snow filter. Snow is retained and collected at this point while air is able to pass through the screen. Downstream of the coned inlet screen and upstream of the conical retaining and collecting screen is an open air flow mid-portion that enables tortuous flow of air as the snow is directed toward the conical retaining and collecting screen in an annular collection volume. The outlet of the snow filter is provided with a contact sleeve that allows the snow filter to be fittingly received by a surrounding corresponding air duct. Thus a snow filter is provided that effectively separates snow from a flow of air while maintaining a clog-free path.

Abstract: This invention relates in general to a guard(s)/cap(s) and/or screen(s) apparatus (single and/or multiple formation) for the nacelle/air inlet for numerous jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL/VSTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) as well as the engine shaft attached apparatus and/or pole that allows the mechanism to function by auto induced movement,without limiting engine thrust. Additional security measures have been introduced to the guard(s)/cap(s) and/or screen(s) apparatus, which includes a centrifuge chamber/manifold for particle collector without limiting engine thrust.

Abstract: A particle separator for use with a turbine engine is arranged to divide a flow of air into a radially inner air flow and a radially outer air flow. The particle separator is further arranged to separate inner particles from the inner air flow to allow air from the inner air flow to enter the turbine engine without the inner particles and arranged to separate outer particles from the outer air flow to allow air from the outer air flow to enter the turbine engine without the outer particles.

Abstract: An intake shield (3) comprises a hollow chamber (4) which locates over the intake (2) of a gas turbine engine (1). The chamber (4) has one or more walls (5) which are pervious to air but impervious to vortices and debris.

Abstract: A jet engine comprises a housing having an inlet. An air net is located adjacent to the inlet cowl and configured by compressed air streams for adequately blowing foreign objects from entering the inlet.

Abstract: An attachment for the air intake of a gas turbine engine includes a plurality of particle separators. The particle separators cooperate to define an attachment axis and are spaced circumferentially about the attachment axis. Each particle separator includes a housing defining a separator axis, a first flow passage having at least a portion that is annular, an annular opening, and an annular second flow passage. The first and second flow passages are configured so that inertia of particles entrained in a stream of air flowing through the annular portion of the first flow passage tends to cause the particles to flow from the annular portion through the opening into the second flow passage to allow the stream of air to enter the engine flow passage free of the particles removed therefrom. The separator axes are parallel to and spaced apart from the attachment axis.

Abstract: A particle separator for use with a turbine engine is arranged to divide a flow of air into a radially inner air flow and a radially outer air flow. The particle separator is further arranged to separate inner particles from the inner air flow to allow air from the inner air flow to enter the turbine engine without the inner particles and arranged to separate outer particles from the outer air flow to allow air from the outer air flow to enter the turbine engine without the outer particles.

Abstract: An attachment for the air intake of a gas turbine engine includes a plurality of particle separators. The particle separators cooperate to define an attachment axis and are spaced circumferentially about the attachment axis. Each particle separator includes a housing defining a separator axis, a first flow passage having at least a portion that is annular, an annular opening, and an annular second flow passage. The first and second flow passages are configured so that inertia of particles entrained in a stream of air flowing through the annular portion of the first flow passage tends to cause the particles to flow from the annular portion through the opening into the second flow passage to allow the stream of air to enter the engine flow passage free of the particles removed therefrom. The separator axes are parallel to and spaced apart from the attachment axis.

Abstract: A particle separator for a gas turbine engine includes a housing defining an annular first flow passage, an annular first opening, and an annular second flow passage positioned in fluid communication with the first flow passage through the first opening. The particle separator also includes a plurality of first vanes coupled to the housing in the first flow passage and a plurality of blades positioned in the first flow passage for rotation about an axis of the particle separator in response to a stream of air flowing past the blades downstream of the first vanes to allow the blades to deflect particles entrained in the stream of air from the first flow passage into the second flow passage through the first opening.

Abstract: A filter for coalescing water and removing odor from air includes a water coalescing layer made of a synthetic fiber and an odor removal layer including an adsorbent material that operatively interfaces the coalescing layer. The coalescing and removal layers are shaped to receive and expel the air. Both layers can be supported by a frame and/or an outer support layer of polyester material.

Abstract: An air inlet assembly for bringing air to an auxiliary power unit mounted in the compartment of an aircraft. The assembly includes a duct extending from an intake contoured to conform to the to the aircraft fuselage to an exit coupled to the inlet plenum of the auxiliary power unit. A first door hingeably mounted to the aft side of said intake and moveable from an open position to a closed position where said first door lies flush against intake, said first door having a closing wall and two side walls and a second door hingeably mounted to the forward end of said intake, said second door having a plate with two inwardly extending walls, each of said inwardly extending walls hinged to one of said side walls so that the second door rotates with said first door. During ground operation air that would have swirled around the side walls of the first door thus generating inlet corner vortices are now blocked by the side walls of the second door.

Abstract: In accordance with the present invention, there is provided an aircraft engine air intake cover for use with an air intake which is characterized by an air velocity profile therewithin. The air intake cover is provided with an air induction plate which disposed across at least a portion of the air intake. The air intake cover is further provided with a multitude of air induction ducts. The induction ducts are disposed about and extend through the air induction plate. Each induction duct has a duct inlet, a duct outlet and a duct body interposed between the duct inlet and the duct outlet. The duct inlets each respectively define an effective inlet diameter. The duct bodies each respectively define a duct body length which is greater than the associated effective duct inlet diameter. The duct outlets each respectively define an effective outlet diameter greater than the effective inlet diameter for increasing the cohesiveness of the air velocity profile within the air intake.

Abstract: An integral inertial particle separator with a de-icing feature in the form of a bifurcated radial intake for a gas turbine engine with an outside wall of the radial intake disposed in contact with heated oil from the engine lubrication system. To discharge particle contaminated bypass air flow from the engine, the separator includes an annular bypass manifold in communication with the bypass duct with vacuum created by an exhaust driven jet air pump.

Abstract: The particle trap (15) that extends behind an elbow in the air flow stream (6) in a turbo-prop engine is delimited at the back by an end plate (12) to which intake housing suspension rods (10) supporting the front of the rotating shaft (2), are fastened. It is divided by suspension arms (11) which may be drilled (21) to restore the continuity of the annular chamber forming the trap. Therefore the intake housing suspension device extends through the trap. This type of trap makes use of the inertia of solid bodies carried by the air drawn in, and which could damage the engine blades, and to collect them.

Abstract: The present disclosure relates to systems and methods that use a hydrophobic medium to remove salt and moisture from the intake air of a gas turbine system. The disclosure also relates to systems and methods that use a two stage filtering process to remove particulate material, salt and moisture from the intake air of a gas turbine system. Particulate material is filtered from the intake air at a first stage air cleaner. Subsequently, salt and moisture are removed from the intake air at a second stage salt barrier located downstream from the first stage air cleaner. In certain embodiments, the second stage salt barrier uses a hydrophobic medium to remove salt and moisture from the intake air.

Abstract: A radial inflow centrifugal filter device for separating fine particulates from a fluid flow, including a rotatable plurality of hollow parallel disks mounted in spaced apart relationship and attached via spacers to a tube. The hollow drive tube is in flow communication with the interior hollow plenum of the disks which is at a lower pressure relative to the open space between the disks. Rotating the tube causes the disks to rotate. Particulate-laden fluid is allowed to enter the filter device at the perimeter of the rotating disks and experiences a change in momentum due to the interaction of boundary layers of fluid established on each side of every disk. The centrifugal force imparted to both the fluid and particulates causes them to be separated in opposite directions.

Abstract: A guard apparatus for the intake of a jet engine includes a generally conically shaped structure that has a plurality of concentric rings of gradually decreasing diameter beginning at a largest ring that affixes to the cowl of the jet engine and progressively smaller diameter concentric rings spaced toward the front end portion of the guard apparatus. The guard apparatus also includes a plurality of longitudinally extended rods each of which forms a structural connection with one or more of the plurality of concentric rings, the rods defining an acute angle with the central longitudinal axis of the guard. Overall, the front end portion of the guard is generally hemispherically shaped defining a generally convex front end portion of the guard apparatus. Each of the longitudinally extending rods is acircular in shape, providing a transverse section that includes a semicircular shaped rear portion and a pointed front portion.

Abstract: A gas turbine engine is disclosed having an air compressor and a generally annular combustion chamber, with a generally annular diffuser located between the compressor and the combustion chamber so as to direct air exiting from the compressor toward the combustion chamber. The diffuser has inner and outer walls and defines an exit which is located adjacent to an opening in an upstream wall portion of the combustion forming a dome cowl. The dome cowl divides the air emanating from the diffuser exit into a primary air stream passing through the opening and one or more secondary air streams which pass between the walls defining the combustion chamber and the walls of a casing enclosing the combustion chamber assembly. A guide is associated with the diffuser for directing water in the air passing through the diffuser away from the opening such that it will not pass directly into the combustion chamber.

Abstract: An inlet particle separator for a gas tubine engine, comprises, (a) an annular air inlet duct, (b) downstream of the inlet duct an annular obturating member having a continuous surface, the menber arranged to bifurcate the inlet duct into annular compressor and scavenge ducts, the compressor duct leading downstream to an engine compressor stage, the scavenge duct being located radially inwardly of the compresor duct and directed upstream thereof, and arranged to scavenge solid matter from the air flow through the inlet duct. The inlet duct is provided with an annular constriction at its downstream end extending radially inwards from a radially outer wall of the inlet duct.

Abstract: A method and apparatus are disclosed for treating ice and debris in a gas turbine engine. More particularly, a specially configured and slidable scoop is positioned between the booster exit and the compressor inlet in a gas turbine engine. An actuator mechanism can be coupled through a linkage to the scoop to position the scoop within the core path at low power conditions and retract the scoop from the core flow path at high power conditions.

Abstract: The invention relates to an air cleaner comprising a generally bell-shaped air cleaner housing and a generally frustoconical filter positioned concentrically within the housing. The housing has an air inlet at its small end and an air outlet at its large end for the flow of air generally axially into and out of the housing. The filter has a filter element coaxially juxtaposed the interior surface of the housing. The filter element is generally annular and has an upstream portion and a downstream portion. The downstream portion of a member supportably engages the upstream portion of the filter element. The upstream portion of the filter element has a diameter larger than the diameter of the member downstream portion. The member blocks the flow of air into the interior of the filter element and directs air axially along the exterior of the filter element. A downstream annular support piece engages the downstream end of the filter element.