Bypass propulsion unit, comprising a thrust reverser with movable cascades

Patent metadata

Field	Value
Publication number	US-11619191-B2
Application number	US-202017025019-A
Country	US
Kind code	B2
Filing date	Sep 18, 2020
Priority date	Mar 19, 2018
Publication date	Apr 4, 2023
Grant date	Apr 4, 2023

Abstract

A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.

First claim

What is claimed is:

1. A bypass propulsion unit, comprising:
an engine; and
a nacelle disposed around the engine and defining a cold flow path, the nacelle including:
a nacelle cradle linked to a suspension pylon of the propulsion unit;
a thrust reverser comprising cascades and at least one cowl, wherein the at least one cowl is slidably mounted relative to thrust reverser flaps, connecting rods, and the nacelle cradle, wherein the connecting rods actuate the thrust reverser flaps;
an inner structure wrapped around the engine, the inner structure defines, with the at least one cowl, a portion of the cold flow path; and
a bifurcation for the passage of piping extending between the engine and the outside of the nacelle, diametrically opposite to the nacelle cradle, wherein:

the thrust reverser of the propulsion unit further comprises two structural half-shrouds disposed downstream of the cascades and secured thereto,
the inner structure comprises two upstream inner half-structures, ends of the two upstream inner half-structures being linked to the half-shrouds to form two half-sections of the cold flow path, wherein the two half-sections are pivotally mounted on the nacelle cradle,
the thrust reverser flaps are hingedly mounted on the half-shrouds,
the connecting rods are hingedly mounted on the thrust reverser flaps and on the upstream inner half-structures, and
the half-sections of the cold flow path are movable between a service position in which the half-sections of the cold flow path bear on and on either side of the bifurcation, and a maintenance position, in which the half-sections of the cold flow path are pivoted outwards of the nacelle, enabling access to the portion of the engine located below the upstream inner half-structures;
wherein the at least one cowl further comprises two half-cowls, in that the portion of the inner structure located downstream of the upstream inner half-structures comprises two downstream inner half-structures, and the half-cowls and the downstream inner half-structures are pivotally mounted respectively on the nacelle cradle between a service position in which the half-cowls and the downstream inner half-structures are respectively joined edge-to-edge downstream of the bifurcation and define a downstream section of the cold flow path, and a maintenance position in which the half-cowls and the downstream inner half-structures are pivoted outwards of the nacelle, enabling access to the portion of the engine located below the downstream inner half-structures.

2. The propulsion unit according to claim 1 , wherein the bifurcation extends axially over a length corresponding substantially to that of the half-sections of the cold flow path.

3. The propulsion unit according to claim 1 , wherein the half-sections of the cold flow path have a D-shaped cross-section in a plane transverse to an axial direction of the nacelle.

4. The propulsion unit according to claim 1 , wherein the half-cowls and the downstream inner half-structures have a C-shaped cross-section in a plane transverse to an axial direction of the nacelle.

5. The propulsion unit according to claim 1 , further comprising one or more locks configured to hold the half-sections of the cold flow path in the service position cooperating with the bifurcation.

Assignees

• Safran Nacelles
• Safran Aircraft Engines

Inventors

• Garnaud Quentin
• Glemarec Guillaume
• Boileau Patrick
• Toupet Ludovic

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02K1/80

  Couplings or connections · CPC title

• F05D2220/323

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