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The present application describes an arrangement and a method for utilizing the heat of waste air for heating the bilge area of aircraft, wherein the bilge area is connected to a heat transfer unit via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into th

The present application describes an arrangement and a method for utilizing the heat of waste air for heating the bilge area of aircraft, wherein the bilge area is connected to a heat transfer unit via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit, wherein the heat transfer unit comprises a second air supply pipe, through which a waste air heat flow to be cooled that is created at another location in the aircraft flows into the heat transfer unit in order to heat the drawn-in bilge air flow, wherein the heat transfer unit comprises a first air discharge pipe, through which the cooled waste air heat flow is discharged, and a second air discharge pipe with a bilge inlet section, and wherein at least a portion of the heated bilge flow is returned to the bilge area via the air discharge pipe and the bilge inlet section.

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1. An arrangement for utilizing heat of waste air for heating a bilge area of an aircraft, comprising a bilge area,a heat transfer unit connected to the bilge area via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit,the heat tran

1. An arrangement for utilizing heat of waste air for heating a bilge area of an aircraft, comprising a bilge area,a heat transfer unit connected to the bilge area via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit,the heat transfer unit being further connected to a second air supply pipe, through which a waste air heat flow to be cooled and that is created at another location in the aircraft flows into the heat transfer unit in order to heat the drawn-in bilge air flow;the heat transfer unit being further connected to a first air discharge pipe, through which the cooled waste air heat flow is discharged, and a second air discharge pipe with a bilge inlet section, whereby at least a portion of the heated bilge flow is returned to the bilge area via the second air discharge pipe and the bilge inlet section;wherein the arrangement is configured to recover electrical or mechanical energy by cooling the heated bilge flow emerging from the heat transfer unit. 2. The arrangement of claim 1, further comprising a third air discharge pipe: and a control valve arranged in the second air discharge pipe to branch the second air discharge pipe into the bilge inlet section and the third air discharge pipe, through which a portion of the heated bilge flow that does not flow into the bilge area can be discharged out of the arrangement. 3. The arrangement of claim 1, further comprising an air quantity control configured to return an air quantity of the bilge flow into the bilge area which is smaller than or equal to the air quantity of the bilge air flow drawn in from the bilge area. 4. The arrangement of claim 1, wherein the heat transfer unit comprises a heat exchanger or a refrigerating machine. 5. The arrangement of claim 1, wherein the waste air heat flow to be cooled consists of at least one of recirculated cabin air, galley waste air, lavatory waste air, waste air from the cooling of electric consumers or a hot air flow of the air-conditioning system of the aircraft. 6. The arrangement of claim 1, further comprising a turbo engine arranged in the second air discharge pipe operable to draw in the cooled waste air heat flow and the heated bilge flow, to compensate flow losses and to maintain the flow process. 7. The arrangement of claim 1, further comprising: a turbine arranged in the first air supply pipe and configured to expand and cool the drawn-in bilge air flow, anda compressor arranged in the second air discharge pipe and configured to additionally heat and compress the heated bilge flow to the bilge pressure level. 8. The arrangement of claim 7, further comprising a generator connected to the turbine. 9. The arrangement of claim 7, further comprising a shaft connecting the turbine to the compressor. 10. The arrangement of claim 7, further comprising a control valve arranged in the first air supply pipe between the turbine and the heat transfer unit, and the control valve being configured such that at least a portion of the drawn-in bilge air flow can be discharged through an opening via the control valve. 11. The arrangement of claim 7, further comprising a hot air pipe connected to the first air supply pipe between the bilge area and the turbine, such that a hot air flow created at another location in the aircraft can be supplied via the hot air pipe in order to heat the drawn-in bilge air flow before it is admitted into the turbine. 12. The arrangement of claim 1, further comprising a turbine arranged in the second air discharge pipe and operable to expand and cool the heated bilge flow emerging from the heat transfer unit, and a compressor arranged in the second air discharge pipe between the turbine and the bilge inlet section and operable to heat and compress the bilge flow arriving from the turbine to the bilge pressure level. 13. The arrangement of claim 12, further comprising a control valve arranged in the second air discharge pipe between the turbine and the compressor and operable to discharge at least a portion of the bilge flow arriving from the turbine through an opening.