Abstract: An aircraft air-conditioning system (10) comprises an air-conditioning unit (12) that is connected by a main fresh-air line (16) to a mixer (18) in order to supply the mixer (18) with fresh air at a desired low temperature. A fresh-air branch line (20) that is connected upstream of the mixer (18) to the main fresh-air line (16) has a flow cross section that is smaller than a flow cross section of the main fresh-air line (16).

Abstract: The invention relates to a device (10) for heating an aircraft cabin and comprises a first hot air supply line (12) that leads to an air conditioning unit (14), a flow control valve (16) that is disposed in the first hot air supply line (12) upstream from the air conditioning unit (14), and a second hot air supply line (18) that branches off from the first hot air supply line (12) between the flow control valve (16) and the air conditioning unit (14) and bypasses the air conditioning unit (14). In order to assure air conditioning of the aircraft cabin in the event of a failure of the air conditioning unit (14) a third hot air supply line (20) branches off from the first hot air supply line (12) upstream from the flow control valve (16), which third hot air supply line (20) connects the first hot air supply line (12) to the second hot air supply line (18).

Abstract: An air exhaust device is equipped with a grid (10) that is connected to an aerodynamic surface of an aircraft, whereby the grid includes a number of openings that are delimited by separating zones that are arranged in the extension of the aerodynamic surface of the aircraft, whereby the device and the grid are characterized by a surface that makes possible the passage of the air called passage surface, characterized in that it includes at least one movable part so as to increase the passage surface of the device, in particular in the case of a malfunction, and in that the grid (10) has a passage surface that is determined as a function of the flow rate of air that is to be evacuated under the most restrictive conditions of a normal flight, in the absence of a malfunction.

Abstract: An air guide element (10) for an aircraft air conditioning system comprises a housing (12), which has an air inlet opening (14) and an air outlet opening (16). The air inlet opening (14) and the air outlet opening (16) are disposed in such a way and the housing (12) is shaped in such a way that air that is fed to the air guide element (10) through the air inlet opening (14), as it flows through the air guide element (10), is deflected at an angle of ca. 45° to 135° relative to the direction of the air flow through the air inlet opening (14). A cross-sectional area of flow of the housing (12) that is disposed at right angles to the direction of the air flow through the air outlet opening (16) is subdivided into at least two regions (18a, 18b, 18c).

Abstract: The invention concerns a cooling system for an aircraft with an air inlet (4) through which air from the environment of the aircraft enters a ram air channel (2), and an air outlet (6) through which air emerges from the ram air channel (2). A heat exchanger (10) is arranged in the ram air channel (2). A ventilation device (8) is in fluid communication with the ram air channel (2). Also connected to the ram air channel (2) is a distribution line (12) to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.

Abstract: A service apparatus for a transportation means comprises a first component in the form of an air shower with an air inlet and at least one air outlet, and a second component in the form of an illumination device. The first component and the second component are arranged essentially centrically in relation to each other, wherein one of the two components encloses the other component essentially in a ring-shaped manner. In this way an integral reading light with a forced-air nozzle, or an integral forced-air nozzle with a reading light, is implemented that uses little design space.

Abstract: A single housing is utilized to mount both an internal fan, and an external alternate flow passage closed by a check valve. The alternate flow passage is defined between an inner and outer wall of the single housing, while the fan is mounted within the inner wall.

Abstract: A supply channel is provided with an air distribution system for vehicles, in particular for aircraft. The supply channel includes, but is not limited to an elongated housing, a hollow profile extending in longitudinal direction of the housing, and at least one air shower that includes, but is not limited to an air inlet and at least one air outlet. A generated surface of the hollow profile includes, but is not limited to a multitude of perforation openings. The at least one is designed such that in a region of the air inlet it rests tightly against the generated surface of the hollow profile. Perforation openings that do not lead to an air inlet of an air shower can be sealed off by an adhesive film or foil that has been applied. The supply channel makes possible variable positioning of air showers along the longitudinal direction of the supply channel.

Abstract: An air supply device (10) for supplying conditioned air into an aircraft passenger cabin comprises an air duct (12) with an air inlet (18), which is connectable to a line system of an aircraft air conditioning system in order to supply conditioned air provided by the aircraft air conditioning system to the air duct (12), and with an air outlet (20), which is connectable to an interior of the aircraft passenger cabin in order to convey the conditioned air supplied to the air duct (12) by the aircraft air conditioning system into the interior of the aircraft passenger cabin. In at least a first portion (14) of the air duct (12) a first boundary wall (24) of the air duct (12) is formed by a portion of a luggage compartment housing back wall (26).

Abstract: The arrangement of the invention includes mobile means for blocking an air passage channel (10) which are controlled by an aerodynamic surface (20) provided in said air passage channel (10) and capable of generating a lift force (P) under the action of the external air flow (F) flowing through said air passage channel (10).

Abstract: An apparatus comprises an inlet capable of receiving air around a seat, a contaminant conditioning system, an outlet, and a fan system. The contaminant conditioning system may be capable of removing contaminants from the air to form conditioned air. The outlet may be capable of expelling the conditioned air around the seat. The fan system may be capable of drawing the air from a breathing zone through the inlet, moving the air drawn from the inlet to the contaminant conditioning system to form the conditioned air, and moving the conditioned air out of the outlet.

Abstract: A seal includes a main body portion having fingers that extend outward to seal against the sides of one or more flexible conduit sections. The seal embodies several features that minimize the effect of compressing the seal over extended use. In one embodiment, the seal include a tab that isolates compression forces from the fingers. Other embodiments, include a recessed hinge point between the fingers and the main body. Still other embodiments, incorporate a material that fills the region between the fingers.

Abstract: A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapted to receive atmospheric air. The outlets of the system turbine and the system compressor are fluidly connectable to the inlet of the compressor of the auxiliary gas turbine engine. A method includes providing compressed air from an aircraft to an inlet of a system turbine mechanically coupled to a system compressor. The method includes providing atmospheric air to an inlet of the system compressor. The method includes providing the inlet of the compressor of an auxiliary gas turbine engine with air from an outlet of the system turbine and with air from an outlet of the system compressor.

Abstract: Methods and systems for providing a depressurization alert. An example method includes receiving a cabin depressurization discrete signal, determining if the cabin depressurization discrete signal is valid, and issuing a cabin depressurization alert, if the cabin depressurization discrete signal was determined to be valid. In accordance with further aspects of the invention, a time delay is executed before the receiving, determining, and issuing steps are repeated. The cabin depressurization discrete signal is determined not valid if uncorrected pressure is not greater than a predefined altitude. The uncorrected pressure is a raw pressure value produced by a Pitot-Static system. Also, the cabin depressurization discrete signal is determined not valid if the aircraft's altitude above an intended runway is not greater than a first predefined value.

Abstract: When conditioned air is supplied in an aircraft, the conditioned air in which at least one of oxygen concentration and humidity is adjusted is generated in the aircraft. The generated conditioned air is blown via a plurality of air blow-off ports 40a disposed inside the aircraft cabin so that the conditioned air reaches face disposition regions of passengers H in a plurality of seat locations inside the cabin.

Abstract: A cabin pressure control system (CPCS) software control logic modification may boost the voltage applied to a motor when conditions are sensed indicating a combination of larger than normal cabin pressure and cabin rate error conditions. The motor may be part of an open-loop system for operating a butterfly valve that may regulate outflow from the aircraft cabin. The larger than normal cabin pressure and cabin rate error conditions may be an indication that the outflow valve is not responding in a normal manner, potentially caused by excessive loading to the motor or motor degradation. By boosting the motor voltage during excessive load conditions or with a degraded motor, CPCS performance and robustness may be improved.

Abstract: An exhaust system for an aircraft galley chiller is provided. The exhaust system includes a galley having a chiller that includes an inlet, a condenser fan inlet, a condenser fan outlet proximate to chiller inlet, and a first flow of air through the condenser, an air ventilation outlet conduit that includes a second flow of air therethrough, and an ejector pump. The ejector pump includes a first airflow inlet, a second airflow inlet and an airflow outlet, wherein the first airflow inlet is coupled in flow communication with the condenser fan outlet, the second inlet is coupled in flow communication with the air ventilation outlet conduit. As the second airflow increases, the first velocity increases in a direction away from the galley chiller facilitating a decrease in temperature at the condenser fan inlet.

Abstract: A method for manufacturing a wall of a thin-walled structure is described. The method includes receiving parameters for the wall and one or more stiffening features associated with the wall via a user interface, providing the parameters to a machine configured to fabricate the wall and incorporate the one or more stiffening features, the machine using a direct manufacturing process and operating the machine to integrally fabricate the wall and the one or more stiffening features.

Abstract: The invention relates to an aircraft air conditioning system with at least one fresh air supply line (14) for conveying fresh air into an aircraft cabin, wherein the fresh air is blown out into the aircraft cabin via at least one discharger (48). In order to form the system so as to save weight and costs, a cyclone unit (10) is disposed in the vicinity of the discharger (48), the unit having an inlet opening (12), which communicates with the fresh air supply line (14), an intake opening (28), through which air is sucked in from the aircraft cabin, and at least one outlet opening (24), which communicates with the at least one discharger (48), wherein a cyclone flow is produced in the cyclone unit (10) during operation of the aircraft air conditioning system by means of the fresh air serving as incoming air and further wherein air is sucked in through the intake opening (28) from the aircraft cabin and expelled together with the fresh air through the outlet opening (24).

Abstract: A system (10) for ventilating an aircraft cabin comprises an air supply pipe (12) connected to an air source, and a plurality of air distribution lines (14a-14h) branching off from the air supply pipe (12). In a first operating state, the ventilating system (10) is adapted to blow out the air, flowing through the air supply pipe (12), directly from the air distribution lines (14a-14h) into the aircraft cabin. In contrast, in a second operating state of the ventilating system (10), at least some of the air distribution lines (14a-14h) are connected to connecting lines (20a, 20e) which supply the air, flowing through the air supply pipe (12), to air outlets (22a, 22e) arranged in a distributed manner in the aircraft cabin.

Abstract: Systems and methods are provided for regulating the pressure within an aircraft flight crew area during and/or after a decompression event. For example, an aircraft may include a flight crew area, at least one pressure sensor for detecting the pressure of the atmosphere within the flight crew area, and at least one regulated decompression panel that is operatively associated with the pressure sensor, for regulating the pressure within the flight crew area during and/or after a decompression event.

Abstract: It consists of two electrically fed pneumatic independent compressors (CAC) (2) which are connected to an independent controller of (CACs) (5), an auxiliary power unit (APU) (3) sized for independently feeding each (PACK) (1) in the operations of the aircraft both on the ground and in flight, which is connected to an independent controller of (APU) (6) and a central controller (12) connected to the controllers (5 and 6) so that the (PACKs) are individually fed either by a (CAC) (2) or by the (APU) (3) and in such a way that a single (PACK) (1) is fed or several of them.

Abstract: A ventilation nozzle assembly is described that includes a first air outlet channel configured to provide an air flow in a first direction, a second air outlet channel adjacent the first air outlet channel configured to provide an air flow in a second direction, a third air outlet channel adjacent the second air outlet channel and configured to provide an air flow in a third direction, and a fourth air outlet channel adjacent the third air outlet channel and configured to provide an air flow in a fourth directions. An air flow from the third air outlet channel is configured reduce an impact of the air flow from the fourth air outlet channel has on the air flows from the first air outlet channel and the second air outlet channel.

Abstract: The invention concerns an arrangement comprising at least one air passage channel (12) with an air vent (14), and designed to ventilate at least one confined zone (11) in an aircraft with fresh air entering upstream, through the air vent, in the channel and exiting downstream thereof towards the zone to be ventilated. The invention is characterized in that the cross-section of the air passage channel (12) is adjustable based on the speed and the altitude of the aircraft and the arrangement comprises therefor a membrane (19) elastically deformable under the action of a fluid control (18) to enable said channel cross-section to be varied.

Abstract: Air treatment systems including an environmental control system, a mixer, an air distribution duct system, and one or more catalysts for treating the air in the aircraft cabin environment are provided. Methods for treating aircraft cabin air are also provided. The air treatment systems treats compressed air provided to the aircraft cabin, which can include bleed air and bleedless air, and also treats existing air recirculated from an aircraft cabin to remove ozone, volatile organic compounds, NOx and other pollutants. The catalysts used to treat the compressed air, recirculated air and/or combined compressed and recirculated air are disposed at various stages of the air treatment systems described herein.

Abstract: An air conditioning arrangement (22) for an aircraft (10) or other premises with a plurality of climate zones (12 to 20) that may be individually temperature-controlled, comprises a main branching system (26) comprising an air supply feed path system (24) with a mixing chamber (28) and a plurality of sub-branching systems (30) branching from the mixing chamber and leading to one of the climate zones in each case. Basic temperature control means (32) are used for controlling the temperature of the air supply in the mixing chamber (28) as a function of at least one desired temperature value. Individual temperature-control means (36, 38, 40, 42) are used on the other hand for individually controlling the temperature of the air supply in each of the sub-branching systems (30) as a function of a desired temperature value of the respective climate zone.

Abstract: The present invention relates to a method for insulating an aircraft cabin 6 and for the cooling or heating of cabin air in an aircraft, respectively with the method comprising the steps of: introducing aircraft cabin air into an aircraft cabin wall 6; guiding this aircraft cabin air along a section of this aircraft cabin wall 6; and leading this aircraft cabin air away from the aircraft cabin wall 6.

Abstract: An improved vent system for venting an internal cavity of an aerospace vehicle to an exterior surface of the aerospace vehicle generally includes a substantially concave vent inlet surface recessed with respect the exterior surface, and a duct opening formed therein. The vent inlet surface has a major axis substantially parallel to the local external flow direction. The upstream surface contour and the downstream surface contour of the vent inlet surface are substantially oblique to the local external flow direction. The placement and orientation of the duct opening, as well as the geometry of the vent inlet surface, may be selected to achieve a particular pressurization of the internal cavity with respect to the external environment under a variety of conditions.

Abstract: The invention relates to a device (30) for mixing fresh air (2) and heating air (4) which comprises a fresh air inlet (32, 42), a heating air supply body (33, 43) for supplying the heating air (4) into the device (30, 40), and a mixed air outlet (36, 46) for delivering mixed fresh air and heating air (6) from the device (30, 40), wherein the heating air supply body (33, 43) comprises a first portion (35, 45) and a second portion (37, 47) which constitute a flow resistance to the fresh air (2), and wherein the second portion (37, 47) is formed as a closed hollow body with a plurality of heating air supply openings (38, 48) and is connected to the first portion (35, 45) at its downstream end, viewed in the flow direction of the heating air. The invention is characterised in that the first portion (35, 45) of the heating air supply body (33, 43) is of streamlined formation. The invention also relates to the use of a device of this kind in a ventilation system installed on board of an aircraft.

Abstract: The apparatus and method provide an airflow to a person or group of persons or a space such as within an airplane cabin or cockpit, operating in conjunction with an air supply which produces a high velocity air stream, such as an aircraft gasper (14). Existing systems may filter, purify and/or clean the air supplied to the occupant, and the air exiting the personal air outlet may be adjusted to a relatively high velocity. The narrow, high velocity stream of air forms a turbulent boundary layer, which tends to entrain potentially foul air from the surrounding region and directs it towards the passenger. The airflow from the apparatus and method may have reduced velocity and lower thermal and humidity gradient and may be treated to remove locally-originating contaminants. The apparatus includes a housing which receives a primary stream of air, such as from an aircraft gasper (14) or personal air outlet.

Abstract: According to the invention, in addition to a main air conditioning device (4, 5) which taps air off the turbine engine (2), the invention provides an auxiliary unit (16 to 22) with compressor, which taps ambient air and conditions it to send it to the distributing means (24) in place of the main device (4, 5) when the aircraft is in cruising flight or close to cruising flight.

Abstract: The invention concerns a ventilating air intake arrangement with mobile sealing device. The arrangement comprises at least one air passage channel (12) with an air vent (14), and is designed to ventilate at least one confined zone (11) in an aircraft with fresh air entering upstream, through the air vent, in the channel and exiting downstream thereof towards the zone to be ventilated. The invention is characterized in that the cross-section of the air passage channel (12) is automatically adjustable based on the speed and the altitude of the aircraft and the arrangement comprises therefor controllable mobile-element closing means (17) associated with the channel and for varying its cross-section.

Abstract: A system for the provision of process air comprises a first cooling system (2) with a first heat exchanger, which is arranged in a channel (3) that serves as a cooling sink, and a cooling system (8), integrated in the first cooling system (2), wherein said cooling system (8) comprises a heat exchanger (9) which is integrated in the channel (3) either upstream or downstream of the first heat exchanger.

Abstract: A cabin air system for aviation electronics comprises a compressor, an air conditioner, a mix manifold, and an aviation electronics module. The compressor compresses ambient air, and the air conditioner cools the compressed ambient air to produce cabin air. The mix manifold delivers some of the cabin air to the electronics module.

Abstract: A “quick change” restrictor assembly that allows quick rebalancing of flow-pressures within a duct system. The invention comprises a removable restrictor plate, a branch circuit for receiving the plate, and a means for retaining the restrictor plate to the branch circuit. The circuit includes a feature that allows for removal and installation of the restrictor plate without removing the branch circuit, inlet or outlet ducting. The quick change restrictor will not require bonding and can be installed easily from outside the duct without any disassembly. The restrictor may also have various clips or tabs to reinforce the slot the restrictor plate is inserted into. The restrictor may also have a smart part number and color code that is visible from outside the duct allowing easy removal, identification and inspection.

Abstract: A device (10) for improving the breathing air quality for the crew and/or the passengers in an aircraft cabin (12) comprises an oxygen source (16), a water source (18) and a feed line (14), wherein the feed line (14) is connectable to the oxygen source (16) and the water source (18) in order to oxygenate and/or humidify air that is introduced into the feed line (14). The feed line (14) is further connected to an inlet port (24) of a locally delimited area (26) of the aircraft cabin (12) and adapted so as to feed oxygenated and/or humidified air to the locally delimited area (26) of the aircraft cabin (12).

Abstract: The system and method of the presented concept is to provide clean and healthy, recirculated air to the flying public, while still maintaining the minimum pneumatic air drawn from the engines, which in turn help minimize fuel burn and provides for fuel economy.

Abstract: A vent baffle includes a vent panel having a vent panel opening; a blowout panel carried by the vent panel and covering the vent panel opening; a plurality of fastener openings provided in the blowout panel; a plurality of tear slits communicating with the plurality of fastener openings, respectively; and a plurality of panel fasteners extending through the plurality of fastener openings, respectively, and engaging the blowout panel. A vent baffle system for an aircraft and a method of venting an air flow path between a sidewall monument or structure and an aircraft sidewall in an aircraft fuselage of an aircraft are also disclosed.

Abstract: Disclosed is an air conditioning system for an aircraft which utilizes high pressure bleed air. The bleed air is pressure controlled and introduced into a vortex cooler which can be operated in two modes using a valve. In a first mode, the bleed air is divided into cold and hot streams. The cold stream is directed into the cabin for cooling purposes. The hot stream is released from the aircraft in a manner that it pulls ambient air across a heat exchanger. In a second mode, the bleed air is not divided, but passes through the vortex cooler as a common stream. The second mode is more commonly used in colder ambient air conditions.

Abstract: An air infeed device (10) for air-conditioning passenger areas in aircraft comprises a central air infeed module (12) for the centrally regulated cabin ventilation and an individual air infeed module (14) for the individually adjustable cabin ventilation. The central air infeed module (12) and the individual air infeed module (14) are connected to form a subassembly that can be handled independently.

Abstract: An aircraft, aircraft system and air fractionization device are provided. The air fractionization device is provided for use on board an aircraft. The air fractionization installation functions according to the principle of pressure swing adsorption and is supplied by the air conditioning and pressurization system with which also the aircraft cabin may be supplied with air.

Abstract: The invention relates to an air-conditioning system with a redundant feed of supply air comprising at least one pack which is supplied with air, with at least one valve being arranged in the feed for the air flow control. In accordance with the invention, an electrical flow control valve and a pneumatic flow control valve are arranged in parallel connection in front of the pack for the air flow control.

Abstract: The present invention relates to a fluid throttle screen for low-noise control of a fluid volume flow rate (Q) in a pipe and the use of such a throttle screen in an aircraft climate control system. In addition, the present invention relates to a climate control system in an aircraft in whose pipe system at least one such throttle screen is installed. The throttle screen according to the present invention comprises multiple friction elements extending longitudinally in the flow direction, which are situated at a distance to one another in such a way that a fluid is throttled continuously over the extension of the fluid throttle screen as a result of friction on the individual friction elements.

Abstract: The invention concerns a turbofan provided with a pre-cooler. The invention is characterized in that to evacuate the heated cool air stream (24), at least one discharge pipe (25) is arranged in the chamber (12) and connects the pre-cooler (18) to at least one discharge orifice (26) provided in the inner fairing (10), in output of the exhaust nozzle (3) and at least more or less opposite the wing (16).

Abstract: The invention relates to a mixing apparatus for an aircraft air-conditioning system comprising a plurality of supply lines and a plurality of discharge lines. In accordance with the invention, the mixing apparatus consists of the flow cross-section of pockets which are arranged above one another, which have a free cross-section in part and which have a diagonal partition wall in part.

Abstract: The invention eliminates recirculation or back draft associated cooling air flows in systems that use two or more cooling fans/blowers and will accomplish this by “Ins-like” solution The solution is to be passive in nature and will be responding to a tiled fan/blower and engage at the time ol tan/blower failure simply by detecting ihe change ol pressure associated with the failed cooling device [“he device will reduce the spate required and the cost associated with back dralt damping or recirculation In addition, the device can be retrofit existing systems and can be designed to be an integral part of a linger guard ol a cooling fan The device will also provide acoustic advantages of more traditional back drat or recirculation as the Ins will retract completely out ol the airflow during normal operation and therefore not result in the acoustic vibrations associated with many of the existing solutions

Abstract: An aircraft air distribution system includes a base and first and second arrays of nozzle air transfer ports in the base. An adjustable flow plate is positioned over the nozzle air transfer ports. A compressible member is located between the base and the adjustable flow plate and between the first and second arrays. First and second air ejector regions are located, respectively, on the sides of the compressible member between the base and the adjustable flow plate to connect to the first and second arrays, and direct air from the first and second arrays from the sides of the base. Fasteners moveably connect the adjustable flow plate to the base and are adjustable to change a size of different sections of the first and second air ejector regions to change an amount of airflow originating from the different sections of these regions.

Abstract: A system for air distribution in the passenger compartment of a vehicle, for example a motor vehicle, includes at least one outlet for outflow of air into the passenger compartment, which can be activated by putting one's hand at a short distance therefrom without touching it. Associated to the air outlet is an optical sensor, which is set at distance from the air outlet and is optically connected to a window adjacent to the air outlet.

Abstract: An integrated environmental control system for a cargo stowage compartment in a mobile platform, for example in a commercial passenger jet aircraft. A fire detection/suppression subsystem is integrated together with an airflow management system. The airflow management system operates to circulate, and optionally to heat or cool, air withdrawn from a cargo stowage compartment of the aircraft before the air is released back into the cargo stowage compartment. A fire suppression substance, for example, Halon gas, can be discharged directly into a recirculation duct of the airflow management system, thus reducing the duct work required to achieve fire suppression and ventilation operations for the cargo stowage compartment. The integration of the fire detection/suppression and airflow management system operations reduces the overall amount, complexity and weight of the ducting employed in a cargo stowage compartment of a commercial jet aircraft.

Abstract: A valve is provided for controlling a flow of a fluid between a first environment and a second environment. The valve includes a frame adapted to fit within a perimeter of an aperture in a divider separating the first environment from the second environment. The valve additionally includes a first gate movable within the frame to control a flow of the fluid through the aperture between the first environment and the second environment. The first gate includes a substantially aerodynamically clean surface substantially free from protrusions disrupting the flow of the fluid over the first gate surface. Additionally, the first gate includes a trailing edge having a baffle adapted to cover an aft edge of the frame when the first gate is positioned to have a small opening angle. The baffle includes a plurality of 3-D notches in a front side of the baffle.