An air temperature sensing apparatus and a system for an aircraft includes an ejector with a first air duct for receiving a first air flow from an aircraft air distribution duct, the first air duct defining a first cross-sectional area, a second air duct for receiving a second air flow from a passenger compartment of the aircraft, the second air flow merging with the first air flow downstream of the second air duct, and a restrictor connected to the first air duct defining a minimal cross-sectional area. The apparatus and system also include a temperature sensor in fluid communication with the second air flow. The minimal cross-sectional area of the restrictor is smaller than the first cross-sectional area of the first air duct to create a region of low pressure within the ejector, causing the second air flow to be suctioned over the temperature sensor.
AIRCRAFT CABIN AIR TEMPERATURE SENSING APPARATUS AND SYSTEM USING PASSIVE AIR FLOW
VORRICHTUNG UND SYSTEM ZUR MESSUNG DER FLUGZEUGKABINENLUFTTEMPERATUR MIT PASSIVEN LUFTSTROM
APPAREIL ET SYSTÈME DE DÉTECTION DE TEMPÉRATURE D'AIR DE CABINE D'AÉRONEF UTILISANT UN FLUX D'AIR PASSIF
2020-04-01
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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