Device and method for temperature control in an aircraft cabin

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.

Description

technical field [0001] The present invention generally relates to temperature control in aircraft cabins. Background technique [0002] For temperature control in aircraft cabins, a commonly used system is to extract hot exhaust air from the turbines of the aircraft drives. This hot air, called drive unit exhaust air, is cooled to the temperature required in the aircraft cabin. In an aircraft, the aircraft cabin is divided into different temperature zones or climate zones, and a portion of the hot air is cooled to the lowest temperature of one or more temperature zones. In order to obtain a higher temperature in other temperature areas, part of the hot air is diverted before it is cooled to the minimum temperature, and it is cooled to a slightly lower degree to thereby reach a temperature higher than the minimum temperature, and it is compared with the temperature already cooled to the minimum temperature. The temperature of the air is mixed so that the desired temperature...

AI Technical Summary

Problems solved by technology

[0017] Thereafter, the supply of heated air from valve 78 to non-faulty valves 60-64 by opening valve 88 is not possible since the failed valve 58 is also supplied with heated air.

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