Aircraft propulsion system including a heat exchanger system

Patent metadata

Field	Value
Publication number	US-11215118-B2
Application number	US-201916712232-A
Country	US
Kind code	B2
Filing date	Dec 12, 2019
Priority date	Dec 14, 2018
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

First claim

The invention claimed is:

1. A propulsion system of an aircraft, the propulsion system including a turbojet including a plurality of compression stages and a fan duct, and a heat exchanger system, which comprises:
a heat exchanger fastened in the fan duct and including a supply connection, a transfer connection disposed aft of the heat exchanger and pneumatically connected to the supply connection through the heat exchanger, at least one scoop connection and an evacuation connection pneumatically connected to each scoop connection of the at least one scoop connection through the heat exchanger;
a supply pipe connected to the supply connection and configured to bleed a hot air from the compression stages and supply the heat exchanger with the bled hot air;
a transfer pipe connected to the transfer connection for transferring hot air that has passed through the heat exchanger to an air management system of the aircraft;
for each scoop connection of the at least one scoop connection, a scoop, which is connected to the scoop connection and which is configured to bleed a cold air from the fan duct and supply the heat exchanger with the bled cold air; and
an evacuation pipe, which includes an inlet connected to the evacuation connection and an outlet, which emerges outside;
wherein passage of hot air through the heat exchanger from the supply pipe to the transfer pipe can be along a first transfer direction and passage of the bled cold air through the heat exchanger from each scoop to the inlet can be along a second transfer direction parallel to the first transfer direction but in an opposite direction, and
wherein the supply connection is disposed forward of the heat exchanger, the at least one scoop connection is disposed aft of the heat exchanger, and the evacuation connection is disposed forward of the heat exchanger.

2. The propulsion system according to claim 1 , comprising a pylon with a primary structure, which supports the turbojet, wherein the heat exchanger is fastened above the primary structure and wherein the primary structure includes a window through which the supply pipe is assembled between the turbojet and the heat exchanger.

3. The propulsion system according to claim 2 , wherein the bled hot air through the heat exchanger from the supply pipe to the transfer pipe goes from forward to aft, and the bled cold air through the heat exchanger from each scoop to the inlet goes from aft to forward.

4. The propulsion system according to claim 1 , comprising a pylon with a primary structure, which supports the turbojet and wherein the heat exchanger is fastened below the primary structure.

5. The propulsion system according to claim 4 , wherein the bled hot air through the heat exchanger from the supply pipe to the transfer pipe goes from aft to forward, and the bled cold air through the heat exchanger from each scoop to the inlet goes from forward to aft.

6. The propulsion system according to claim 1 , wherein each scoop includes a door which is mobile between an open position in which the door does not blank off the scoop and a closed position in which the door blanks off the scoop.

7. The propulsion system according to claim 1 , wherein the heat exchanger includes a first stage and a second stage disposed aft of the first stage, a plurality of first cold channels and a plurality of first hot channels are configured to be placed in the first stage, a plurality of second cold channels and a plurality of second hot channels are configured to be placed in the second stage, wherein the first cold channels and the second cold channels are connected together, wherein the first hot channels and the second hot channels are connected together, wherein forward of the first stage, the first hot channels are connected to the supply connection, wherein forward of the first stage, the first cold channels are connected to the evacuation connection, wherein the second stage has a shape of a truncated pyramid, which has a large base and a small base perpendicular to the first transfer direction and which has two sides inclined between the large base and the small base, wherein the large base constitutes a junction zone between the first stage and the second stage, wherein the small base constitutes a zone where only the second hot channels emerge and where a junction is made with the transfer connection, and wherein each side of the two sides constitutes a zone where only the second cold channels emerge and where a junction is made with one of the at least one scoop connection.

8. The propulsion system according to claim 1 , wherein the heat exchanger includes a first stage and a second stage disposed aft of the first stage, wherein a plurality of first cold channels and a plurality of first hot channels are placed in the first stage, wherein a plurality of second cold channels and a plurality of second hot channels are placed in the second stage, wherein the first cold channels and the second cold channels are connected together, wherein the first hot channels and the second hot channels are connected together, wherein forward of the first stage, the first hot channels are connected to the supply connection, wherein forward of the first stage, the first cold channels are connected to the evacuation connection, wherein the second stage has a shape of a two-sided pyramid, which has a base perpendicular to the first transfer direction and two sides inclined from the base, wherein the base constitutes a junction zone between the first stage and the second stage, wherein one of the sides constitutes a zone where only the second cold channels emerge and where a junction is made with the at least one scoop connection, and wherein the other side of the two sides constitutes a zone where only the second hot channels emerge and where a junction is made with the transfer connection.

9. The propulsion system according to claim 8 , comprising at an inlet of each second cold channel and at an outlet of each second hot channel, at least one deflector element.

10. An aircraft including at least one propulsion system according to claim 1 .

Assignees

• Airbus Sas
• Airbus Operations Sas
• Airbus Operations Sl

Inventors

• Medda Bruno
• Stevens Thomas
• Cayssials Julien
• Soulie Adeline
• Poirier Didier
• Pinault Pierre-Alain
• Martino González Esteban
• Prieto Padilla Juan Tomas
• Barron Vega Diego

Classifications

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• F02C7/10 Primary

  by means of regenerative heat-exchangers · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D13/08

  the air being heated or cooled · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title