| CPC B64D 13/08 (2013.01) [B64D 13/02 (2013.01); B64D 2013/0644 (2013.01); B64D 2013/0648 (2013.01)] | 7 Claims |

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1. An energy recovery device for an aircraft comprising:
a turbine that is provided between a cabin of the aircraft and an opening for discharging cabin discharge air from the cabin to outside of the aircraft;
a power generator that is driven by the turbine;
a plurality of cooling units that are provided between the cabin and the turbine, each of the plurality of cooling units including a heat conducting member, the heat conducting member being configured to exchange heat;
a plurality of first flow channels, each of the plurality of first flow channels having a first end and a second end; and
one second flow channel, the one second flow channel having a third end and a fourth end, wherein
the first end is connected with each of the plurality of cooling units,
the second end is connected with the third end,
the fourth end is connected with the turbine,
each of the plurality of cooling units is configured to cool each of a plurality of electrical instruments and heat the cabin discharge air using the heat conducting member, and discharge heated cabin discharge air to the turbine via each of the plurality of first flow channels and the second flow channel, and
the turbine is configured to rotate using only a total fluid obtained by totaling a plurality of flows of the heated cabin discharge air discharged from the plurality of cooling units.
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