Aircraft with a propulsion unit with offset fan

Patent metadata

Field	Value
Publication number	US-10850859-B2
Application number	US-201615284895-A
Country	US
Kind code	B2
Filing date	Oct 4, 2016
Priority date	Oct 5, 2015
Publication date	Dec 1, 2020
Grant date	Dec 1, 2020

Abstract

An aircraft includes a wing having a first upstream spar and a second downstream spar extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream spar via at least one first and second fastener.

First claim

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

1. An aircraft comprising:
a wing comprising a first upstream spar and a second downstream spar extending in a direction of the span of said wing, and
at least one propulsion unit supported by the wing, the propulsion unit comprising a turbine engine and a propeller,
wherein the turbine engine extends along a first axis and comprises a fan and a gas generator arranged downstream of the fan,
wherein the propeller extends along a second axis and comprises a plurality of fan blades surrounded by an external annular casing, wherein the external annular casing is fixed to the first upstream spar via at least a first fastener, and the second axis is distinct from the first axis,
wherein the external annular casing comprises an air-inlet lip arranged upstream of a plane transverse to the leading edge of the wing.

2. The aircraft according to claim 1 , wherein the external annular casing is fixed to the downstream spar via a second fastener.

3. The aircraft according to claim 1 , wherein the external annular casing is fixed to one of the spars via a first strut.

4. The aircraft according to claim 1 , wherein the propeller comprises at least one movable hub, a central casing supporting the movable hub, and radial arms connecting the central casing to the external annular casing.

5. The aircraft according to claim 1 , wherein either the turbine engine or the propeller is fixed under the wing and the other one is fixed on top of the wing, the first axis of the turbine engine and the second axis of the propeller being situated in the same vertical plane.

6. The aircraft according to claim 5 , wherein the turbine engine is suspended from the wing via a second strut.

7. The aircraft according to claim 1 , wherein the turbine engine is a multiflow turbojet engine or a turboprop engine.

8. The aircraft according to claim 1 , wherein the turbine engine comprises at least one free-turbine stage driving said propeller.

9. The aircraft according to claim 1 , wherein the turbine engine and/or propeller is equipped with a thrust reverser.

10. An aircraft comprising:
a wing comprising a first upstream spar and a second downstream spar extending in a direction of the span of said wing, and
at least one propulsion unit supported by the wing, the propulsion unit comprising a turbine engine and a propeller, the turbine engine and propeller extending along a first and second axis, respectively,
wherein the propeller comprises a plurality of fan blades surrounded by an external annular casing, wherein the external annular casing is fixed to the first upstream spar via at least one of a first fastener and a second fastener,
wherein either the turbine engine or the propeller is fixed under the wing and the other one is fixed on top of the wing, the first axis of the turbine engine and the second axis of the propeller being situated in the same vertical plane,
wherein the external annular casing comprises an air-inlet lip arranged upstream of a plane transverse to the leading edge of the wing.

11. An aircraft comprising:
a wing comprising a first upstream spar and a second downstream spar extending in a direction of the span of said wing, and
at least one propulsion unit supported by the wing, the propulsion unit comprising a turbine engine and a propeller,
wherein the propeller comprises a plurality of fan blades surrounded by an external annular casing, wherein the external annular casing is fixed to the first upstream spar via at least one of a first fastener and a second fastener,
wherein the turbine engine comprises at least one free-turbine stage driving said propeller,
wherein the external annular casing comprises an air-inlet lip arranged upstream of a plane transverse to the leading edge of the wing.

12. The aircraft according to claim 1 , wherein the external annular casing is fixed to the first upstream spar via the first fastener and a second fastener.

13. The aircraft according to claim 1 , wherein the fan is surrounded by a casing which is distinct from external annular casing of the propeller.

Assignees

• Safran Aircraft Engines

Inventors

• Lemarchand Kevin Morgane
• Boudebiza Tewfik
• Charier Gilles Alain
• Nowakowski Nathalie

Classifications

• B64D27/18 Primary

  within, or attached to, wings · CPC title

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D35/04 Primary

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

• B64D27/12

  within, or attached to, wings · CPC title

• F02K1/54

  Nozzles having means for reversing jet thrust (reversing jet thrust using fluid jets F02K1/32) · CPC title