Aircraft cooling system and aircraft with aircraft cooling system

Patent metadata

Field	Value
Publication number	US-11273918-B2
Application number	US-201916384297-A
Country	US
Kind code	B2
Filing date	Apr 15, 2019
Priority date	Apr 20, 2018
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

An aircraft cooling system and an aircraft having an aircraft cooling system of this type. The aircraft cooling system comprises a ram air duct, a nozzle arranged in the ram air duct and connected to a first water-conducting line, and a refrigeration device. The refrigeration device comprises a heat exchanger thermally coupled to the refrigeration device and configured to release waste heat generated by the refrigeration device to cooling air present in the ram air duct, a first water separator configured to separate off water from the air cooled by the refrigeration device, and a water outlet configured to conduct water obtained in the first water separator into the first water-conducting line. Furthermore, the water outlet has an inlet configured to be connected to a second water-conducting line, wherein the water outlet is furthermore configured to generate a negative pressure at the inlet.

First claim

The invention claimed is:

1. An aircraft cooling system having:
a ram air duct;
a nozzle arranged in the ram air duct and connected to a first water-conducting line;
a refrigeration device, comprising:
a heat exchanger thermally coupled to a different portion of the refrigeration device and configured to release waste heat generated by the refrigeration device to cooling air present in the ram air duct,
a first water separator configured to separate off water from air cooled by the refrigeration device, and
a water outlet configured to conduct water obtained in the first water separator into the first water-conducting line,
the water outlet having an inlet configured to be connected to a second water-conducting line,
the water outlet furthermore being configured to generate a negative pressure at the inlet;

a mixing chamber configured to mix two or more air streams to discharge a mixed air stream, wherein the mixing chamber comprises:
a second water separator configured to separate off condensation water that precipitates out in the mixing chamber,
the second water separator being connected via the second water-conducting line to the inlet of the water outlet of the refrigeration device upstream of the first water separator;

a source of compressed air configured to supply compressed air to the refrigeration device;
the refrigeration device being configured to expand the compressed air and cool the compressed air in the heat exchanger; and
a third water separator configured to separate off water at an inlet opening for a feed air stream supplied to the source of the compressed air, wherein the third water separator is connected by means of an outlet to the inlet of the water outlet of the refrigeration device.

2. The aircraft cooling system according to claim 1 , wherein the water outlet forms a Venturi nozzle, wherein a negative pressure formed by the Venturi nozzle is applied via the inlet to the second water-conducting line.

3. The aircraft cooling system according to claim 1 , wherein at least one of the first water separator or the water outlet of the refrigeration device is configured to pressurize the water that is introduced into the first water-conducting line.

4. The aircraft cooling system according to claim 3 , wherein the refrigeration device is configured to apply compressed air to the first water separator, such that the pressure is imparted to the water introduced into the first water-conducting line by the water separated off in the first water separator.

5. The aircraft cooling system according to claim 3 , wherein at least one of the first water separator or the water outlet of the refrigeration device comprises a conveying device configured to convey the water separated off in the first water separator through the first water-conducting line.

6. The aircraft cooling system according to claim 1 , furthermore comprising:
a fourth water separator configured to separate off water from the compressed air of the source, wherein the fourth water separator is connected by means of an outlet to the inlet of the water outlet of the refrigeration device.

7. The aircraft cooling system according to claim 1 , wherein
the ram air duct comprises an air inlet and an air outlet, such that ambient air flows through the ram air duct from the air inlet to the air outlet, wherein the heat exchanger is arranged downstream of the nozzle.

8. The aircraft cooling system according to claim 1 , wherein the ram air duct has an air conveying device for conducting ambient air through the ram air duct.

9. The aircraft cooling system according to claim 1 , wherein the mixing chamber furthermore comprises:
a first inlet configured to introduce a fresh air stream generated by the refrigeration device into the mixing chamber,
a second inlet configured to introduce a recirculation air stream extracted from an aircraft section into the mixing chamber, and
an outlet configured to supply the fresh and recirculation air streams introduced into the mixing chamber and mixed there to the aircraft section.

10. An aircraft comprising an aircraft cooling system according to claim 1 .

Assignees

• Airbus Operations Gmbh
• Airbus Operation GmbH

Inventors

• Klimpel Frank

Classifications

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title

• B64D13/08 Primary

  the air being heated or cooled · CPC title

• B64D2013/0674

  comprising liquid subsystems · CPC title

• B64D2013/0618

  with arrangements for reducing or managing bleed air, using another air source, e.g. ram air · CPC title