Triple-flow axial turbomachine comprising a diverging heat exchanger in the third flow

Patent metadata

Field	Value
Publication number	US-12372008-B2
Application number	US-202418824259-A
Country	US
Kind code	B2
Filing date	Sep 4, 2024
Priority date	Nov 30, 2021
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

An axial turbomachine including a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary f flow and a tertiary flow, said tertiary flow being in a tertiary flow vein radially external to said flow primary; and an air/oil type heat exchanger disposed in the tertiary flow stream and including heat exchange surfaces with air and oil passages extending in said tertiary flow stream; and structural arms extending radially through the tertiary flow vein. Each structural arm has in the tertiary flow vein a cross section with a downstream portion having a width decreasing towards the downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.

First claim

The invention claimed is:

1. An axial turbomachine, comprising:
a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow the radially external air flow defining a secondary flow;
a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, said tertiary flow being in a tertiary flow vein radially external to said primary flow; and
an air/oil type heat exchanger arranged in the tertiary flow stream and comprising heat exchange surfaces with air and oil passages extending into said tertiary flow vein; and
structural arms extending radially through the tertiary flow vein;
wherein each of the structural arms has in the tertiary flow vein a cross section with a downstream portion having a width decreasing towards the downstream, the heat exchanger being adjacent to said downstream portions of the structural arms, wherein the heat exchanger extends circumferentially between two structural arms so that said heat exchanger is in direct contact with at least one of said two structural arms, and wherein the heat exchange surfaces are adjacent to the downstream portions of the structural arms, said heat exchange surfaces have a diverging circumferential profile conforming to the downstream portions of the structural arms.

2. The axial turbomachine according to claim 1 wherein the circumferential profile diverging from the heat exchange surfaces is formed by lateral profiles directly adjacent to the structural arms, said lateral profiles each comprising an inclined lateral profile relative to an axial direction.

3. The axial turbomachine according to claim 1 , further comprising a stator disposed in the vein of the tertiary flow and upstream of each structural arm.

4. The axial turbomachine according to claim 1 , wherein each of the structural arms is arranged axially between a low pressure compressor and a high pressure compressor.

5. The axial turbomachine according to claim 1 , wherein each of the structural arms comprises an upstream portion comprising a leading edge, the heat exchanger being arranged downstream of said leading edge.

6. The axial turbomachine according to claim 1 , wherein the downstream portion of each structural arm comprises a trailing edge, the heat exchanger being arranged between a leading edge and said trailing edge.

7. The axial turbomachine according to claim 1 , wherein the heat exchanger is arranged at a level of a greatest width of the structural arms.

8. The axial turbomachine according to claim 1 , further comprising an internal casing disposed between the primary flow and the tertiary flow, said internal casing comprises a “VBV” channel having an outlet at the level of the tertiary flow vein, said outlet being arranged downstream of the heat exchanger.

9. The axial turbomachine according to claim 1 , wherein the heat exchanger extends circumferentially between two of the structural arms so that said heat exchanger is in direct contact with each of said two structural arms.

10. The axial turbomachine according to claim 9 , wherein the heat exchange surfaces comprise oil passages extending fluidly between an internal wall and an external wall of the tertiary flow vein.

11. The axial turbomachine according to claim 10 , wherein the internal wall and the external wall of the tertiary flow vein are integrally formed with the exchange surfaces.

12. The axial turbomachine according to claim 1 , wherein the heat exchange surfaces extend radially and are distributed angularly in the tertiary flow vein, said heat exchange surfaces being adjacent to the downstream portions of the structural arms and having an inclination with respect to an axial direction so as to conform to said downstream portions.

13. The axial turbomachine according to claim 1 , wherein a number per unit area of heat exchange surfaces adjacent to the lateral profile is greater by at least 20% to a number per unit area of heat exchange surfaces located in a central part of the exchanger.

14. The axial turbomachine according to claim 13 , wherein the number per unit area of heat exchange surfaces adjacent to the downstream portion increases progressively following the inclination of the inclined lateral profile.

15. The axial turbomachine according to claim 1 , wherein a number of heat exchange surfaces per unit area increases as the circumferential increase in the cross section increases to the heat exchange surfaces.

Assignees

• Safran Aero Boosters Sa

Inventors

• Weicker David
• Cleyet Florian
• Servais Bruno

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D25/12 Primary

  Cooling · CPC title