Aircraft with multiple fan propulsion assembly fixed under the wing

Patent metadata

Field	Value
Publication number	US-11059597-B2
Application number	US-201615765469-A
Country	US
Kind code	B2
Filing date	Sep 29, 2016
Priority date	Oct 5, 2015
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

An aircraft including a fuselage, a lateral support wing ( 1 ) and a propulsion assembly ( 100 ) mounted under the wing. The wing includes at least two structural spars ( 11 ba, 11 bf ) extending from the fuselage toward the tip of the wing, one of these ( 11 ba ) being upstream and the other ( 11 bf ) downstream. The propulsion assembly includes a gas generator ( 106 ) and at least two offset fans ( 102, 104 ) arranged on either side of the axis of the gas generator. The offset fans ( 102, 104 ) are attached directly to one of the spars ( 11 ba, 11 bf ) and the gas generator ( 106 ) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (α) with the axis of the fuselage. The two offset fans ( 102, 104 ) are axially offset from one another.

First claim

The invention claimed is:

1. An aircraft comprising
a fuselage,
a lateral lifting wing, and
a powerplant mounted under the wing,
wherein the wing comprises at least two structural spars extending from the fuselage towards the tip of the wing, one of said at least two structural spars being upstream in a flight direction and another one of said at least two structural spars being downstream,
wherein the powerplant comprises a gas generator having a first longitudinal axis and at least two offset fans, one of said at least two offset fans being arranged on a first side of a vertical plane extending along the first axis and another one of said at least two offset fans being arranged on a second side of the vertical plane,
wherein the at least two offset fans are attached directly to one of said at least two structural spars and the gas generator is attached directly to each of said at least two structural spars,
wherein each of said at least two offset fans comprises an air intake, each air intake is under and close to a leading edge of the wing, and
wherein the intake of at least one offset fan is further upstream relative to the intake of another one of the at least two offset fans along the first axis.

2. The aircraft according to claim 1 , wherein each of the at least two offset fans are attached to the upstream spar.

3. The aircraft according to claim 2 , wherein each of said at least two offset fans comprises a housing supported by the upstream spar via a suspension device connecting the housing to said upstream spar directly.

4. The aircraft according to claim 1 , wherein the lateral lifting wing comprising the leading edge which forms a sweepback of a given angle (a) with a longitudinal axis of the fuselage.

5. The aircraft according to claim 1 , wherein each of the at least two offset fans comprises a longitudinal axis, wherein the first axis of the gas generator is located higher than the longitudinal axes of the at least two offset fans.

6. The aircraft according to claim 1 , wherein the gas generator is integral with the wing, and wherein an outer envelope of the gas generator is formed at least partly by a part of a wall forming a lower surface and/or an upper surface of the wing.

7. The aircraft according to claim 6 , wherein at least part of an envelope of at least one of the at least two offset fans is formed by a part of a wall forming a lower surface and/or an upper surface of the wing.

8. The aircraft according to claim 1 , wherein the gas generator comprises a gas ejection nozzle, and, wherein an axis of an ejected gas stream forms an angle (β) between 5 and 25° downwards with a horizontal plane.

9. The aircraft according to claim 1 , wherein the gas generator comprises a gas ejection channel directing a gas flow along an upper surface of the wing.

10. The aircraft according to claim 1 , wherein each of the at least two structural spars is formed in one piece.

11. The aircraft according to claim 1 , wherein the powerplant is suspended from at least one of said at least two structural spars.

Assignees

• Safran Aircraft Engines

Inventors

• Beutin Bruno Albert
• Aussedat Nicolas Maurice Herve
• Bader Nicolas Alain
• Chanez Philippe Gerard
• Charier Gilles Alain
• Lallia Mathieu
• Lefranc Lionel Jean Leon
• Lemarchand Kevin Morgane
• Mouton Herve Jean Albert
• Sirvin Nicolas Joseph
• Toupet Ludovic Michael Laurent
• Vessot Christian Sylvain
• Nowakowski Nathalie

Classifications

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• F02K1/52

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

• F05D2220/323

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

• B64C3/32

  specially adapted for mounting power plant · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title