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.

Abstract: A method for privately transferring filtered air through a partition of a compartment in an aircraft cabin to equalize a pressure difference between the inside and outside the compartment via a vent assembly comprising two substantially structurally identical vent halves joining together in a locking manner through a vent opening in the partition. Each vent half comprising integrally molded rim, frame, plurality of louvers fixed within the frame, latch, keeper, guide prong, and a installation index key; plastic injection molded from high strength unreinforced polycarbonate.

Abstract: An aircraft cabin pressure control system outflow thrust recovery valve includes a frame, a valve element, and actuation hardware. The frame, valve element, and at least a portion of the actuation hardware are made of composite material. The actuation hardware is disposed external to the frame.

Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.

Abstract: A method for calculating an aircraft fuselage leakage calculation of an aircraft is provided. The method comprises determining a calculation period for an aircraft fuselage leakage value and inputting the calculation period into a computer to obtain a first input data. The method further comprises obtaining one or more outside air inflow rates and inputting the one or more outside air inflow rates into the computer to obtain a second input data. The method further comprises obtaining one or more air outflow rates and inputting the one or more air outflow rates into the computer to obtain a third input data. The method further comprises accumulating the first input data, the second input data, and the third input data in the computer to obtain an accumulated input data. The method further comprises processing the accumulated input data with a process software to obtain an output data in the form of a calculated aircraft fuselage leakage value.

Abstract: An adjustable orifice for use in an aircraft air conditioning system includes a first orifice element which has an orifice frame as well as a first orifice area. When the orifice is assembled at a duct, the first orifice area of the first orifice element leaves open a part of a cross section of the duct. The orifice also includes a second orifice element with a second orifice area. When the orifice is assembled at the duct, the second orifice area of the second orifice element leaves open a part of the cross section of the duct. The second orifice element is rotatable about an axis, so that the second orifice area is rotatable relative to the first orifice area in order to set a desired flow cross section in the duct.

Abstract: An autarkic monument in an aircraft pressure cabin supplied with the required operating mediums in a decentralized fashion by carrying along these operating mediums in the monument in operating medium reservoirs is provided. Methods for the efficient energy conversion within this autarkic monument are also provided. The efficiency is achieved such that the energy conversion is, based on the operating mediums, optimized with respect to exergo-economic and/or exergo-ecologic aspects, and such that energy conversion processes are adapted to one another if several energy conversion processes take place.

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: The present invention relates to an emergency ram air inlet valve, also designated as an ERAI valve, of an aircraft. The valve includes an actuating element for opening and/or closing the valve and a controller operatively coupled to the valve, by which the valve can be set at different open angles. The open angle is set as a function of a temperature prevailing or preset in the aircraft cabin.

Abstract: An air conditioning arrangement for an aircraft with a plurality of climate zones that may be individually temperature-controlled includes a main branching system having an air supply feed path system with a mixing chamber and a plurality of sub-branching systems branching from the mixing chamber and leading to one of the climate zones in each case. Basic temperature control means are used for controlling the temperature of the air supply in the mixing chamber. Individual temperature-control means are used on the other hand for individually controlling the temperature of the air supply in each of the sub-branching systems as a function of a desired temperature value of the respective climate zone. Basic temperature control of the air supply in the mixing chamber preferably takes place independently of a temperature requirement of the climate zone with associated combined heat and power engine.

Abstract: A thrust recovery outflow valve and method for controlling the transfer of air between a cabin in an aircraft and atmosphere outside of the aircraft are provided. An outflow valve is mounted on the aircraft that includes a valve frame, a first valve door, and a second valve door. The first valve door is rotated to a first predetermined open position while the second valve door is in the second door closed position to thereby open first and second flow passages that place the aircraft cabin in fluid communication with the atmosphere. When the first valve door is at a first predetermined open position, a flap is rotated, relative to the first valve door, to at least partially cover the second flow passage and thereby at least inhibit flow through the second flow passage.

Abstract: A bi-fold valve door and method for controlling aircraft cabin pressure are provided. The bi-fold valve door includes an aft door section and a forward door section, and only the forward door section is selectively rotated about one rotational axis to a position between a closed position and a full-open position, while the aft door section is maintained in its closed position. The forward door section is selectively rotated about the rotational axis to a full-open position to engage the aft door section, while the aft door section is maintained in its closed position. When the forward door section is in the full-open position, the aft door section and the forward door section are simultaneously rotated about another rotational axis.

Abstract: A valve for use in a cabin pressure control system includes a valve body and a poppet. The valve body includes an inlet, an outlet, and a fluid flow passage therebetween. The poppet is disposed in the valve body. The poppet is moveable between at least a closed position, in which the poppet at least substantially restricts fluid from flowing through the fluid flow passage, and an open position, in which fluid is allowed to flow through the fluid flow passage. The valve body, the poppet, or both, have a fluorocarbon coating.

Abstract: A thrust recovery valve has two flaps, with each flap controlled independently via its own rotary actuator. Embodiments of the present invention also provide a cabin pressure control system that includes one or two thrust recovery valves and the controls architecture to efficiently operate the valves. On each thrust recovery valve, only one door can be operated during flight, making less effective area change per unit time (relative to the operating both doors at the same time), allowing higher resolution of valve control. Further, the valve doors can be made such that the primary door that is operated in flight is smaller than the other door (mostly only operated on the ground). Because the doors of the thrust recovery valve can be operated independently, the forward door of each valve can be rotated such that the door creates a ram air “scoop” to ingress air to prevent negative pressure from building up beyond a specified limit.

Abstract: An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section; and an environmental control system coupled to an output of the auxiliary compressor for conditioning the compressed air to a predetermined level.

Abstract: The present invention describes a modular hatrack for an interior of an aircraft, wherein the modular hatrack comprises at least one container and at least one housing to accommodate the container, wherein at least one component from the group comprising a personal supply channel, an electrical line, a light strip, an air duct for an air conditioning system, and an air outlet for an air conditioning system is integrated in the housing. The present invention also describes the use of the modular hatrack in an aircraft or in some other vehicle.

Abstract: An outflow valve is provided for use in conjunction with an actuator. In one embodiment, the outflow valve includes a frame and a first door rotatably coupled to the frame. The outflow valve is configured to be moved by the actuator between an open position and a closed position. The first door includes: (i) a main body having a sealing edge, and (ii) a J-shaped bellmouth fixedly coupled to the main body proximate the sealing edge. The J-shaped bellmouth is configured to condition fluid flow through the outflow valve when the first door is in the open position.

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

Abstract: An air system for pressurizing and air conditioning a cockpit and cabin space of a plane comprises a compressor (3) for compressing an air mass flow, wherein the air mass flow to be compressed is extracted through a ram air duct (13, 14) from the environment of the plane and supplied through a heat exchanger (15, 18) to at least one zone (10A-D) to be pressurized and air conditioned.

Abstract: The invention relates to a decompression element for pressure equalization in a cabin of an aircraft, with a decompression element frame, a flap, and a hinge element or at least one bearing element for fitting the flap to the decompression element frame. The hinge element or the bearing element can be produced from a plastics material. A decompression device for decompressing a cabin area includes a decompression device frame, a first opening which enables a flow to take place between a line of an air-conditioning system of the aircraft and the interior space of the decompression device, a second opening which enables a flow to take place between the cabin area and the interior space of the decompression device, and a third opening receiving the decompression element with the flap.

Abstract: A thrust bearing shaft has an enlarged disk at one axial end to provide a rotating surface in a thrust bearing. A first cylindrical portion extends from the disk. A second cylindrical portion has a smaller diameter than the first cylindrical portion and extends from the first cylindrical portion to an end of the thrust shaft remote from the disk. The thrust shaft has a hollow bore with a ledge extending across the bore at a location within the first cylindrical portion. The ledge is formed with a central hole of a first hole diameter, and twelve air holes spaced circumferentially about the central hole. The twelve holes are formed of a second hole diameter, with a ratio of the first hole diameter to the second hole diameter being between 2.55 and 2.71. In addition, a bearing assembly, a compressor, and a method of assembling a compressor are disclosed.

Abstract: An air bearing shaft has a first cylindrical portion with a relatively small outer diameter, and a ramped surface extending at an angle that is non-perpendicular and non-parallel to a central axis of a shaft body. The ramped surface leads into a second cylindrical portion of the shaft has a large outer diameter that is greater than the diameter of the first cylindrical portion. There are twelve air holes formed to extend into an interior of the second cylindrical portion. A bore diameter is defined to an inner periphery of the second cylindrical portion at the location of the air holes. A ratio of the bore diameter to a diameter of the air holes is between 6.30 and 6.54. In addition, a bearing assembly, a compressor, and a method of incorporating an air bearing shaft into a compressor are all disclosed and claimed.

Abstract: A single valve door thrust recovery outflow valve is provided that does not rely on a relatively large and expensive actuator to move it, and does not create unwanted drag during aircraft cruise operations. The valve includes a valve frame, a valve door, and an aerodynamic flap. The valve door is rotationally coupled to the valve frame, is adapted to receive a drive torque, and is configured, upon receipt of the drive torque, to rotate between a closed position, a full-open position, and a plurality of partial-open positions between the closed position and the full-open position. The aerodynamic flap is coupled to the valve door. When the valve door is in the closed position and in numerous partial-open positions, the aerodynamic flap makes the thrust recovery outflow valve aerodynamically clean.

Abstract: A device for supplying a multi-component jet into the visual field of a user, wherein the device has a line, an outlet opening and a transport unit. An oxygen-containing component and a water-containing component can be supplied to the line. The transport unit can be used to transport a mixture consisting of the oxygen-containing component and the water-containing component through the line to the outlet opening, so that the mixture streams out of the outlet opening directly toward the visual field of the user.

Abstract: A device (10) for connecting two duct elements (12, 14) and a baffle (34) in an aircraft air conditioning system may include first (30) and second (32) connecting flanges each connected to one of the two duct elements (12, 14), and at least one connecting element (38) formed on the first connecting flange (30) which interacts with at least one corresponding connecting element (40) formed on the second connecting flange (32) to establish the connection of the two duct elements (12, 14) and the baffle (34). The first (30) and/or second connecting flange (32) has/have an opening (44) for receiving the baffle (34), which is substantially disc-shaped and formed with at least one air passage (46, 48). The baffle (34) serves to control the flow of at least one air stream flowing through the connected duct elements (12, 14).

Abstract: An emergency pressurization system for an aircraft having an air pump that is powered by bleed air from an engine of the aircraft. Although the air pump is powered by engine bleed air, the air pump draws ambient fresh air from outside the aircraft, compresses the fresh air to a predetermined pressure and pumps compressed fresh air into the pressurized cabin of the aircraft without ever exposing the compressed fresh air to the engine air. The speed of the air pump is selectively controlled as a function of cabin pressure and/or bleed air pressure. In this manner, the cabin is maintained at a constant safe pressure.

Abstract: Method and arrangement for adjusting nitrogen and oxygen concentrations within regions of an aircraft. The method includes separating nitrogen from ambient air onboard an aircraft thereby establishing a high-concentration nitrogen supply and then dispensing high-concentration nitrogen from the supply to a fire-susceptible, non-habitable region of the aircraft where the high-concentration nitrogen is reservoired thereby decreasing the capability for the atmosphere therein to support combustion. Oxygen is also separated from the ambient air thereby establishing a high-concentration oxygen supply that is dispensed to an occupant cabin of the aircraft thereby increasing the level of oxygen concentration within the cabin to a level greater than the naturally occurring concentration of oxygen at the experienced internal cabin pressure.

Abstract: Methods and apparatus are provided controlling aircraft cabin pressure, and more specifically engine bleed air manifold pressure, during aircraft descent. An aircraft engine bleed air manifold control pressure setpoint is to either a descent pressure setpoint or a cruise pressure setpoint by determining a rotational speed of an aircraft engine component, determining a component speed setpoint value, and determining aircraft vertical speed. The engine bleed air manifold control pressure setpoint is set to the descent pressure setpoint if either the determined rotational speed of the aircraft engine component is below the component speed setpoint value or the aircraft vertical speed is less than a predetermined vertical speed value.

Abstract: A combination ventilation and stowage bin system including at least one support duct defining an inlet for receiving conditioned air from a supply duct and an outlet for directing air into a passenger compartment, and a stowage bin for stowing luggage mounted to and supported by the at least one support duct, the stowage bin entirely supported by the duct such that the bin is free from direct attachment to an interior wall or supporting structure other than the duct.

Abstract: A cabin pressure control system and method improves cabin pressurization during aircraft take-off operations. The cabin pressure control system sets a cabin pressurization rate limit based on a cabin pressurization rate error. The cabin pressurization rate error is derived from a comparison of a sensed cabin pressure rate-of-change value and a predetermined cabin pressurization rate value.

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 method and a line system for the air-conditioning of a cabin of an aircraft envisage that at sites remote from passengers air that is at a temperature lower than air at sites closer to passengers is introduced into the cabin.

Abstract: Systems and methods for providing airflow in an aerospace vehicle are disclosed. A system in accordance with one embodiment includes an aerospace vehicle having an interior volume with a first portion and a second portion. The system can further include an external air supply device positioned to provide supply air to the interior volume at a variable supply flow rate and a recirculation fan configured to move air positioned within the interior volume between the first portion of the interior volume and the second portion of the interior volume. The system can still further include a controller operably coupled to the recirculation fan and configured to vary a rotation speed of the recirculation fan. Variations in the rotation speed of the recirculation fan can be associated with variations in a recirculation flow rate. In selected embodiments, the system can include sensors and/or data link devices operably coupled to the controller.

Abstract: An air exit guidance which in particular is provided for arrangement in the personal service unit of an passenger aircraft. The guidance includes an air inlet and an air outlet as well as an adjustable throttle which is arranged at the inflow side of the air exit guidance.

Abstract: The present invention relates to a fuselage of an aircraft or spacecraft, with at least one shell element and a structural element. An interspace to which air can be admitted by an air stream is provided between the at least one shell element and the structural element. The fuselage is distinguished by the fact that, to form the air-admitting air stream as an outgoing/incoming air stream of a pressurized interior space of the fuselage, the interspace is connected to a corresponding outgoing/incoming air connection of the interior space. The invention also relates to a corresponding aircraft or spacecraft and to a method of actively insulating such a fuselage.

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 method for reducing outside air inflow required for aircraft passenger cabin air quality is provided. The method determines when passenger cabin air quality is the driving outside air inflow requirement and reduces the outside air inflow to that required for passenger cabin air quality. In one embodiment, there is provided a method for reducing outside air inflow required for aircraft passenger cabin air quality using a fixed minimum outflow valve open area setpoint. In another embodiment, there is provided a method for reducing outside air inflow required for aircraft passenger cabin air quality using calculations that are repeated at regular intervals and using a mathematical function relating an outside air inflow requirement to a set of independent variables.

Abstract: The invention relates to a valve for controlling a fluid flow from a first environment to a second environment, having a frame for disposing a separating element in the region of an opening, said element separating the first environment from the second environment, and a first flap and a second flap for controlling the fluid flow through the opening between the first environment and the second environment, the flaps being movable in the frame. The flaps have protrusions designed to reduce noise generation in the fluid flow.

Abstract: This door includes a device that permits air to flow through the door in one direction but prevents this flow of air in the opposite direction. On the attached illustration, the door includes at least a window (74), that less air pass through as well as an elastic membrane (76) covering window (74). Elastic membrane (76) includes on the one hand an area that is airtight facing window (74) and capable of fully covering it and on the other hand, an area that is pervious to air near the impervious area.

Abstract: A system for air conditioning at least one partial region of an aircraft comprises 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, and that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a temperature that a desired ambient temperature is set in the aircraft region to be ventilated.

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: An environmental control system includes a RAM air fan system downstream of a respective heat exchanger in the relatively high temperature RAM exhaust. The RAM air fan includes a RAM air fan electric motor such that the RAM air fan is driven at a speed independent of an air cycle machine. A fan rotor is completely supported by hydrodynamic foil journal and thrust bearings. As the RAM air fan is driven by the RAM air fan electric motor the RAM air fan is installed in the environmental control system as a self-contained system.

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 outflow valve is provided for use in conjunction with an actuator. In one embodiment, the outflow valve includes a frame and a first door rotatably coupled to the frame. The outflow valve is configured to be moved by the actuator between an open position and a closed position. The first door includes: (i) a main body having a sealing edge, and (ii) a J-shaped bellmouth fixedly coupled to the main body proximate the sealing edge. The J-shaped bellmouth is configured to condition fluid flow through the outflow valve when the first door is in the open position.

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: An aircraft exhaust vent assembly for venting an exhaust gas through a window opening formed in an airplane fuselage. The aircraft exhaust vent assembly has an enclosure connected to the airplane fuselage and at least partially disposed within the window opening. An inlet is formed in the enclosure and connectable to an exhaust gas source for directing the exhaust gas into the enclosure. An outlet is formed in the enclosure for venting said exhaust gas to the exterior of the airplane fuselage. An outlet flap is connected to the enclosure for movement between a first position and a second position. In the first position, the outlet flap substantially seals the outlet in the enclosure when the exhaust gas is not supplied to the enclosure. In the second position, the outlet flap does not seal the outlet in the enclosure to allow for venting of the exhaust gas to the exterior of the airplane fuselage.

Abstract: Testing of an aircraft pressure control system may be performed without use of an altitude chamber. Aircraft cabin configuration date may be modeled and used, along with high resolution positional feedback from a simulated valve, to produce a high resolution electrical signal that may represent a simulated cabin pressure. A voltage-to-pressure transducer may convert the electrical signal to a pneumatic signal. The pneumatic signal may be employed to operate a cabin-pressure controller under test. The controller may operate an outflow valve actuator and an attached potentiometer. The potentiometer may produce a feedback signal and closed-loop testing of the aircraft pressure control system may thus be performed. The outflow valve actuator may be operated without being attached to an outflow valve because a simulated aerodynamic load may be applied to the actuator.

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: 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: 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.