Cooling system

1. A cooling system for an aircraft, comprising:

a heat exchanger for cooling a hot fluid with cooling air, comprising:

a cooling air inlet in fluid communication with a cooling air outlet and

a hot fluid inlet in fluid communication with a hot fluid outlet by means of one or more hot fluid conduits,

wherein the one or more hot fluid conduits are configured to transfer heat between a flow of hot fluid flowing between the hot fluid inlet and the hot fluid outlet, and a flow of cooling air flowing between the cooling air inlet and the cooling air outlet;

an air intake configured to supply cooling air from outside of the cooling system to the heat exchanger, wherein the air intake is in fluid communication with the cooling air inlet of the heat exchanger; and

a Coandă-effect air amplifier comprising an air amplifier inlet, an air amplifier outlet, a pressurized air inlet and a pressurized air outlet configured as a nozzle, the Coandă-effect air amplifier being configured to create a flow of cooling air between the air amplifier inlet and the air amplifier outlet induced by a stream of pressurized air injected through the nozzle, wherein the air amplifier inlet is in fluid communication with the cooling air outlet of the heat exchanger,

wherein the one or more hot fluid conduits comprise a plurality of hot fluid conduits,

wherein the plurality of hot fluid conduits are arranged in a tubular configuration defining a hollow interior volume, and

wherein the cooling air flows between the hot fluid conduits from the plurality of hot fluid conduits and through the hollow interior volume of the tubular configuration of the hot fluid conduits such that spacings between adjacent hot fluid conduits of the plurality of hot fluid conduits form the cooling air inlet,

and wherein the cooling air flows from the hollow interior volume to the cooling air outlet without passing through the spacings between adjacent hot fluid conduits.

2. The cooling system according to claim 1 , wherein the one or more hot fluid conduits, the hot fluid inlet and the hot fluid outlet define at least part of a hot fluid circuit.

3. The cooling system according to claim 1 wherein the heat exchanger comprises a plurality of hot fluid circuits with corresponding hot fluid inlets and hot fluid outlets.

4. The cooling system according to claim 3 , wherein the hot fluid circuits are arranged in different sectors of the tubular configuration.

5. The cooling system according to claim 3 , wherein each hot fluid circuit is configured to transport a different hot fluid.

6. The cooling system according to claim 3 , wherein a value of at least one dimension of a hot fluid conduit of a first hot fluid circuit is different from a value of a at least one dimension of a hot fluid conduit of a second hot fluid circuit, wherein the at least one dimension of the hot fluid conduit of the first hot fluid circuit is the same as the at least one dimension of the hot fluid conduit of the second hot fluid circuit.

7. A power unit for an aircraft, comprising an engine and a cooling system according to claim 1 .

8. The power unit according to claim 7 , further comprising a source of high pressure air configured to feed the pressurized air inlet of the Coandă-effect air amplifier.

9. The power unit according to claim 7 , wherein one or more of the hot fluid inlets are in fluid communication with a hot fluid source of the engine.

10. The power unit according to claim 7 , wherein the cooling system is housed in a compartment, and the engine is housed in a compartment separated from the compartment housing the cooling system.

11. An aircraft comprising a power unit according to claim 7 .

12. The aircraft according to claim 11 , wherein the power unit is positioned in an aft section of the aircraft.

13. The aircraft according to claim 12 , wherein the cooling system is positioned in a housing with rails.