Abstract: An example temperature sensing device includes an air distribution inlet through which primary air is blown into via an environmental control system, a cabin air inlet through which secondary air enters from a passenger area of a fuselage and the cabin air inlet is coupled to the air distribution inlet through a duct and the secondary air is passively drawn into the cabin air inlet and to the duct due to a pressure difference present in the duct, and a temperature sensor coupled to the duct and positioned downstream of the cabin air inlet along an airflow path of the secondary air so as to be exposed to the secondary air drawn in through the cabin air inlet and flowing through the duct.

Abstract: Disclosed herein are catalyst compositions for removing formaldehyde, volatile organic compounds, and other pollutants from an air flow stream. In one embodiment, a catalyst composition comprises manganese oxide particles and rare earth metal catalyst particles.

Abstract: An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.

Abstract: A system includes an air pressurization system (APS) and an environmental control system (ECS). The APS is configured to supply pressurized supply air to the ECS. The ECS includes a primary heat exchanger (PHX), an air-driven turbine downstream of the PHX, and a vapor cycle refrigeration system (VCRS) downstream of the PHX. The PHX is configured to cool the supply air using environmental air. The turbine is configured to power a vapor cycle refrigeration system (VCRS) using the supply air. The VCRS is configured to cool the supply air to generate cabin air.

Abstract: Systems, apparatus and methods for disinfection of airflow. An apparatus for disinfecting air-conditioned airflow in a confined space includes: a modular housing; and a disinfection chamber enclosed within the housing. The disinfection chamber includes a plurality of disinfection sheets. Each disinfection sheet comprises a plurality of ultraviolet (UV) light sources. The airflow is configured to be routed along a serpentine pathway within the housing to expose microorganisms in the airflow to far UV-C light emitted by the UV light sources for an extended and optimal duration.

Abstract: A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.

Abstract: Apparatus and methods for providing a desired volumetric conditioned airflow rate and for reducing noise level, airflow recirculation and airflow separation are disclosed. An example apparatus includes a nozzle housing having a pair of opposing sidewalls and a front and back wall that define an airflow passage. The airflow passage has a centerline extending between the inlet and the outlet and has a plurality of cross-sections taken perpendicular to the centerline that collectively define a smooth contour along a length of the airflow passage. The cross-sections each have a thickness between the front and back wall that is greater at side edges than at the centerline. The thickness of the cross-sections decreases along a length of at least a first portion of the nozzle housing. A width of each of the cross-sections between the sidewalls increases along the length of at least the first portion of the nozzle housing.

Abstract: An overhead flow distribution assembly for an aircraft cabin, including a conduit defining a plenum having an inlet, upper outlets and lower outlets, the upper outlets spaced apart from each other along a longitudinal direction of the aircraft, the lower outlets spaced apart from each other along the longitudinal direction, the inlet being located between the upper outlets and the lower outlets, and a baffle extending within the plenum along the longitudinal direction, the baffle being located between the upper outlets and at least part of the inlet along a transverse direction normal to the longitudinal direction, the baffle having openings defined therethrough, the baffle configured to restrict airflow from the at least part of the inlet toward the upper outlets. A method of balancing a flow in an overhead flow distribution assembly for an aircraft cabin is also discussed.

Abstract: A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.

Abstract: A direction controlled service apparatus may include a mounting assembly, a housing assembly configured to operably connect to the mounting assembly, the housing assembly being movable with respect to the mounting assembly, and a plurality of actuators connected between the mounting assembly and the housing assembly, each actuator of the plurality of actuators being configured to contract upon a current being applied to the actuator to rotate the housing assembly with respect to the mounting assembly.

Abstract: An air inlet for a flight vehicle engine includes at least one fin, at least partially upstream of a throat of the engine. The fin protrudes into a flow channel, extending beyond a boundary layer into the main airstream in the inlet. The fin causes mixing in the flow, bringing high-momentum flow into areas of the flow channel containing low-momentum flow by aggregating the boundary layer and causing it to lift from the surface. The fin may have a width and/or height that varies along its length in the flow direction, which may allow it to shape the flow around it in predictable ways, without resulting in excessive drag.

Abstract: An aircraft cabin blower system includes: a transmission configured to receive mechanical power from a first part of a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and a power management system, wherein an output of the transmission is configured to drive a cabin blower compressor when operating in a blower mode, the first electrical machine being configured to receive mechanical power from a second part of the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine being configured to act as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system.

Abstract: A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor.

Abstract: An airplane is provided. The airplane includes a first medium, a second medium, and an air conditioning. The air conditioning system includes a first turbine, a compressor, and a mixing point. The compressor is located upstream of the turbine in a flow path of the first medium. The mixing point is a location at which the first medium mixes with the second medium. The mixing point is downstream of the compressor and upstream of the turbine.

Abstract: Auxiliary power unit inlet apparatus and methods are disclosed. An example apparatus includes an aircraft including a fuselage, the fuselage including an air inlet including a first sub-inlet and a second sub-inlet separated from the first sub-inlet; and a door coupled along the air inlet to enable air to separably flow into the first sub-inlet and the second sub-inlet, the door to deter the air from flowing between the first sub-inlet and the second sub-inlet.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changes a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor is configured to operate at airflow conditions greater than a demand of the pneumatic system. An exhaust valve controls airflow between an exhaust outlet and an outlet passage to the pneumatic system. The exhaust valve is operable to exhaust airflow from the booster compressor in excess of the demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

Abstract: A direction controlled service apparatus may include a mounting assembly, a housing assembly configured to operably connect to the mounting assembly, the housing assembly being movable with respect to the mounting assembly, and a plurality of actuators connected between the mounting assembly and the housing assembly, each actuator of the plurality of actuators being configured to contract upon a current being applied to the actuator to rotate the housing assembly with respect to the mounting assembly.

Abstract: An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

Abstract: A personal valve apparatus includes an air inlet, an air outlet, a nozzle, a valve seat, and a moveable poppet valve. The nozzle comprises an inner air-flow surface having a nozzle cavity, extending along the inner air-flow surface, in communication with the air inlet. The valve seat comprises a seat member disposed over the nozzle cavity at the air inlet. The moveable poppet valve is disposed over the seat member and the nozzle cavity at the air inlet. The moveable poppet valve comprises a convex surface. When the moveable poppet valve is in an open position, the convex surface is disposed over and apart from the seat member at the air inlet and configured to allow air to flow from the air inlet, against the convex surface at the air inlet, between the seat member and the convex surface at the air inlet, into and through the nozzle cavity, and out of the air outlet.

Abstract: A disclosed method of hard coating a wear surface of a valve of an aircraft air management system is performed by depositing a hardface alloy powder onto the wear surface, heating the wear surface and the hardface alloy powder to transform the hardface alloy powder into a molten liquid mass, and subsequently cooling the molten liquid hardface alloy mass to solidify the hardface alloy onto the wear surface. The disclosed process provides for localized application and subsequent bonding of the hardface alloy to discrete portions of the wear surface. The solidified hardface alloy coating may then be machined to obtain specific wear surface geometries.

Abstract: A mixer assembly for an air-conditioning system comprising a recirculation air line, connectable to a vehicle region to be air-conditioned, to remove recirculation air from the region, and an air-conditioning air line, connectable to an air-conditioning unit to remove conditioned air from the air-conditioning unit. A first mixing region, for mixing the recirculation air with the conditioned air, is connected to the two air lines. A second mixing region, for mixing the first mixing region air with recirculation air, is connected to the recirculation air line and the first mixing region. Also, a first supply line is connected to the first mixing region to supply air from the first mixing region to a first partial region of the vehicle region, and a second supply line is connected to the second mixing region to supply air from the second mixing region to a second partial region of the vehicle region.

Abstract: Aircraft, wing-to-body fairing assemblies, and air exchange systems are provided. An aircraft includes a fuselage, a wing secured to the fuselage, an outer skin panel, and an air exchange system. The outer skin panel is secured to the wing and/or the fuselage and at least partially defines a cavity. The air exchange system is secured to the outer skin panel and exchanges air between the cavity and an external environment. The air exchange system includes an air inlet, a diffuser, and a silencer. The air inlet is disposed in the outer skin panel and accommodates an air flow between the cavity and the external environment. The diffuser is attached to the air inlet and has a varying cross sectional area to change the speed of the air flow. The silencer is attached to the diffuser and communicates the air flow between the diffuser and the cavity and reduces noise.

Abstract: A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system. The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.

Abstract: An air discharging device for discharging an air flow into a vehicle interior is provided that includes a first air conducting device that can be adjusted with respect to the air discharging characteristic thereof, the air conducting device lying in a first air through-flow region of the air discharging device. The air discharging device also includes a second air conducting device that can be adjusted with respect to the air discharging characteristic thereof, the air conducting device lying in a second air through-flow region of the air discharging device.

Abstract: A locking mechanism, in particular suitable for use in a decompression arrangement, includes a pressure chamber surrounded by a delimiting wall, wherein at least a section of the pressure chamber delimiting wall is formed by an actuating element which is in a rest position when the pressure in the interior of the pressure chamber corresponds to the ambient pressure and moves into a differential pressure position when the pressure in the interior of the pressure chamber exceeds the ambient pressure by a predetermined differential value. The locking mechanism further includes a locking bar which is kept in a locked position when the actuating element is in its rest position and is movable into an unlocked position when the actuating element is in its differential pressure position.

Abstract: An air guiding element (10) for an aircraft air conditioning system comprises a housing base body (12), in which an air inlet opening (14) and an air outlet opening (16) are constructed. A first flow control element (28) is arranged in the housing base body (12), relative to the direction of the air flow through the air guiding element (10), upstream of the air outlet opening (16). The first flow control element (28) comprises a plurality of air guiding channels (30) which are surrounded by a noise-absorbing material (32).

Abstract: An air supply system for passengers includes an air supply line with a plurality of laterally situated air outlets, an individual air panel with at least one air nozzle and an air inlet opening. The individual air panel can be variably positioned along the air supply line in such a way that the air inlet opening faces one of the air outlets. A plurality of magnetic valves is arranged at the air outlets of the air supply line. One of the magnetic valves may be magnetically actuated by the individual air panel, when the air inlet opening of the individual air panel faces said one magnetic valve, so that air can flow out of the air supply line through the air outlet and the air inlet opening to the air nozzle.

Abstract: An outflow valve (10) for an aircraft has a frame (12) for arrangement in an opening (14) of an outer shell (16) of the aircraft, a first flap (18) pivotably arranged in the frame (12) for controlling a flow cross-section of at least one first inflow opening (24) and at least one outflow opening (15). To achieve a simplified construction of the ventilation system of the aircraft, the outflow valve (10) has a second inflow opening (26) configured to be closable by means of a drivable adjustable member (28).

Abstract: A system for air-conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer, a first recirculation system designed to remove exhaust air from a first aircraft cabin region and connected to the central mixer, and a second recirculation system designed to remove exhaust air from a second aircraft cabin region and connected to a local mixer. A control device is designed to control the second recirculation system to reduce an air volume flow being removed from the second aircraft cabin region when shifting from a first operating state (e.g., normal operation) to a second operating state (e.g., defined operating situations such as when quick cooling is desired). The air volume being removed from the first aircraft cabin region may be increased accordingly in the second operating state.

Abstract: An elongated nozzle for distributing airflow in varying directions may include at least one set of channels. Each set may include a plurality of groups of channels. Each set may further include spaced-apart opposed dividers extending lengthwise along an elongated length of the nozzle, and spaced-apart channel side-walls extending between the spaced-apart opposed dividers. The opposed dividers and the spaced-apart channel side-walls may form the channels of each set. At least one of the spaced-apart opposed dividers of each set may be oriented at a first angle which is non-parallel to an imaginary vertical plane extending along the elongated length of the nozzle. Within each set, the spaced-apart channel side-walls of each group of channels may be oriented at different second angles, relative to an imaginary vertical plane extending along a width of the nozzle, than the spaced-apart channel side-walls of other groups of channels.

Abstract: A system for ventilating an explosion hazard region of an aircraft includes a ram-air channel, which has an air inlet for feeding ambient air into the ram-air channel as well as an air outlet. The ram-air channel is devised to feed air to a device that is to be cooled on board the aircraft. A ventilation line has an air inlet for feeding air flowing through the ram-air channel into the ventilation line as well as an air outlet. The ventilation line is devised to feed air to a region of the aircraft that is to be ventilated. An accumulator is disposed between the ram-air channel and the air inlet of the ventilation line and is devised to convert the dynamic pressure of the air flow conveyed through the ram-air channel at least partially into static pressure for regulating flow through the explosion hazard region.

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: An airflow control system for use in a vehicle is provided. The airflow control system includes a manifold and a recirculation duct in flow communication with the manifold. The recirculation duct includes a fan and a recirculation valve. The system additionally includes a ventilation duct coupled in flow communication with the recirculation duct between the fan and the recirculation valve. The ventilation duct is in flow communication with an ambient environment surrounding the vehicle and includes at least one ventilation valve.

Abstract: A supply system is provided that includes, but is not limited to a profile element. The profile element includes, but is not limited to a front wall, a rear wall, and webs between the front wall and the rear wall so that there are ducts within the profile element. The supply system also includes, but is not limited to at least one functional component integrated in at least one of the plurality of ducts.

Abstract: A grille for a vehicle wall opening may comprise a frame, a pair of first louvers, and a second louver. The frame may be receivable on the vehicle wall in an installed position extending around the opening, and may have an inboard side and an outboard side. The pair of first louvers may be supported on the frame, and may be transversely inclined to an outboard direction at a first angle. The second louver may be located between the first louvers, fixed relative to the first louvers, and inclined to the outboard direction at a second angle different from the first angle.

Abstract: A jet pump apparatus for mixing a higher pressure gas and a lower pressure gas, includes an inlet section, an outlet section, a diffuser section and a mixing section. Inlet section includes a higher pressure inlet and a lower pressure inlet. Mixing section includes a plurality of separated mixing chambers. The diffuser section includes diffusers for receiving mixed gases from the mixing chambers. The outlet section receives mixed gases from the diffuser section and conveys those gases to an outlet. The inlet section includes a higher pressure inlet which receives higher pressure gas, and a lower pressure gas inlet which receives lower pressure gas. Each of the mixing chambers has a primary nozzle for introducing primarily higher pressure gas from to a respective mixing chamber, and a secondary inlet for introducing primarily lower pressure gas to each of the mixing chambers.

Abstract: A fresh air inlet for an aircraft features a ram air inlet with a ram air inlet opening, a secondary air inlet opening separate from the ram air inlet and a movably mounted flap. The flap can be moved into a first or second position, and essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and extends away from the aircraft body in the second position to shield the ram air inlet opening from foreign matter in the air. The secondary air inlet reduces the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. The ram air inlet can be optimized for cruising phases, and the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced.

Abstract: An aircraft structure is provided with load-bearing hollow structural elements that form an aircraft fuselage. The cavities in the structural elements are designed as air ducts for an air conditioning system of the aircraft. An aircraft is also provided with such an aircraft structure.

Abstract: Auxiliary power unit inlet apparatus and methods are disclosed. An example apparatus includes an air inlet for an aircraft including a first air flow path and a second air flow path. The first air flow path is immediately adjacent the second air flow path. The first air flow path is at least partially separated from the second air flow path by a first panel. The example apparatus includes a door hingably coupled adjacent the air inlet. The door includes a second panel extending from an interior surface of the door to substantially prevent air from flowing across the interior surface between the first air flow path and the second air flow path.

Abstract: A smoke mitigation system for an aircraft includes an exhaust shutter in an upper region of a fuselage of the aircraft. The exhaust shutter has a closed position in which the exhaust shutter does not exchange air from outside of the fuselage with air inside of a passenger cabin that is within the fuselage and an open position in which the exhaust shutter exchanges air from outside of the fuselage and inside of the passenger cabin, thereby enabling escape of smoke from the passenger cabin. The system includes one or more devices for opening the exhaust shutter and a device for initiating opening of the exhaust shutter. The device for initiating opening of the exhaust shutter includes mechanisms for determining that it is safe to open the exhaust shutter.

Abstract: An aircraft has a ventilation system that employs a plurality of nozzles positioned in a cavity between a sidewall of the aircraft cabin and a section of the aircraft fuselage. The nozzles receive a supply of ventilation air and direct jets of air from the nozzles, through the cavity and into the aircraft cabin. The jets of air produced by the nozzles create low-pressure areas in the cavity. At least one return air opening in the cabin sidewall communicates the low-pressure areas with the cabin interior, whereby the low pressure areas draw air from the cabin interior into the cavity where the drawn air is entrained with the jets of air produced by the nozzles. Devices inside the cavity remove suspended impurities from the air drawn into the cavity. In this manner, the ventilation system filters or sanitizes the air drawn through the system.

Abstract: An aircraft air conditioning system includes a main air conditioning device which taps air off a turbine engine, and an auxiliary unit with a compressor that taps ambient air and conditions it to send to a distributing device in place of a main device, when the aircraft is in cruising flight or close to cruising flight.

Abstract: An air outlet valve for use in an aircraft is adapted during normal operation of the aircraft as a component of a cabin pressure control system for adjusting a desired pressure level in an aircraft cabin to remove air from an interior of the aircraft into the environment around the aircraft. The air outlet valve is further adapted during emergency ventilation operation of the aircraft as a component of a system for emergency ventilation of the aircraft cabin to introduce air from the environment around the aircraft into the interior of the aircraft. The air outlet valve comprises a nose-side valve flap, which is pivotable about an axis and is adapted to open or close a nose-side portion of an air outlet valve aperture, and a tail-side valve flap, which is pivotable about an axis and is adapted to open or close a tail-side portion of the air outlet valve aperture.

Abstract: A cabin air compressor assembly that include a cabin air compressor disposed at a compressor inlet and a cabin air compressor motor operably connected to the cabin air compressor. At least one cooling flow inlet is configured to direct a cooling flow through various pathways in the cabin air compressor assembly, including across the cabin air compressor motor. A blower is configured to boost the cooling flow across the cabin air compressor motor, thereby increasing cooling flow provided to the air compressor motor. A static seal plate is downstream of the blower and guides the boosted cooling flow toward a cooling flow exit. In addition, the static seal plate isolates boosted cooling flow from a moving rotor of the cabin air compressor, and also forms part of a containment structure that contains fragments and breakage that may come from the cabin air compressor rotor.

Abstract: Systems and methods for sound damping in air conditioning systems in an aircraft is provided. In one embodiment, an air conditioning conduit can comprise a sound-damping wall that at least partially encloses a continuous hollow space for guiding the air. The wall comprises a multilayer design with a core layer and at least one first cover layer. The core layer comprises a sound-absorbing open-pore core material so that the wall shows an acoustic effect. The first cover layer is airtight, is arranged on the external surface of the core layer, and is two-dimensionally connected to the core layer. The two-dimensional connection between the core layer and the first cover layer causes a composite effect in such a manner that the wall is self-supporting and has a structural function in order to be able to transfer mechanically-occurring loads to structural parts of the aircraft.

Abstract: A ventilation system for an interior room is provided, having a first air suction device, a second air suction device, a suction volume control device, a first air conduction pipe, a second air conduction pipe, a vacuum generating device and a control unit. The suction volume control device affects an air flow from the first and the second air suction device to the first and the second air conduction pipe, respectively, wherein the control unit controls the suction volume control device so that the air flow from the first air suction device to the first air conduction pipe is controllable.

Abstract: An aircraft air supply system may include a primary duct to supply a primary air flow to a flight deck of an aircraft. A nitrogen generating system may be configured for generating nitrogen enriched air and oxygen enriched air. A secondary duct may be provided for channeling the oxygen enriched air from the nitrogen generating system to the primary duct. The flow of the oxygen enriched air into the primary duct and to the flight deck may be controlled to reduce an effective altitude of the flight deck.

Abstract: A cooling tube includes a tube member extending from a first end to a second end through an intermediate portion having an outer surface and an inner surface. The outer surface has an outside diameter. A flange is mounted at one of the first and second ends of the tube member. The flange includes a flange body extending from a first end portion to a second end portion through an intermediate section having an outer surface and an inner surface. The inner surface defines an inside diameter. The outside diameter of the tube member is between about 0.010-inch (0.0254-cm) and about 0.030-inch (0.0762-cm) smaller than the inside diameter of the flange.

Abstract: A supply duct is provided for supplying a gaseous fluid at a constant flow rate per unit length of the duct. The supply duct includes a main compartment, at least one nozzle disposed in the main compartment, and a plurality of restrictors extending from an inner wall of the main compartment. The main compartment of the supply duct has a generally constant cross-section. Each nozzle in the main compartment defines an outlet to allow a gaseous fluid to flow out from the main compartment. Each restrictor is configured to produce a flow rate through the nozzle at the first end of the main compartment that is substantially equal to the flow rate through the nozzle at the second end of the main compartment. The restrictor may be, for example, a restrictor plate. A method of sizing restrictor plates is also provided.