Propulsion assembly for an aircraft, comprising a gas generator and two offset fans

Patent metadata

Field	Value
Publication number	US-10518890-B2
Application number	US-201615346612-A
Country	US
Kind code	B2
Filing date	Nov 8, 2016
Priority date	Nov 13, 2015
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17′) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.

First claim

The invention claimed is:

1. A propulsion assembly for an aircraft, intended to be attached below a wing of said aircraft, the assembly comprising a single gas generator and two fans being each driven in rotation by the gas generator and offset on either side of a vertical plane passing through a longitudinal axis of the gas generator, the rotational axes of the fans lying substantially in the same fan plane, wherein the propulsion assembly comprises an air inlet fairing formed upstream of a nacelle connecting the fans, said fairing having, between the fans, an air inlet opening lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator with a part of the air entering through the air inlet and to take off, from the remaining part of the air entering through the air inlet opening, a cooling airflow intended to cool elements of the propulsion assembly and/or the wing supporting the propulsion assembly.

2. The assembly according to claim 1 , wherein said fairing has a front wall arranged between the fans and upstream of the gas generator, the front wall being provided with the air inlet opening.

3. The assembly according to claim 1 , wherein the longitudinal axis of the gas generator passes inside the air inlet opening.

4. The assembly according claim 1 , wherein the fans have air inlet lips defined in the same plane.

5. The assembly according to claim 1 , wherein the fans have air inlet lips defined in planes that are offset axially and substantially parallel.

6. The assembly according to claim 4 , wherein the air inlet opening is situated substantially in the same plane as the one defined by the air inlet lip of the fan furthest downstream.

7. The assembly according to claim 1 , wherein the air inlet opening is formed in a single part.

8. The assembly according to claim 1 , wherein the air inlet opening is formed by two parts distributed on either side of the fan plane and separated from each other by a wall.

9. The assembly according to claim 1 , wherein the air inlet opening is symmetrical with respect to a vertical plane passing through the longitudinal axis of the gas generator.

10. The assembly according to claim 2 , wherein the longitudinal axis of the gas generator is situated above the fan plane, and the air supply device comprises an air inlet sleeve supplying the gas generator, said air inlet sleeve comprising upstream an inlet pipe having an opening situated essentially below the fan plane.

11. The assembly according to claim 10 , wherein the air supply device comprises a ventilation pipe situated essentially above the fan plane and from which the cooling airflow is taken.

12. The aircraft propulsion wing, wherein the aircraft supports a propulsion assembly according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Chanez Philippe Gerard
• Lallia Mathieu Patrick Jean-Louis
• Vessot Christian Sylvain

Classifications

• F02K1/52

  Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F02K3/077

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2250/312

  the axes being parallel to each other · CPC title