Abstract: A system comprises an environmental control system (ECS) having a plurality of ducts configured to convey a flow of air into an interior space through the plurality of ducts. A plurality of valves are disposed in the plurality of ducts to control the flow of air through a respective duct into the interior space. A plurality of sensors are disposed in the interior space configured to sense a passenger condition.

Abstract: Disclosed is a drive device, in particular for a flying vehicle such as an aircraft or a spacecraft, comprising at least one engine and a device for cooling the engine, the device for cooling the engine comprising a cryogenic refrigerator, i.e. refrigerating to a temperature between ?100° C. and ?273° C.

Abstract: A compressing device for use in an environmental control system includes at least one turbine configured to provide energy by expanding one or more mediums. The one or more mediums provided at an outlet of the at least one turbine form a heat sink within the environmental control system. A compressor is configured to receive energy from the one or more mediums expanded across the at least one turbine. During a first mode of the compressing device, energy derived from a first medium and a second medium of the one or more mediums is used to compress a second medium at the compressor. During a second mode of the compressing device, energy derived from the first medium, the second medium, and a third medium of the one or more mediums is used to compress the second medium at the compressor.

Abstract: An aircraft air conditioning system comprises intakes ram air from outside the aircraft, and uses a heat exchanger to pretreat (preheat or precool) some of the ram air. The system further includes a heat recovery unit that uses the cabin exhaust air to further heat the pretreated ram air, resulting in conditioned ram air. The system further includes an air conditioning pack unit to produce a first conditioned air stream from the conditioned ram air. The system further includes a mixing box to mix the first conditioned air stream with another subflow of ram air to produce a second conditioned air stream.

Abstract: An aircraft propulsion system includes a gas turbine engine; an environmental control system (ECS); and a bleed flowpath from the gas turbine engine through the ECS. A turbine is along the bleed flowpath and a propulsion fan is mechanically coupled to the turbine to be driven by the turbine.

Abstract: A protection device for an electrical cabinet is divided into a plurality of compartments, the protection device including a rain guard and an air manifold formed as an integral unit. The rain guard is designed to cover a section of an electrical cabinet and thus prevent water from falling on it. The air manifold includes at least one first pipe fluidically connected to a second pipe. Each first pipe intended to be connected to a corresponding air-circulation opening of a compartment, and the second pipe being intended to be connected to an air-circulation means in order thus to allow air to be circulated in the plurality of compartments. A cabinet is provided with such a protection device.

Abstract: A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; and a controller to: detect an in-flight windmill re-start condition of the gas turbine engine; and cause power to be supplied from a power source to the electric motor in order to augment rotational power of the high speed or the low speed spool during the detected in-flight windmill re-start condition.

Abstract: An aircraft air conditioning system comprises intakes ram air from outside the aircraft, and uses a heat exchanger to pretreat (preheat or precool) some of the ram air. The system further includes a heat recovery unit that uses the cabin exhaust, air to further heat the pretreated ram air, resulting in conditioned ram air. The system further includes an air conditioning pack unit to produce a first conditioned air stream from the conditioned ram air. The system further includes a mixing box to mix the first conditioned air stream with another subflow of ram air to produce a second conditioned air stream.

Abstract: The disclosure is directed to an independent manual control system of an all-electric cabin pressure control system (CPCS). The manual control system may include a momentary electrical switch to manually set the position of an outflow valve (OFV) along with a closed loop control to hold the cabin pressure at the pressure setpoint. The closed loop control of the manual control system is independent from the automatic pressure control functions of the all-electric CPCS.

Abstract: A passenger cabin air distribution system includes a ventilation system and an ejector-diffuser. The ventilation system is operable to provide a conditioned air. The ejector-diffuser is positioned to receive a flow of the conditioned air from the ventilation system. The ejector-diffuser includes an induction unit and a diffuser section. The induction unit includes a secondary inlet in communication with a cabin air from a passenger cabin and is configured to mix the flow of the conditioned air with an induced flow of the cabin air into a mixed air. The diffuser section includes a discharge to eject the mixed air to the passenger cabin. The diffuser section is shaped to provide for efficient mixing with low backpressure in order to maintain the low motive pressure in the nozzle.

Abstract: An air-conditioning duct structure of an aircraft includes an air-conditioning duct that is provided on each of a starboard side and a port side and guides conditioned air to a vicinity of a ceiling of a cabin in the aircraft. The air-conditioning duct includes a blowout portion and a blowout upstream portion. The blowout portion blows out the conditioned air to the cabin from an outboard side of the ceiling to an inboard side of the ceiling and toward a lower part than the ceiling, and the blowout upstream portion communicates with an upstream side of the blowout portion. In addition, the blowout portion or the blowout upstream portion is curved to cause a terminal end side of the blowout portion to be inclined downward with respect to a horizontal direction.

Abstract: An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

Abstract: A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.

Abstract: Systems and methods for limiting infiltration of cabin air into the flight deck of an aircraft, where the systems include at least one upper nozzle disposed adjacent to and above an outer upper edge of a flight deck doorway and directed downwardly, and at least one lower nozzle disposed adjacent to and below an outer lower edge of the flight deck doorway and directed upwardly; a conduit system to deliver air from a flight deck air supply to the upper and lower nozzles; and an airflow controller configured to provide sufficient air flow from the flight deck air supply to the upper and lower nozzles to create directional airstreams across the gaps between the closed flight deck door and the upper and lower edges of the flight deck doorway, so that the airstreams limit infiltration of cabin air into the flight deck via the gaps.

Abstract: An aircraft includes an environmental control system having a bleed air inlet, a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply, and a turbo air cycle machine. The turbo air cycle machine includes a compressor fluidly coupled to the low pressure bleed air supply, as well as a turbine fluidly coupled to at least one of the low pressure bleed air supply or the high pressure bleed air supply.

Abstract: Auxiliary power systems, aircraft including the same, and related methods. An auxiliary power system comprises an auxiliary power unit (APU) controller and an APU with an air intake, a powerhead, and a load compressor stage. The load compressor stage includes a flow regulator assembly, a load compressor, and a bleed air temperature (BAT) sensor for generating a BAT signal. The APU controller regulates a flow rate of a load compressor airflow through the load compressor based on the BAT signal. A method of utilizing an auxiliary power system includes compressing a load compressor airflow to generate a bleed air flow, measuring the BAT with a BAT sensor, generating a BAT signal based on the BAT, transmitting the BAT signal to an APU controller, generating a flow regulator command with the APU controller, transmitting the flow regulator command to a flow regulator assembly, and controlling a flow regulator assembly.

Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. At least one temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link each comprise a respective winch operable to adjust pay out of a respective tension member thereby to provide length adjustment. The temporary forward link and the temporary rearward link maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.

Abstract: A compressing device added to a cabin air conditioning system to increase a pressure of air in the cabin air conditioning system itself and, thus, allow for lower pressure air to be bled from the engine. For instance, the compressing device allows air to be bled from a low, rather than a high, pressure locations of the engine.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.

Abstract: An environmental control system for an aircraft is provided. The environmental control system comprises a bleed air system. Also included is a ram air system. Further included is an air pressure and temperature conditioning system, wherein bleed air and ram air are mixed to satisfy a cabin fresh air requirement. The air pressure and temperature conditioning system includes a compressor that pressurizes ram air. The air pressure and temperature conditioning system also includes a power turbine that expands bleed air, the pressurized ram air and expanded bleed air at identical pressures prior to mixing downstream of the compressor and the power turbine.

Abstract: An aircraft turboprop engine has at least one low-pressure body and one high-pressure body. The low-pressure body drives a thrust propeller using a gearbox. The turboprop engine further includes a means for supplying air to an air-conditioning circuit of an aircraft cabin. The supply means includes a load compressor and a rotor that is coupled to the low-pressure body by the gearbox. The supply means further includes a means for controlling the rotation speed of the rotor of the compressor, which means comprise an electric motor, and a mechanical differential for coupling a first output shaft of said electric motor to a second output shaft of said gearbox and to said compressor rotor, such that the rotation speed of said rotor depends on the respective rotation speeds of said first and second output shafts.

Abstract: An air conditioning pack includes an air cycle assembly, a vapor cycle system, and a mixing duct. The air cycle assembly is configured to receive bleed air and utilize the bleed air to compress ram air. The vapor cycle system is configured to receive the compressed ram air and to reduce an operating temperature of the compressed ram air. The mixing duct is configured to receive the compressed ram air and mix the compressed ram air with the bleed air to generate a hybrid air stream that is used for cooling at least a portion of a vehicle.

Abstract: An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage is fluidly coupled to a bleed port of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system includes a pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. The intercooled cooling system includes an air cycle machine in fluid communication to outputs of the cooling stages to selectively receive the cool bleed air or the intercooled cooling air.

Abstract: An aircraft cooling machine is provided that includes a closed loop air cycle system and a vapor cycle system that both provide cooling aircraft loads. The closed loop air cycle system includes a compressor and a turbine and the vapor cycle system includes a compressor, condenser and an evaporator. A coupler is provided that pneumatically couples the turbine in the closed loop air cycle system to the compressor in the vapor cycle system via existing pneumatic power in the closed loop air cycle system.

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 system for air conditioning at least one partial region of an aircraft includes an air providing device for providing air to be supplied to a region of the aircraft to be ventilated at a desired temperature and pressure. A supply air duct is connected at a first end to the air providing device. A second end of the supply air duct is connected to an air inlet which opens near the floor into the aircraft region to be ventilated. A control device is set up to ensure that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a speed that the air is distributed near the floor in the aircraft region to be ventilated and rises at heat sources present in the aircraft region to be ventilated.

Abstract: An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin includes an environmental control system having at least one pneumatic air cycle air conditioning unit, a bleed air port in the at least one thrust providing jet engine, a non thrust providing auxiliary supply unit configured to provide electricity and compressed air on ground and during flight, and at least one compressed air line. The at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit. The environmental control system is coupled with the at least one compressed air line. Further, the auxiliary supply unit is dimensioned to exclusively operate the environmental control system by delivering compressed air, and bleed air from the bleed air port is selectively providable to the environmental control system for redundancy.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.

Abstract: An aircraft air conditioning system including a process air line having a first end connected to a process air source to allow a flow of process air therethrough. A ram air channel of the air conditioning system allows ambient air flow therethrough. A heat exchanger unit is disposed in the process air line and arranged within the ram air channel to thermally couple process air flowing through the process air line to ambient air flowing through the ram air channel. A water extractor disposed in the process air line downstream of the heat exchanger unit extracts water from the process air. A water supply system supplies extracted water into the ram air channel. The water supply system has a control arrangement to control a fluid connection between the water extractor and the ram air channel in dependence on an operating state of the aircraft air conditioning system.

Abstract: An air conditioning system includes a first mix manifold and a second mix manifold. A first air conditioning pack is coupled in flow communication with the first mix manifold, wherein the first air conditioning pack is configured to channel a supply of fresh air to the first mix manifold. A second air conditioning pack is coupled in flow communication with the second mix manifold, wherein the second air conditioning pack is configured to channel the supply of fresh air to the second mix manifold. The first air conditioning pack is also coupled in flow communication with the second air conditioning pack.

Abstract: Disclosed herein is a hybrid mechanical/reactive pressure prevention system that includes a passive pressure control device operably coupled to a door that allows air within a pressurized vehicle to flow out of the pressurized vehicle. An event module detects a door event in the pressurized vehicle. The door event indicates that a door is not secure and air within the pressurized vehicle is being released through the passive pressure control device. An altitude module determines an altitude of the pressurized vehicle in response to detecting the door event. An electronic pressure control device one or more of reduces air inflow into the pressurized vehicle and increases air outflow out of an active pressure control device of the pressurized vehicle in response to the altitude of the pressurized vehicle being below a cutoff altitude.

Abstract: A method for emergency ventilating and pressurizing an aircraft cabin comprises determining a cabin pressure within the aircraft cabin and determining an ambient pressure in an aircraft environment. Descent of the aircraft is initiated when the cabin pressure falls below a predetermined threshold value. A supply of ambient air from the aircraft environment into the aircraft cabin is initiated, when, during descent of the aircraft, a differential pressure between the cabin pressure and the ambient pressure falls below a first calculated threshold value. The supply of ambient air into the aircraft cabin and an operation of an air outflow valve of a cabin pressurization system of the aircraft are controlled such that a flow of ambient air into the aircraft cabin corresponds to at least a predetermined minimum value and the differential pressure between the cabin pressure and the ambient pressure does not fall below a second calculated threshold value.

Abstract: A system for cooling and/or heating aircraft devices to be cooled and/or heated includes a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated, a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated, a cooling and/or heating energy supply apparatus adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated, a control device adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system.

Abstract: A bleed air conditioning system within an aircraft including a low-pressure bleed air line and a high-pressure bleed air line. The system includes an air-to-air heat exchanger and an un-cooled bleed air line to connect the air-to-air heat exchanger to the low-pressure bleed air line and the high-pressure bleed air line. The un-cooled bleed air line carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger. The system also includes a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line, bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line.

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 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: 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: A bleed system that comprises a bleed inter-compressor fluidly coupled to a low pressure port of the bleed system and configured to utilize a portion of a medium received from the low pressure port to increase the pressure of another portion of that medium. A turbine of the bleed inter-compressor is coupled to a compressor of the bleed inter-compressor and drives the compressor via a shaft, so as to regulate the pressure of the medium.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: An aircraft air system includes a gas turbine engine, a bleed air duct directing compressed air bled from a compressor to an inner compartment within the aircraft, and an air contamination detector located downstream of the gas turbine engine compressor. The air contamination detector includes a visual indicator which detects the presence of a fluid contaminant within the bleed air.

Abstract: A heating, ventilating, and air conditioning (HVAC) module for a vehicle includes an HVAC structure to accommodate a plurality of HVAC system components, the HVAC structure configured to be installed in a host vehicle. The HVAC module also includes an interconnect network with a first group of the HVAC system components and a hub component, wherein the hub component is coupled to a second group of the HVAC system components. An HVAC module connector is coupled to the interconnect network to establish data connectivity between the interconnect network and an electronic control module of the host vehicle.

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: The present invention provides a method for controlling an internal pressure in an aircraft or spacecraft, the method comprising the following steps: detecting the internal pressure in the craft and an external pressure Pa outside of the craft and comparing said pressures with each other; and adjusting a flap of at least one outflow valve to a blade position, in which the flap directs air flowing past an outer surface of the craft into the craft to increase the internal pressure, if the external pressure exceeds the internal pressure by a predetermined value during the descent of the craft. The idea, on which the present invention is based, is to assign a double function to the outflow valve: during normal flight the positive pressure in the craft is relieved by means of the outflow valve.

Abstract: An aircraft comprises composite skin having an opening, and a ventilation conduit having an end portion that extends to the opening in the composite skin. The conduit is made of metal except for the end portion, which functions as an electrical insulator.

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: One embodiment of a pressure management system for an aircraft may include a cavity, an opening in a surface of the cavity, and a moveable door. An interior area within the cavity may have an interior pressure and an exterior area outside of the cavity may have an exterior pressure. The door may open to uncover the opening and may close to cover the opening in response to pressure differential between the exterior pressure and the interior pressure.

Abstract: An aircraft air-conditioning system includes an air-conditioning unit that is connected by a main fresh-air line to a mixer in order to supply the mixer with fresh air at a desired low temperature. A fresh-air branch line that is connected upstream of the mixer to the main fresh-air line has a flow cross section that is smaller than a flow cross section of the main fresh-air line. In a region of connection of the main fresh-air line to the fresh-air branch line the main fresh-air line and the fresh-air branch line are so formed that a main fresh air flow flowing through the main fresh-air line is deflected, while a fresh air branch flow flowing through the fresh-air branch line experiences substantially no deflection.

Abstract: An nitrogen generation system for an aircraft is provided. The system includes a RAM air circuit, a motor driven compressor (MDC) having a rotor, a stator to drive rotor rotation and a compressor rotatably coupled to the rotor and a cooling system. The cooling system directs cooling air from the RAM air circuit to an inlet of the compressor and an alternative low pressure environment such that the cooling air removes heat from the stator.