Thrust reverser for an aircraft having semi-recessed turbofan engines

Patent metadata

Field	Value
Publication number	US-9062626-B2
Application number	US-201013520917-A
Country	US
Kind code	B2
Filing date	Dec 27, 2010
Priority date	Jan 8, 2010
Publication date	Jun 23, 2015
Grant date	Jun 23, 2015

Abstract

A propulsion unit comprising a turbofan engine faired by a nacelle, and held in suspension by at least one pylon, the turbofan engine including a fan; a duct, bounded by an internal surface of the duct and an inner surface of the nacelle, that channels air accelerated by the fan; and a thrust reverser including a first part and a second part, wherein the turbofan engine has a first circumferential sector and a second circumferential sector distinct from the first circumferential sector, wherein the first circumferential sector and the second circumferential sector span the entire turbofan engine, the first part is entirely within the first circumferential sector and includes doors that channel the air in the duct towards an exterior of the nacelle via openings, and the second part is entirely within the second circumferential sector and includes mobile elements that channel the air in the duct toward the doors.

First claim

The invention claimed is:

1. A jet propulsion unit of an aircraft, comprising:
a turbofan engine faired by a nacelle, and held in suspension by at least one pylon, the turbofan engine including a fan;
a duct that channels air accelerated by the fan, the duct being bounded by an internal surface of the duct and an inner surface of the nacelle; and
a thrust reverser device including a first part and a second part, wherein
the jet propulsion unit has a first circumferential sector and a second circumferential sector distinct from the first circumferential sector, wherein the first circumferential sector and the second circumferential sector span the entire turbofan engine,
the first part is entirely within the first circumferential sector and includes doors that channel the air in the duct towards an exterior of the jet propulsion unit via openings, and
the second part is entirely within the second circumferential sector and includes mobile elements that channel the air in the duct toward the doors.

2. The jet propulsion unit according to claim 1 , wherein the mobile elements comprise at least one internal deflector suited to constitute aerodynamic continuity of the inner surface of the nacelle when the deflector is in a propulsion position, and to channel the air toward the doors when the deflector is in a thrust reversal mode.

3. The jet propulsion unit according to claim 2 , wherein the at least one internal deflector comprises a first mobile surface, rotatably hinged, with a shape of the first mobile surface being continuous with the inner surface of the nacelle, when the first mobile surface is in an angular rest position and two edges of the first mobile surface are in substantial contact with the inner surface of the nacelle and with the internal surface of the duct respectively, when the first mobile surface is in an angular thrust reversal position.

4. The jet propulsion unit according to claim 3 , wherein the first mobile surface is located near the pylon which traverses the duct and supports the turbofan engine, the first mobile surface including a mount edge coming into substantial contact with a surface of the pylon when the first mobile surface is in the angular thrust reversal position.

5. The jet propulsion unit according to claim 2 , wherein the mobile elements include two internal deflectors, arrayed on each side of the pylon.

6. The jet propulsion unit according to claim 2 , wherein the at least one internal deflector is formed by at least two mobile surfaces, substantially in cylindrical or conical sectors, with each one of the at least two mobile surfaces being rotatably hinged on an axis separate from a longitudinal axis X of the turbofan engine, between an inoperative position in which the mobile surfaces are continuous with the inner surface of the nacelle, and a thrust reversal position, in which the mobile surfaces locally interrupt the air in the duct, and channel the air toward the doors.

7. The jet propulsion unit according to claim 6 , wherein the mobile surfaces comprise continuous edges facing and complementary to each other, configured to come into contact with each other when the said mobile surfaces are in the thrust reversal position.

8. The jet propulsion unit according to claim 3 , wherein the at least one mobile surface comprises an edge that comes into contact with an edge of one of the doors toward the inner surface of the nacelle, when the mobile surface and the one door are in the angular thrust reversal position.

9. The jet propulsion unit according to claim 2 , wherein the at least one internal deflector is formed from mobile surfaces including a first mobile surface being set in an area of the pylon and a second mobile surface set in the an area of the doors toward the exterior of the jet propulsion unit, with the a hinge axis of the first mobile surface oriented substantially at an angle of between 40 and 50° with a longitudinal axis X of the turbofan engine, and the hinge axis of the second mobile surface oriented substantially at an angle of between 60 and 80° with the longitudinal axis X of the turbofan engine.

Assignees

• Marche Jacques Herve
• Airbus Operations Sas

Inventors

• Marche Jacques Herve

Classifications

• F05D2260/90

  Braking · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02K1/62

  by blocking the rearward discharge by means of flaps · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title