Aircraft with an offset nacelle aligned with the wake of the wing

Patent metadata

Field	Value
Publication number	US-2022242583-A1
Application number	US-202217721549-A
Country	US
Kind code	A1
Filing date	Apr 15, 2022
Priority date	Oct 15, 2019
Publication date	Aug 4, 2022
Grant date	—

Abstract

An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.

First claim

What is claimed is:

1 . An aircraft comprising a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft, the nacelle forming an air inlet fairing of a propulsion assembly, the nacelle including a lower wall and an upper wall delimiting together a height of the nacelle, the lower wall comprising an air inlet edge being contiguous with a trailing edge of the wing.

2 . The aircraft according to claim 1 , wherein the nacelle extends laterally from the fuselage of the aircraft in an oblong rectangular shape.

3 . The aircraft according to claim 1 , wherein the air inlet edge of the lower wall is downstream of an upper surface of the wing while being parallel to the trailing edge of the wing.

4 . The aircraft according to claim 1 , wherein the propulsion assembly comprises a plurality of fans.

5 . The aircraft according to claim 4 , wherein the nacelle comprises partitions of the fans.

6 . The aircraft according to claim 1 , wherein the nacelle is mechanically connected to the wing by at least one pylon.

7 . The aircraft according to claim 6 , wherein the propulsion assembly is formed of gas turbines powered by a gas generator, each gas turbine being associated with a fan.

8 . The aircraft according to claim 7 , wherein the at least one pylon is configured to allow the passage of a gas supply conduit of the gas turbines.

9 . The aircraft according to claim 7 , wherein outlet nozzles of the gas turbines have a Y shape for the passage of gas supply conduits of each of the gas turbines.

10 . The aircraft according to claim 9 , further comprising a distribution duct configured to envelop each of the gas supply conduits extending along the nacelle.

11 . The aircraft according to claim 7 , wherein the gas generator is integrated into the nacelle.

12 . The aircraft according to claim 7 , wherein the gas generator is directly coupled to one of the fans of the propulsion assembly.

13 . The aircraft according to claim 7 , wherein the gas generator is carried by the lower surface of the wing.

14 . The aircraft according to claim 7 , wherein the gas generator is carried directly by the fuselage of the aircraft.

15 . The aircraft according to claim 1 , wherein the propulsion assembly is formed of mechanical transmission turbines powered by a mechanical transmission generator, each mechanical transmission turbine being associated with a fan.

Assignees

• Safran Nacelles
• Safran Aircraft Engines
• Inst Superieur De Laeronautique Et De Lespace

Inventors

• Gonidec Patrick
• Aguirre Miguel Angel
• Tantot Nicolas
• Beutin Bruno
• Robic Bernard
• Duplaa Sébastien

Classifications

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64D29/04

  associated with fuselages · CPC title

• Y02T50/10

  Drag reduction · CPC title