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

Patent metadata

Field	Value
Publication number	US-10814989-B2
Application number	US-201615349675-A
Country	US
Kind code	B2
Filing date	Nov 11, 2016
Priority date	Nov 13, 2015
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.

First claim

The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:

1. A propulsion assembly of an aircraft, comprising: a gas generator and two fans driven in rotation by the gas generator and offset on either side of a vertical plane passing through a longitudinal axis of said gas generator; an air inlet sleeve comprising an inlet pipe which is located substantially between the fans and oriented along a first axis that is substantially parallel and offset with respect to the longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator, wherein the inlet pipe has a front section, of which a projection in the downstream direction in parallel with the longitudinal axis passes outside the perimeter of the inlet opening of the gas generator.

2. The propulsion assembly according to claim 1 , wherein the two fans are contained in an aerodynamic fairing having an upper surface and a lower surface, and the front section of the inlet pipe is incorporated in an air inlet opening which extends between the two fans and between the upper surface and the lower surface of the fairing.

3. The propulsion assembly according to claim 2 , wherein the longitudinal axis of the gas generator passes inside the air inlet opening.

4. The propulsion assembly according to claim 2 , wherein the air inlet opening extends on either side of a fan plane containing the rotational axes of the two fans.

5. The propulsion assembly according to claim 3 , wherein the air inlet opening is formed in a single part.

6. The propulsion assembly according to claim 4 , 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.

7. The propulsion assembly according to claim 2 , wherein the air inlet opening feeds air entering both the inlet pipe and a ventilation flow path from which the air for cooling the propulsion assembly or of a wing of the aircraft is taken.

8. The propulsion assembly according to claim 7 , wherein the ventilation flow path is delimited partly by a wall of the inlet pipe, said wall separating the airflow entering the flow path into ventilation flows passing along an external casing of the gas generator.

9. The propulsion assembly according to claim 1 , wherein the discharge pipe comprises an inlet section which is divided downstream into two channels formed in order to circumvent a suspension of the gas generator.

10. A propulsion wing comprising the propulsion assembly according to claim 1 , which is suspended from the wing.

11. A propulsion wing comprising the propulsion assembly according to claim 1 , which is integrated in the wing.

12. The assembly according to claim 2 , wherein the air inlet opening is curved.

13. The assembly according to claim 12 , wherein the curved shape of the air inlet opening is an hour-glass shape or has rounded ends.

14. The assembly according to claim 1 , wherein each of the two fans of the assembly comprises a fan casing and each of the fan casings has air inlet lips which are defined in a geometrical plane, both geometrical planes of said inlet lips being in the same geometrical plane.

15. The assembly according to claim 10 , wherein each of the two fans of the assembly comprises a fan casing and the fan casings have air inlet lips which are defined in geometrical planes that are axially offset and parallel to each other so as to adapt to a sweep angle of the wing relative to an elongation axis of a fuselage.

Assignees

• Safran Aircraft Engines

Inventors

• Vessot Christian Sylvain
• Beutin Bruno Albert
• Chanez Philippe Gérard
• Lallia Mathieu Patrick Jean-Louis

Classifications

• F01D13/00

  Combinations of two or more machines or engines (F01D15/00 takes precedence; combinations of two or more pumps F04; fluid gearing F16H) · CPC title

• F05D2250/312

  the axes being parallel to each other · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D29/02

  associated with wings · CPC title