Abstract: A control system for aircraft anti-icing is disclosed including a conduit coupled at a first end to a source of hot high-pressure bleed air, a control valve in fluid communication with the conduit and an injector head, wherein the control valve is in electronic communication with a controller and configured to regulate the flow of bleed air between the conduit and the injector head, and a first sensor in electronic communication with the controller and configured to report a first data. The system may initialize a control valve to an initial regulated pressure. The system may determine a control temperature and control the control valve based on the control temperature, the first data, and a set value.

Abstract: A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. The heat pipe system includes one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section. The heat pipe system is operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown.

Abstract: An aircraft is provided including an environmental control system (ECS) having a first ECS pack and a second ECS pack. A duct couples the first ECS pack to the second ECS pack. The duct includes a first bypass conduit configured to form a bypass around a first primary heat exchanger of the first ECS pack. A second bypass conduit configured to form a bypass around a second primary heat exchanger of the second ECS pack. The duct includes a crossover conduit extending between the first bypass conduit and the second bypass conduit. The duct includes a plurality of valves for selectively controlling a flow between the first bypass conduit and the second bypass conduit.

Abstract: An aircraft adaptive power thermal management system for cooling one or more aircraft components includes an air cycle system, a vapor cycle system, and a fuel recirculation loop operably disposed therebetween. An air cycle system heat exchanger is between the air cycle system and the fuel recirculation loop, a vapor cycle system heat exchanger is between the vapor cycle system and the fuel recirculation loop, and one or more aircraft fuel tanks are in the fuel recirculation loop. An intercooler including a duct heat exchanger in an aircraft gas turbine engine FLADE duct may be in the air cycle system. The system is operable for providing on-demand cooling for one or more of the aircraft components by increasing heat sink capacity of the fuel tanks.

Abstract: A device for temperature control in an aircraft cabin includes a first supply control arrangement and a first pressure control arrangement. The first supply control arrangement includes an air duct and a valve arrangement that controls a supply of heated air delivered to a first temperature area of the aircraft cabin such that a first specified temperature for the first temperature zone is achieved. When the valve arrangement fails, the first pressure control arrangement operates to control a pressure of heated air supplied into the first temperature area such that the first specified temperature for the first temperature zone is achieved.

Abstract: Aircraft air-conditioning system (1) for an aircraft having a plurality of zones (2, 4), comprising a first line (6) for feeding cold air at an actual temperature T1act., a second line (14) which branches off a portion of the air from the first line (6) at a branching point (10) and feeds the air to a plurality of zones (2, 4) of an aircraft, wherein warm air is fed through a first trim valve (12) into the second line (14) so that the air in the second line (14) is heated to the actual temperature T2act., and a first zone feed line (24) feeding the air downstream of the first trim valve (12) to a first zone (2), wherein a second trim valve (26) is arranged in the first zone feed line (24), through which valve warm air is fed into the first zone feed line (24) so that the air in the first zone feed line (24) is heated to the actual temperature Tzf1act., and the first line (6) downstream and/or upstream of the branching point (1) feeds cold air at least to one further zone.

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 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: 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: A combined smoke detector and cooling control system for a mobile platform is operable to control multiple electronic units. A smoke detector is connected to the electronic unit and operates to identify a smoke event. A cooling system is connected to the electronic unit. A fan in the cooling system includes a switch which indicates if a cooling system fault occurs. A plurality of relays connect to the electronic unit, the smoke detector and the cooling system. If a cooling system fault occurs, a first relay immediately de-energizes the cooling system. After a fixed period of smoke persistence during a smoke event, a second relay de-energizes the cooling system.

Abstract: A forward in flight entertainment system (IFE) which allows air to be directed to and exhausted from the IFE equipment in isolation from the cabin conditioned air. Further, potential IFE generated smoke may be kept isolated from the cabin air. The forward IFE equipment is located in forward sections of the aircraft system switching from ground to air mode is accomplished through air/ground signal 10 responsive to landing gear truck tilt. Once the air/ground transition from ground mode to air mode has occurred, ventilation valves 1 and 2 will be closed and the heated air will be exhausted overboard by forward IFE cooling overboard valve 4 whose overboard flow increases with altitude and cabin to ambient pressure differential.

Abstract: In an air conditioning system for an aircraft, two pre-mixing units respectively mix cold air from two air conditioning units with recirculated fuselage interior air from two recirculation units, to prepare two pre-mixed air flows that are both directed into and mixed together in a common air distribution mixing chamber, from which mixed air distribution lines branch off to respectively associated separate air conditioning zones within the fuselage. Post-mixing units are respectively interposed in the mixed air distribution lines and respectively mix additional quantities of recirculated fuselage interior air into the mixed air distribution lines. Thereby, the admixture of recirculated air is divided into at least two stages, the system provides redundant failure tolerant operation, and the danger of ice formation in the air lines is reliably prevented even while the air conditioning units provide cold air at a temperature below the water freezing point.

Abstract: The present invention relates to a hot-air supply system for an aircraft equipped with at least one engine (2) with a fan (3) and compressors (4). According to the invention, the regulating devices (14, 15, 16) intended to regulate the flows of hot air and of cold air sent by the pipes (10 and 11) to the heat exchanger (12) are pneumatic, controlled electrically, and are controlled by a centralized management device (24).