Environmental control system tri-heat exchanger

Patent metadata

Field	Value
Publication number	US-10619937-B2
Application number	US-201815879234-A
Country	US
Kind code	B2
Filing date	Jan 24, 2018
Priority date	Jan 24, 2018
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

A heat exchanger assembly for an aircraft includes a first heat exchanger with a first hot air circuit, a second heat exchanger with a second hot air circuit, a third heat exchanger with a third hot air circuit, and a cold circuit. The first heat exchanger is in fluid communication with a source of bleed air from the engine. The second heat exchanger is disposed adjacent to and in fluid communication with the first heat exchanger. The third heat exchanger is disposed adjacent to and in fluid communication with the second heat exchanger. The first, second, and third heat exchangers are fluidly connected in series. The cold air circuit passes through each of the first, second, and third heat exchangers. The first, second, and third heat exchangers are in cross-flow communication with the cold air circuit.

First claim

The invention claimed is:

1. A heat exchanger assembly for an aircraft with an environmental control system, the heat exchanger assembly comprising:
a first heat exchanger with a first hot air circuit passing therethrough, wherein the first heat exchanger is in fluid communication with a source of bleed air from the aircraft;
a second heat exchanger with a second hot air circuit passing therethrough, wherein the second heat exchanger is disposed adjacent to and in fluid communication with the first heat exchanger;
a third heat exchanger with a third hot air circuit passing therethrough, wherein the third heat exchanger is disposed adjacent to and in fluid communication with the second heat exchanger, wherein the first, second, and third heat exchangers are fluidly connected in series;
a cold air circuit passing through each of the first, second, and third heat exchangers, wherein the first, second, and third heat exchangers are in cross-flow communication with the cold air circuit;
a first closure bar disposed between the first and second hot air circuits, wherein the first closure bar prevents fluid communication across the first closure bar between the first and second hot air circuits;
a second closure bar disposed between the second and third hot air circuits, wherein the second closure bar prevents fluid communication across the second closure bar between the second and third hot air circuits;
a first top Y-septum welded to a top end of the first closure bar;
a second top Y-septum welded to a top end of the second closure bar;
a first bottom Y-septum welded to a bottom end of the first closure bar; and
a second bottom Y-septum welded to a bottom end of the second closure bar.

2. The heat exchanger assembly of claim 1 , wherein the first heat exchanger comprises a bleed air heat exchanger, wherein the second heat exchanger comprises a fresh air heat exchanger, and wherein the third heat exchanger comprises a chiller heat exchanger.

3. The heat exchanger assembly of claim 1 , further comprising:
a plurality of hot layers, wherein each hot layer of the plurality of hot layers comprises a plurality of hot fins, wherein the first, second, and third hot air circuits are in fluid communication with the plurality of hot layers; and
a plurality of cold layers, wherein each cold layer of the plurality of cold layers comprises a plurality of cold fins, wherein the cold air circuit is in fluid communication with the plurality of cold layers.

4. The heat exchanger assembly of claim 1 , wherein each cold fin of the pluralities of cold fins is continuous and extends across an entire width of the heat exchanger assembly.

5. The heat exchanger assembly of claim 1 , wherein the first, second, and third heat exchangers are brazed together to form a single unitized tri-heat exchanger.

6. The heat exchanger assembly of claim 1 , further comprising:
a first top header and a first bottom header both in fluid communication with the first hot air circuit, wherein the first top header is welded to the first top Y-septum, wherein the first bottom header is welded to the first bottom Y-septum;
a second top header and a second bottom header both in fluid communication with the second hot air circuit, wherein the second top header is welded to the first top Y-septum, wherein the second bottom header is welded to the first bottom Y-septum; and
a third top header and a third bottom header both in fluid communication with the third hot air circuit, wherein the third top header is welded to the second top Y-septum, wherein the third bottom header is welded to the second bottom Y-septum.

7. The heat exchanger assembly of claim 1 , wherein the cold air circuit further comprises:
an inlet fluidly connected to a source of RAM air of the aircraft; and
an outlet fluidly connected to a fan inlet diffuser housing of the environmental control system of the aircraft.

8. The heat exchanger assembly of claim 1 , wherein the first hot air circuit is configured to direct a first flow of air, wherein the second hot air circuit is configured to direct a second flow of air, wherein the third hot air circuit is configured to direct a third flow of air, wherein directions of the first, second, and third flows of air are parallel to a direction of gravity.

9. The heat exchanger assembly of claim 1 , further wherein a direction of flow of the cold air circuit is perpendicular to directions of flow of the first, second, and third hot air circuits.

10. A method of transferring thermal energy in a heat exchanger assembly of an environmental control system, the method comprising:
passing hot air of a first hot air circuit through hot layers of a first heat exchanger of the heat exchanger assembly, wherein the first heat exchanger is in fluid communication with a source of bleed air from the aircraft;
passing hot air of a second hot air circuit through hot layers of a second heat exchanger of the heat exchanger assembly, wherein the second heat exchanger is disposed adjacent to and in fluid communication with the first heat exchanger;
passing hot air of a third hot air circuit through hot layers of a third heat exchanger of the heat exchanger assembly, wherein the third heat exchanger is disposed adjacent to and in fluid communication with the second heat exchanger, wherein the first, second, and third heat exchangers are fluidly connected in series, and wherein the first, second, and third heat exchangers are brazed together to form a single unitized tri-heat exchanger; and
passing cold air of a cold air circuit through cold layers of each of the first, second, and third heat exchangers, wherein a direction of flow of the cold air circuit is perpendicular to directions of flow of the first, second, and third hot air circuits, wherein the first, second, and third heat exchangers are in cross-flow communication with the cold air circuit; and
wherein the heat exchanger assembly comprises:
the first, second, and third heat exchangers;
a first closure bar disposed between the first and second hot air circuits, wherein the first closure bar prevents fluid communication across the first closure bar between the first and second hot air circuits;
a second closure bar disposed between the second and third hot air circuits, wherein the second closure bar prevents fluid communication across the second closure bar between the second and third hot air circuits;
a first top Y-septum welded to a top end of the first closure bar;
a second top Y-septum welded to a top end of the second closure bar;
a first bottom Y-septum welded to a bottom end of the first closure bar; and
a second bottom Y-septum welded to a bottom end of the second closure bar.

11. The method of claim 10 , further comprising:
mixing two separate cold air streams in an inlet plenum of the environmental control system to create a mixed air stream; and
feeding the mixed air stream into the cold air circuit.

12. The method of claim 10 , further comprising:
passing air from the first heat exchanger to the third heat exchanger through an external plenum mounted to at least two end walls of the first, second, and third heat exchangers.

13. The method of claim 10 , wherein passing the hot air through the hot layers of the first, second, and third heat exchangers comprises passing the hot air in a direction that is parallel to gravity.

14. A heat exchanger assembly for an aircraft, the heat exchanger assembly comprising:
a bleed air heat exchanger in fluid communication with a source of bleed air from the aircraft, the bleed air heat exchanger with a first hot air circuit passing therethrough;
a fresh air

Assignees

• Hamilton Sundstrand Corp

Inventors

• Army Donald E
• Peacos Iii Frederick

Classifications

• F28F9/0214

  having only longitudinal partitions · CPC title

• B64D13/02

  the air being pressurised · CPC title

• F28D2021/0021

  for aircrafts or cosmonautics · CPC title

• F28F3/02

  Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations (F28F3/08 takes precedence) · CPC title

• B64D13/08

  the air being heated or cooled · CPC title