Airbus Operations Gmbh

Airbus Deutschland Gmbh

Hamilton Sundstrand Corporation

Juergen Kelnhofer

Dariusz Krakowski

Uwe Buchholz

Thomas Scherer

John M Maljanian

Steffen Kalsow

Walter S Hojnowski

Alvy Biccum

David Leenhouts

Stefan Gumm

Jose-Javier Francisco-Palomares

Marcus Petrac

A method for controlling an aircraft air conditioning system includes the steps of detecting an operating state of an air conditioning unit of the aircraft air conditioning system and controlling the temperature of a process air mass flow supplied to the air conditioning unit in dependence on the operating state of the air conditioning unit.

Method and device for controlling an aircraft air conditioning system

The invention pertains to a relief valve () for being arranged on an opening () of a fuselage shell of an aircraft, wherein the opening () has a front opening edge () and a rear opening edge (), and wherein the relief valve () features:

Relief valve for being arranged on an opening of a fuselage shell of an aircraft, fuselage part with such a relief valve and aircraft fuselage

A system for cooling an aircraft zone includes a mixing chamber which is connected to an air-conditioning assembly for making cool air available and/or to a recirculated-air conveying device for supplying recirculated air into the mixing chamber. The system further includes an aircraft-side air-distribution system which includes at least one line connecting the mixing chamber to the aircraft zone to be cooled and also at least one line that is connectable to an aircraft-external air-generating assembly in order to route air made available by the aircraft-external air-generating assembly into the aircraft-side air-distribution system.

System and process for cooling an aircraft zone using an aircraft-external air assembly

A system for cooling a heat exchanger on board an aircraft includes an engine bleed air line connected to an engine of the aircraft and adapted to supply engine bleed air to the heat exchanger. The system further includes a process air line branching off from the engine bleed air line such that the engine bleed air is supplied to the process air line and connecting to an input side of a turbine. The system also includes a cooling air line connected to an output side of the turbine such that cooling air produced by an expansion of the engine bleed air supplied to the turbine is supplied to the cooling air line and then to the heat exchanger. The heat exchanger is adapted to transfer cooling energy from the cooling air to the engine bleed air supplied to the heat exchanger from the engine bleed air line.

System for cooling a heat exchanger on board an aircraft

The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device.

Compressor/turbine arrangement, air conditioning unit and method for operating a compressor/turbine arrangement

A system for cooling an aircraft region includes an air-conditioning unit for providing cool air, a circulating air conveying device, and a mixing chamber which is connected to the air conditioning unit via an air distribution line and to which circulating air can be fed by the circulating air conveying device. An inlet line which is connected to an aircraft-side connection for an aircraft-external air unit opens into the air distribution line connecting the air conditioning unit to the mixing chamber. Therefore, air flows from the aircraft-external air unit and air flow from the air-conditioning unit are simultaneously provided to the mixing unit and then to the aircraft region.

System for cooling an aircraft zone, to be connected to an aircraft-external air unit

A ventilation system for ventilation of an aircraft area includes a ram-air duct with an air inlet, a first ram-air duct branch and a second ram-air duct branch parallel to the first ram-air duct branch. A supply line connected to the ram-air duct is adapted to supply air flowing through the ram-air duct to the aircraft area to be ventilated. In the first ram-air duct branch a conveying device is arranged. In the second ram-air duct branch a heat exchanger of an aircraft system to be supplied with cooling energy is arranged. The ventilation system provides ventilation to the aircraft area during ground operation without requiring the conveying device to flow air through the heat exchanger.

System for ventilation of an aircraft area

A method and a device determines an air mass flow flowing through a ram air channel having disposed therein a feed device adapted in a first operating state of the ram air channel to feed air through the ram air channel and further adapted in a second operating state of the ram air channel to be set in rotation by an air mass flow flowing through the ram air channel. The method includes the step of detecting an actual operational characteristic of the feed device that is characteristic of the air mass flow flowing through the ram air channel in the second operating state of the ram air channel as well as the step of determining the air mass flow flowing through the ram air channel on the basis of the detected actual operational characteristic of the feed device.

Method and device for determining an air mass flow flowing through a ram air channel

An arrangement is provided for de-icing pipeline connections of an aircraft, which are connected to all fresh air outlets of an air conditioner, whose construction includes, but is not limited to the functions of multiple turbines and heat exchangers, having a first pipeline, which is connected to a first turbine, and a second pipeline, which is connected to a second turbine, the two pipelines, which are each connected downstream from the two turbines and to which process air is fed at the turbine outlets, being connected at the pipe ends and being continued using a third pipeline. The arrangement is characterized in that a first hot air source is fed hot fresh air from a bleed air system of the aircraft and is connected at its outlet to a fourth pipeline, into which temperature-reduced fresh air is fed from the hot air source. The fourth pipeline is connected at its pipe end to two further valve-regulated pipelines, of which a fifth or a sixth pipeline is connected to the first or the second pipeline, and through which temperature-reduced fresh air is transported and fed valve-regulated to the first and/or second pipeline.

Optimized defrosting regulation of parallel arranged fresh air outlets of air conditioners

In a method for controlling an aircraft air conditioning system, a correlation is established between a plurality of values of a process air mass flow supplied to an air conditioning unit of the aircraft air conditioning system and the fuel consumption of the aircraft. A correlation is also established between a plurality of values of an ambient air mass flow which is used to cool the process air mass flow supplied to the air conditioning unit of the aircraft air conditioning system and the fuel consumption of the aircraft. The process air mass flow and the ambient air mass flow are controlled in dependence on a predetermined cooling capacity of the aircraft air conditioning system such that the fuel consumption of the aircraft is minimized.

Method and system for controlling an aircraft air conditioning system with optimised fuel consumption

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

System for producing process air

A ram air inlet includes a channel with an intake in a wing leading edge, front and rear flaps arranged in the channel for selectively closing or opening the channel, and an actuator connected to the flaps. A front end of the front flap is pivotably connected by a fixed bearing to an aircraft structure adjacent the intake. A rear end of the rear flap is moveably and pivotably mounted to the aircraft structure via a movable bearing arrangement, e.g. a pivot bearing linearly movable in guide tracks, or a flexible lever connected to a fixed pivot bearing, or a swinging bearing pivotably connected to a fixed bearing. The opposite ends of the flaps are pivotably connected to each other by a third bearing. The actuator drives the third bearing to pivot the front flap between opened and closed positions, while the rear flap pivots and moves in the wing chord and/or thickness directions.

Aircraft ram air inlet with multi-member closure flap

An air discharge valve for an aircraft has an inner valve flap () and an outer valve flap () which partially overlap each other to form a nozzle of the Laval type with a nozzle inlet () converging toward a nozzle neck (S) and with a nozzle outlet () diverging away from the nozzle neck (S). The inner valve flap () has a trailing edge (A) hinged to the aircraft body and a first leading edge () facing in the flight direction and having a curved sectional configuration. The outer valve flap () has a second leading edge () hinged to the aircraft body and a trailing edge (A). Both flaps () have a wedge shape. An outwardly facing surface portion (B) of the inner flap () forms an air flow guide for air flowing out of the nozzle outlet (). An inwardly facing surface portion (B) of the outer flap () forms an air flow guide into the nozzle inlet () formed by the curved sectional configuration of the first leading edge () and by the inwardly facing surface portion (B).

Air discharge valve for an aircraft

A suspension arrangement for suspending an air conditioning system from an aircraft airframe structure includes a first suspension unit including plural individual suspension rods, and a second suspension unit including a base frame supported from vertical carrier members. Upper ends of the carrier members are secured to load-carrying suspension points of the airframe structure. Upper ends of the suspension rods are secured to load-introduction points on the base frame. Bottom ends of the suspension rods are secured to suspension points on the components of the air conditioning system. The frame provides a greater number and variety of suspension locations to accommodate a greater number of suspension rods for suspending the air conditioning system, with a smaller number of vertical carrier members being secured to corresponding suspension points on the airframe structure. An intermediate mounting support arrangement may further be provided between the suspension rods and the suspension frame.

Suspension for air generation units in aircraft

A cooling air arrangement for an aircraft air conditioning unit includes an air inlet, a heat exchanger, an outlet plenum, first and second air outlet channels branching from the plenum, and a fan arranged in the first outlet channel. During flight of the aircraft, external ram air driven into the air inlet flows primarily through the second outlet channel. During ground operation, the fan primarily sucks cooling air through the first outlet channel, which merges back into the second outlet channel at an air mixing junction that functions as an injector nozzle and a non-return flap valve. The first outlet channel is provided in a spiral housing of the fan, or in a smooth curved duct. The air inlet and outlet of the cooling air arrangement, and the air outlet of the air cycle machine, are oriented in the same direction, e.g. the flight forward direction.

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Jork, Germany

Juergen Kelnhofer