Aircraft propulsion assembly comprising a fan conjointly driven by two engines

Patent metadata

Field	Value
Publication number	US-2018327104-A1
Application number	US-201815919970-A
Country	US
Kind code	A1
Filing date	Mar 13, 2018
Priority date	Mar 14, 2017
Publication date	Nov 15, 2018
Grant date	—

Abstract

An aircraft propulsion assembly including a fan. It include a first engine and a second engine which are not coaxial and a mechanical energy transmission device configured to enable the fan to be conjointly rotated by the first engine and the second engine. This allows an aircraft propulsion assembly to be produced of which the fan may be positioned so as to ingest the boundary layer formed at the surface of a member of the aircraft equipped with the propulsion assembly, while allowing operating modes in the case of certain failures, and certification for commercial use of an aircraft equipped with such a propulsion assembly, to which the invention also relates.

First claim

1 . An aircraft propulsion assembly including a fan, including a first engine and a second engine which are not coaxial and a mechanical energy transmission device between:
a first output shaft of the first engine and a device for driving the fan; and a second output shaft of the second engine and the device for driving the fan, the transmission device being configured to allow rotation of the fan conjointly by the first engine and the second engine,
wherein each of the first and second engines is equipped with a backup airscrew and a disengageable drive device between the engine and its respective backup airscrew or includes a turbine able to generate thrust by post-combustion, so as to provide a backup propulsion function in an event of failure of the fan or an auxiliary propulsion function in climb phases at maximum angle of attack.

2 . The aircraft propulsion assembly according to claim 1 , in which the transmission device comprises:
a first transmission shaft connected to the first output shaft of the first engine, and a second transmission shaft connected to the second output shaft of the second engine,
the device for driving the fan including a first input to which the first transmission shaft is connected, a second input to which the second transmission shaft is connected, and an output to which the fan is connected.

3 . The aircraft propulsion assembly according to claim 1 , in which the transmission device includes a speed reducer.

4 . The aircraft propulsion assembly according to claim 1 , in which the transmission device includes a coupler or decoupler between the output shafts of the engines and the fan.

5 . The aircraft propulsion assembly according to claim 4 ,
in which the transmission device comprises: a first transmission shaft connected to the first output shaft of the first engine, and a second transmission shaft connected to the second output shaft of the second engine, the device for driving the fan including a first input to which the first transmission shaft is connected, a second input to which the second transmission shaft is connected, and an output to which the fan is connected; and in which the coupler or decoupler between the output shafts of the engine and the fan include a coupling or decoupling system on each of the first transmission shaft and the second transmission shaft.

6 . An aircraft including an oblong fuselage and including a propulsion assembly, the propulsion assembly comprising:
a fan, including a first engine and a second engine which are not coaxial and a mechanical energy transmission device between: a first output shaft of the first engine and a device for driving the fan; and a second output shaft of the second engine and the device for driving the fan, the transmission device being configured to allow rotation of the fan conjointly by the first engine and the second engine, wherein each of the first and second engines is equipped with a backup airscrew and a disengageable drive device between the engine and its respective backup airscrew or includes a turbine able to generate thrust by post-combustion, so as to provide a backup propulsion function in an event of failure of the fan or an auxiliary propulsion function in climb phases at maximum angle of attack; and the fan being fixed to a aft portion of the fuselage substantially centered on a principal axis (A) of the fuselage, and the first engine and the second engine being disposed on respective opposite sides of the fuselage.

7 . The aircraft according to claim 6 , in which the first engine and the second engine are fixed to a respective end of a horizontal or V-shaped tailplane.

8 . The aircraft according to claim 6 , in which the first engine and the second engine are fixed to a nacelle of the fan.

Assignees

• Airbus Operations Sas

Inventors

• Abele Antoine
• Rogero Jean-Michel
• Guillemaut Julien
• Belleville Mathieu

Classifications

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2260/84

  Redundancy · CPC title

• B64D35/08 Primary

  characterised by the transmission being driven by a plurality of power plants (for hybrid-electric power plants B64D35/022) · CPC title

• F05D2220/323

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