An airplane is provided. The airplane includes a pressurized volume and an air conditioning system. The air conditioning system includes a compressor configured to receive a flow of a first medium, a turbine downstream of the compressor in a flow path of the first medium, a first valve that diverts the flow of the first medium around the turbine, a second valve that provides a second medium to the turbine, and a third valve downstream of the turbine that directs an outlet flow of the turbine towards the pressurized volume and that directs the outlet flow of the turbine away from the pressurized volume.

An airplane is provided. The airplane includes a pressurized volume and an air conditioning system. The air conditioning system includes a compressor configured to receive a flow of a first medium, a turbine downstream of the compressor in a flow path of the first medium, a first valve that diverts the flow of the first medium around the turbine, a second valve that provides a second medium to the turbine, and a third valve downstream of the turbine that directs an outlet flow of the turbine towards the pressurized volume and that directs the outlet flow of the turbine away from the pressurized volume.

A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.

A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.

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.

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.

Air conditioning system for a cabin (10) of an aircraft, comprising: an air bleed device; an air cycle turbine engine (12); at least one main cooling exchanger (16); a water extraction loop (30); and a pipe (26) for distributing water extracted by said extraction loop (30), characterized in that said system further comprises means (40) for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel (22) which supplies said main exchanger (16).

Thrust recovery outflow valves for aircraft are disclosed. An example thrust recovery outflow valve includes a flow control member having a first aerodynamic surface and a second aerodynamic surface to define at least a portion of a fluid flow passageway between an inlet and an outlet of the thrust recovery outflow valve. A first portion of the first aerodynamic surface and a first portion of the second aerodynamic surface provides a converging profile between the inlet and a throat of the fluid flow passageway. A second portion of the first aerodynamic surface and a second portion of the second aerodynamic surface provides a diverging profile between the throat and the outlet of the fluid flow passageway. The fluid flow passageway is positioned at a small angle relative to an outer surface of an aircraft to enable fluid exiting the fluid flow passageway to provide a thrust recovery vector oriented substantially parallel to the outer surface of the aircraft and opposite a direction of drag.

Thrust recovery outflow valves for aircraft are disclosed. An example thrust recovery outflow valve includes a flow control member having a first aerodynamic surface and a second aerodynamic surface to define at least a portion of a fluid flow passageway between an inlet and an outlet of the thrust recovery outflow valve. A first portion of the first aerodynamic surface and a first portion of the second aerodynamic surface provides a converging profile between the inlet and a throat of the fluid flow passageway. A second portion of the first aerodynamic surface and a second portion of the second aerodynamic surface provides a diverging profile between the throat and the outlet of the fluid flow passageway. The fluid flow passageway is positioned at a small angle relative to an outer surface of an aircraft to enable fluid exiting the fluid flow passageway to provide a thrust recovery vector oriented substantially parallel to the outer surface of the aircraft and opposite a direction of drag.

An aircraft air conditioning system comprising an ambient air supply line with a first end connected to an ambient air inlet and a second end connected to a mixing chamber. A first electrically driven ambient air compressor in the ambient air supply line compresses the ambient air flowing therethrough. A first ambient air branch line branches off from the ambient air supply line upstream of the first ambient air compressor and rejoins the supply line downstream of the air compressor. A second ambient air compressor in the first ambient air branch line compresses the ambient air flowing therethrough. A cabin exhaust air line has a first end connected to an air conditioned aircraft area. A cabin exhaust air turbine in the exhaust air line is driven by the exhaust air flowing through the cabin exhaust air line and is coupled to drive the second ambient air compressor.