Abstract: An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the guard body, at least three, vertical, peripherally extending walls located between the base and the dome section, with successive ones of the peripheral walls having different peripheral dimensions, peripherally cylindrical, with the dimension increasing from the base toward the dome section. A plurality of air intake openings are defined in and between the peripheral walls with at least one dimensional size which is small enough to prevent having birds from being able to pass through the guard into the aircraft engine.

Abstract: An engine system including an air intake duct positioned upstream of an engine cylinder may include an ice ingestion feature for retaining condensation. An ice ingestion feature may include indents formed in the bottom of an air intake duct wall. As such, the ice ingestion feature may include compartments and/or grooves of varying depths, widths, and/or angles such that the ice retention rate may be based on the surface area of the compartment or grooves.

Abstract: A particle separator comprises a vessel, a fluid inlet, a fluid swirl passage, a scupper cavity, a first fluid outlet, and a second fluid outlet. The vessel includes a vessel sidewall extending between a vessel top side and a vessel bottom side. The fluid swirl passage includes a first passage end in communication with a fluid inlet disposed on the vessel top side. A second passage end is in communication with a vessel swirl cavity defined at least in part by an inner surface of the vessel sidewall. The scupper cavity includes a scupper entrance disposed along the inner surface of the vessel sidewall, and is spaced circumferentially apart from the second passage end. The first fluid outlet is in communication with the scupper cavity and disposed on the vessel bottom side. The second fluid outlet is disposed above the first fluid outlet in communication with the vessel swirl cavity.

Abstract: A retractable deflector to deflect birds and debris from an air intake duct of an aircraft jet engine. The duct has a forward opening for air receipt. The deflector includes a plurality of elongate members disposed on the duct in spaced relation to each other, each member having two end segments and a central segment disposed between the two end segments; and a plurality of guiding members, each mounted for movement along the perimeter of the duct and coupled to one end segment of an elongate member. The central segment of each elongate member extends between a pair of guiding members such that the elongate member is movable by a respective pair of guiding members between a retracted position and a deployed position in front of the duct. When in the deployed position, the central segments are situated to impede the ingress of debris into the duct.

Abstract: An environmental defense shield includes symmetric airfoil-shaped vanes contributing to and positioned around a plenum space and positioned in front of a turbine engine. An annular band stiffener is set into the vanes, which projects forward in a diminishing size, the vanes merging together to create or attaching to a solid nose. The environmental defense shield serves to protect the engine from debris while also smoothing airflow into the engine.

Abstract: A bird strike prevention device for covering an air intake of a jet engine of an airplane includes a plurality of stays arranged to form a conical shape as a whole; and a joining portion configured to connect the plurality of stays to each other on an apex side of the conical shape. The plurality of stays is mounted on the jet engine near an outer edge of the air intake at a base of the conical shape. An axis of the conical shape coincides with a rotation axis of the jet engine. The number of the stays included in the plurality of stays is determined based on a minimum size of target birds to be prevented from striking the jet engine.

Abstract: A non-fouling, bypass filter is disclosed. The filter is formed of a tapered structure having particulate material filtering properties. The tapered structure has an open base and a closed top, with its exterior surface being exposed to a gas/fluid stream to be filtered. A gas/fluid stream generating device generates a gas/fluid stream that is drawn into the tapered structure's interior and that is filtered due to the particulate material filtering properties of the tapered structure. The external profile of the conically shaped structure is adapted to cause a plurality of gas/fluid streams from the ambient gas/fluid to flow against the exterior surface of the tapered structure to prevent the building up of particulate material on the exterior surface.

Abstract: An airfoil (10) having a main structure (15) including at least one spar (16) and a front structure (20) forming a leading edge (21), said airfoil (10) having an empty space (25) between said main structure (15) and said front structure (20). The airfoil (10) includes a rigid deflector member (30) in said empty space (25), the deflector member being fastened to the main structure (15), said deflector member (30) having a sharp edge (31) facing towards said front structure (20) in order to deflect an external obstacle impacting against said front structure (20).

Abstract: An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: An energy efficient and quiet air cooling system for a building structure is provided. The air cooling system includes an evaporator system mounted in the wall of the building, a remotely mounted fan, an air intake, and a sound and heat insulating duct. The fan is mounted in the attic and configured to draw air from the living area of the building through the sound insulating duct with sufficient power to create a negative static pressure in the living area. The negative static pressure in turn causes outside air to flow through the evaporator system which removes heat from the outside air. The cooled air is in turn drawn into the building and pulled into the attic through the duct and expelled through the attic.

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: A filter system includes a filter assembly having an interior, an end defining a bypass opening, and another end for coupling to an air intake of an aircraft engine to permit intake air from the interior to enter the air intake. The filter system includes a bypass closure movable relative to the filter assembly between at least a first position and a second position. The bypass closure substantially covers the bypass opening in the first position to inhibit intake air from entering the interior through the bypass opening. The filter system includes an actuator coupled to at least one of the filter assembly and the bypass member to cause relative movement of the bypass closure between the first and second positions.

Abstract: Embodiments of the present invention provide an inlet particle separator for a gas turbine engine having an inlet flow path, a scavenge flow path, a core flow path, and a flow splitter disposed between the scavenge and core flow paths. A plurality of grooves may be disposed about an inner surface of a wall of the separator within the inlet flow path.

Abstract: This invention relates in general to a fixed guard(s)/cap(s) and/or screen(s) apparatus (single and/or double formation) shall effect multiple aspects for example the nacelle and inlet for numerous craft, jets, turbojet, turboprop and turboshaft engines—(Helicopters and other VTOL aircraft) such as power plants or the like. This apparatus contains the rotational system(s) which may be applied to the engine shaft attached apparatus and/or pole that allows the mechanism to function by self-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 gaseous intake cavity, centrifuge, chamber, manifold and processes—static free and or purification chamber, and a particle collector without limiting engine thrust.

Abstract: A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, a recorder to record the sound of the impacts, an analyzer to analyze the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavorable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store 68 sounds of impacts and if the comparator determines that the sound of the impacts of particles matches one or more stored sounds of impacts, a signal is sent to a control system for the gas turbine engine to adjust the operation of the gas turbine engine such that it operates in a safe mode of operation.

Abstract: An inlet protection system for filtering air prior to entry into an air intake of an engine of an aircraft includes interchangeably a particle separator panel and a barrier filter panel. The barrier filter panel is adapted to be mounted conformal to the contour of the aircraft and to be interchangeable with the particle separator panel. The particle separator panel has an outer skin and a plurality of particle separators. The outer skin has an opening disposed along a portion of it to discharge filtered particles from within the removable panel directly outward therefrom.

Abstract: One embodiment of the present disclosure is a unique particle separator. Another embodiment is a unique aircraft. Another embodiment is a unique inertial particle separator. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft, engines and particle separators for aircraft and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present disclosure will become apparent from the description and figures provided herewith.

Abstract: A system for preventing foreign objects from entering an air unit of an aircraft is provided including a reverse J-tube mounted to a wall of the ram air header. The first end of the reverse J-tube defines a portion of a cool fluid flowpath. The ram air header also includes a particle separator that is removably mounted to the first end of the reverse J-tube. The particle separator prevents foreign objects from entering the cool fluid flowpath. The particle separator has a generally conical shape. An airflow, opposite the direction of the cool fluid flowpath removes foreign objects from a surface of the particle separator.

Abstract: A foreign object damage protection system comprises a sensor for detecting a foreign object, a fluid in a reservoir, a means for dispensing the fluid, the means for dispensing the fluid in communication with the reservoir, and a control unit, whereby when the sensor detects a foreign object, the control unit causes fluid to be dispensed from the reservoir through the means for dispensing and towards the foreign object. The sensor is attachable to one or more locations on an aircraft, such as a wing, nose, windshield, fuselage or tail. The sensor can be a radar sensor, weather radar sensor, weather radar sensor modified to detect objects at short ranges, infra-red sensor, forward-looking infrared sensor, a light detection and ranging sensor, motion sensor, thermal sensor, or video sensor. The system provides a way to protect an aircraft from striking foreign objects, such as birds, in the path of the aircraft.

Abstract: A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine.

Abstract: A particle separator includes a first housing and a second housing. The first housing extends along an axis from an open proximal end to an open distal end. The second housing has a closed proximal end disposed adjacent the open proximal end of the outer housing. The second housing extends from the closed proximal end into the first housing along substantially a same axis as the axis of the first housing. The second housing has one or more passages disposed at a distance from the closed proximal end of the second housing. Additionally, the one or more passages are disposed within the first housing at a distance from the open proximal end thereof.

Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Abstract: A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: The Debris Intrusion Shield for Jet Engine Applications is a prolate hemispheroid metallic assembly installed at the intake of a jet engine. The assembly is designed and intended to limit or prevent the intrusion of solid or semi-solid objects into the engine intake while on the ground or in-flight. All elements of the assembly are arrayed symmetrically about the longitudinal axis of the engine. The assembly is constructed of four basic parts. Tubing is positioned as a radial array about the engine circumference, and serves as the primary debris deflection element. The engine mounting collar serves as the aft point-of-attachment of the assembly to the engine nacelle, and as the aft mounting point for the radial array of tubing. The forward mounting fixture serves as the forward point of connection for the tubing elements. The forward mounting fixture cover serves as a protective cover for the electrical anti-icing elements located at the forward surface of the forward mounting fixture.

Abstract: A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.

Abstract: The turbojet engine inlet and exhaust covers are permanently installed at the inlet and exhaust outlet or nozzle of an aircraft turbojet engine installation. The covers preclude the entrance of small animals, windblown debris, snow, and/or other contaminants into the engine inlet or exhaust while the airplane is inoperative. The covers have an iris-type shutter configuration, each cover having a plurality of leaves pivotally attached to a circumferential stationary housing that is attached to the engine or nacelle. A rotary ring is rotated through a small arc to pivot the shutter leaves inward and outward to close and open the engine opening. The rotary ring may be driven by an electric motor, or by hydraulic or pneumatic power. The system may be automated to close according to engine temperature after flight, and/or to open upon initiation of the engine start sequence for the aircraft.

Abstract: A jet engine air intake guard system wherein direct axial air flow into an engine during takeoff and landing may be temporarily closed off while air intake is provided laterally through screened air intake ports located on a cylindrical housing that extends forward of the conventional air intake cowling openings.

Abstract: A filtration system for a gas turbine engine includes an inlet main body which defines an inner inlet fairing section and a bellmouth inlet faring section transverse thereto. An Engine Air Particle Separator (EAPS) is mounted adjacent to the inlet main body to define a plenum therein. A particulate laden airflow is filtered by the Engine Air Particle Separator (EAPS) to produce a substantially filtered airflow. The substantially filtered airflow is communicated into the plenum, through the bellmouth inlet faring section and into a gas turbine engine.

Abstract: A flow divider (1) for a fan engine which forms an annular leading edge (4) simultaneously on the outer circumference of an annular core air duct and the inner circumference of an annular secondary air duct, protrudes into the fan airflow and has an aerodynamic profile. In order to avoid blockage of the core air and/or secondary air ducts in the event of destruction or detachment of the flow divider (1), the flow divider features separable parts (6) which, whatever their orientation, are capable of passing the vane passages of the core air duct and the secondary air duct.

Abstract: A retractable deflector to deflect birds and debris from an air intake duct of an aircraft jet engine. The duct has a central longitudinal axis and a forward opening for air receipt. The deflector includes a plurality of elongate first support members disposed on the duct having leading ends which extend from a perimeter of the opening, mounted for movement to extend and retract the leading ends. A second support member is coupled to these leading ends to retain them in spaced relation. The second support member is extendible in length and configured to hold the leading ends of the first support members sufficiently close together to cause the first support members to deflect at least one of a bird and debris when deployed, and to allow the leading ends to maintain a spaced-apart relation along a line which approximately corresponds to the perimeter of the duct when retracted.

Abstract: A bird deflector and air replacement system for a jet engine, the bird deflector being conical or arcuate in shape as formed by suitable longitudinal and lateral interconnected bars, and the air replacement apparatus being one of a frustum or a selectively perforated tube or a modified cowl with cooperating external spaced-apart channels or openings formed therearound for directing additional air into the mainstream of the jet engine inlet. The system may be manufactured as an aftermarket add-on, or it may be manufactured as original cowl equipment for respective jet engine models.

Abstract: A radial air intake device for an engine or a power unit that includes a ring-shaped filter for covering the radial air intake. The ring-shaped filter includes a first fixed part and a second mobile part which is movable with respect to the first fixed part through actuator elements, from a filtering position in which the whole radial air intake is covered by the ring-shaped filter, to a bypass position in which the second mobile part uncovers at least partly the radial air intake.

Abstract: A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine.

Abstract: The disclosure relates to a modular waste liquid separator and collector device, comprising component modules. A first module comprises a support structure, a second module comprises a droplet separator connectable to said support structure, and a third module comprises a waste liquid collector. The component modules are individually portable, and are assembled at the point of use.

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.

Abstract: A jet engine intake deflector system for preventing foreign objects from entering the intake of a jet engine. The jet engine intake deflector system generally includes an air intake frame, a plurality of fins and a deflection member. The air intake frame is generally comprised of a plurality of laterally extending outer supports arranged at equidistance from each other in a substantially circular configuration around a center support. Each fin is generally comprised of a flat plate, wherein a front end of each fin is attached to the deflection member and a rear end of each fin is attached to the air intake frame. The free end of the air intake frame is generally welded directly onto a jet engine to protect its intake from foreign objects, such as birds. Upon striking a foreign object, the deflector member will direct the foreign object out and away from the jet engine intake.

Abstract: An energy efficient and quiet air cooling system for a building structure is provided. The air cooling system includes an evaporator system mounted in the wall of the building, a remotely mounted fan, an air intake, and a sound and heat insulating duct. The fan is mounted in the attic and configured to draw air from the living area of the building through the sound insulating duct with sufficient power to create a negative static pressure in the living area. The negative static pressure in turn causes outside air to flow through the evaporator system which removes heat from the outside air. The cooled air is in turn drawn into the building and pulled into the attic through the duct and expelled through the attic. The fan expels warm air into the attic, creating a positive pressure environment which causes the warm air to be expelled from the attic through natural vents.

Abstract: A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat

Abstract: A bird deflector and air replacement system for a jet engine, the bird deflector being conical or arcuate in shape as formed by suitable longitudinal and lateral interconnected bars, and the air replacement apparatus being one of a frustum or a selectively perforated tube or a modified cowl with cooperating external spaced-apart channels or openings formed therearound for directing additional air into the mainstream of the jet engine inlet. The system may be manufactured as an aftermarket add-on, or it may be manufactured as original cowl equipment for respective jet engine models.

Abstract: A filtration system for a gas turbine engine includes an inlet main body which defines an inner inlet fairing section and a bellmouth inlet faring section transverse thereto. An Engine Air Particle Separator (EAPS) is mounted adjacent to the inlet main body to define a plenum therein. A particulate laden airflow is filtered by the Engine Air Particle Separator (EAPS) to produce a substantially filtered airflow. The substantially filtered airflow is communicated into the plenum, through the bellmouth inlet faring section and into a gas turbine engine.

Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Abstract: An inertial inlet particle separator system for a vehicle engine includes an inertial inlet particle separator and an adjustment mechanism. The separator includes a fluid inlet coupled to a scavenge channel and to a clean channel such that a first amount of fluid passing through the fluid inlet enters the scavenge channel and a second amount of fluid passing through the fluid inlet enters the clean channel. The scavenge channel is defined by a first wall and a splitter, and the clean channel is defined by a second wall and the splitter. The splitter and the second wall are stationary with respect to each other. The adjustment mechanism is coupled to the inertial inlet particle separator and configured to adjust a size of the scavenge channel. Although not necessarily, the adjustment mechanism may also be coupled to the scavenge fan speed.

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 inertial separator comprising a tubular body, the tubular body comprises a composition comprising a polymer selected from the group consisting of a cyclic olefin polymer and a cyclic olefin copolymer, and, a polyhedral oligomeric silsesquioxane and/or a flame retardant and/or an anti-static additive, is disclosed.

Abstract: A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat

Abstract: An intake duct for a compressor comprises an inlet and an outlet means. The duct has a serpentine path. The outlet means comprises a first outlet and a second outlet. The duct further comprises at least one grille member configured to prevent the passage of objects over a predetermined size which is positioned in the duct out of the line of sight when viewed through the inlet. The duct is shaped such that in operation objects passing through the at least one grille member greater than a predetermined mass are directed towards the first outlet and the remainder of the objects are directed towards the second outlet. The first outlet leads overboard and/or to a trap and the second outlet leads to a compressor.

Abstract: An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating sine-wave ring is used to activate and move a plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere.

Abstract: A bird collision prevention device with a plurality of circular interior support members with decreasing diameters concentrically disposed along an axis, a plurality of outer ribs welded tangentially to the circular interior support members forming a like conical shape mesh body, a plurality of bolts or latches securable to the circular interior support member with the largest diameter and the cowling, and wherein the mesh body is secured to the cowling of the turbine engine enabling a tapered end of the mesh body to extend away from the turbine engine.