System for cooling an aircraft turbojet engine

Patent metadata

Field	Value
Publication number	US-11994069-B2
Application number	US-202117490766-A
Country	US
Kind code	B2
Filing date	Sep 30, 2021
Priority date	Apr 3, 2019
Publication date	May 28, 2024
Grant date	May 28, 2024

Abstract

An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger.

First claim

What is claimed is:

1. A nacelle for a turbojet engine, the nacelle comprising:
an outer structure and an inner structure defining an annular flow path configured to direct a secondary air stream, the outer structure comprising an outer fairing defining an outer aerodynamic surface and an inner fairing defining an inner aerodynamic surface, the outer fairing and the inner fairing being connected upstream by a leading edge wall forming an air inlet lip;
a thrust reverser; and
a cooling system comprising:
a first heat-exchanger configured to exchange heat between a heat-transfer fluid and a lubricant of the turbojet engine;
a second heat-exchanger configured to exchange heat between the heat-transfer fluid and air;
a heat-transfer fluid inlet conduit configured to permit the heat-transfer fluid to flow into the second heat-exchanger; and
a heat-transfer fluid outlet conduit configured to permit the heat-transfer fluid to flow out of the second heat-exchanger,

wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit are configured to form a recirculation loop between the second heat-exchanger and the first heat-exchanger,
wherein the second heat-exchanger is movable relative to the first heat-exchanger and is disposed in the thrust reverser, and the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit are extendable, flexible, or extendable and flexible to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger.

2. The nacelle according to claim 1 , wherein the second heat-exchanger is a surface heat-exchanger.

3. The nacelle according to claim 2 , wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit comprise a deployable device configured to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger.

4. The nacelle according to claim 3 , wherein the deployable device is a telescopic tube.

5. The nacelle according to claim 4 , wherein the telescopic tube comprises several stages.

6. The nacelle according to claim 4 , wherein the telescopic tube comprises one single stage.

7. The nacelle according to claim 3 , wherein the deployable device is a bellow device.

8. The nacelle according to claim 7 further comprising a guide system configured to guide the movement of the bellow device.

9. The nacelle according to claim 8 , wherein the guide system is a tube comprising at least two portions configured so as to slide into one another.

10. The nacelle according to claim 8 , wherein the guide system includes a rail and a slide.

11. The nacelle according to claim 3 , wherein the deployable device is a flexible conduit adapted to be wound on itself and to be unwound to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger.

12. The nacelle according to claim 1 , wherein the second heat-exchanger is a structural heat-exchanger integral with the nacelle.

13. The nacelle according to claim 1 , wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit comprise a deployable device configured to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger.

Assignees

• Safran Nacelles

Inventors

• Corbin Julien
• Bouchout Jean-Nicolas
• Dang Caroline

Classifications

• F02C7/14 Primary

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

• F02K1/56

  Reversing jet main flow · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2250/41

  with one degree of freedom · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title