Aircraft air conditioning system providing auxiliary ventilation

Abstract

An air conditioning system for an aircraft includes a first rotatable shaft with a first compressor, a first turbine, a cooling air fan, and an auxiliary compressor connected for rotation therewith, and preferably further includes a second rotatable shaft with a second compressor and a second turbine connected for rotation therewith. A compression, cooling, and expansion cycle driven by at least the first compressor and the first turbine provides a principle flow of air conditioning air. The auxiliary compressor draws in outside air and provides a redundant auxiliary ventilation air flow, which is supplied into the installation space in which the air conditioning unit is installed, or another space in the aircraft that requires a reliable constant ventilation and cooling whenever the air conditioning unit is operational. The auxiliary ventilation air may be connected to a common air distribution network with other air conditioning units.

Description

PRIORITY CLAIM[0001] This application is based on and claims the priority under 35 U.S.C. .sctn.119 of German Patent Application 100 09 373.6, filed on Feb. 29, 2000, the entire disclosure of which is incorporated herein by reference.[0002] The invention relates to an air conditioning system especially for a passenger aircraft that includes at least one rotational shaft with a rotary compressor and a rotary turbine mounted thereon, to provide at least one compression stage and at least one expansion stage of an air cycle cooling process. The air conditioning system especially provides a redundant or auxiliary ventilation.BACKGROUND INFORMATION[0003] In all known aircraft having an integrated air conditioning system, the required cooling energy is recovered from highly compressed engine bleed air, through an air cycle including a thermodynamic air compression and expansion process with an intermediate cooling of the compressed air. Various condensation processes are provided in the c...

AI Technical Summary

Problems solved by technology

The energy that is transferred and transformed through such a cooling unit or air conditioning pack is unavoidably associated with power losses, which are given off as thermal heat energy and / or particularly thermal radiation, into the installation environment immediately surrounding the cooling unit.

The above mentioned heating of the installation space in which a cooling unit is installed in an aircraft is undesirable, because the installation space may overheat and require the cooling unit to be shut down, unless the heat can be removed from the installation space.

However, if this separate turbo-compressor fails for any reason, then the positive forced ventilation and cooling of the installation spaces of the air conditioning units will not be provided, whereupon these spaces and the associated air conditioning units will overheat and must necessarily be shut down.

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