Turbojet engine rear portion having an augmented A9/A8 nozzle area ratio

Patent metadata

Field	Value
Publication number	US-12429012-B2
Application number	US-202218546543-A
Country	US
Kind code	B2
Filing date	Feb 14, 2022
Priority date	Feb 18, 2021
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

A rear portion of a convergent-divergent nozzle turbojet engine includes a device for controlling the position of a divergent flap relative to that of a convergent flap, including a first connecting rod having a first end portion hinged to the convergent flap and an opposite second end portion, a second connecting rod having a first end portion hinged to the divergent flap and an opposite second end portion, and a third connecting rod having a first end portion hinged to a synchronization ring and an opposite second end portion. The second end portion of the first connecting rod is hinged to the second end portion of the second connecting rod and/or to the second end portion of the third connecting rod, and the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod.

First claim

The invention claimed is:

1. A turbojet engine rear portion, comprising:
an upstream stator structure;
a convergent-divergent nozzle with a variable geometry comprising
a set of convergent flaps distributed around a longitudinal axis of the rear portion of the turbojet engine, each of the convergent flaps comprising a panel intended to channel an exhaust gas flow within the nozzle, and a lever secured to the panel, each of the convergent flaps having an upstream end hinged on the upstream stator structure so that the convergent flaps are movable in rotation around first hinge axes attached to the upstream stator structure, and
a set of divergent flaps distributed around the longitudinal axis, each of the divergent flaps comprising a panel intended to channel the exhaust gas flow within the nozzle, and each of the divergent flaps having an upstream end hinged on a downstream end of a corresponding convergent flap so that the divergent flaps are movable in rotation around second hinge axes attached to the convergent flaps;

a synchronisation ring arranged around the set of convergent flaps or the upstream stator structure and configured to act on at least some of the convergent flaps, called controlled convergent flaps, to control a geometric variation of the nozzle;
cylinders configured to move the synchronisation ring in translation according to the longitudinal axis, relative to the upstream stator structure, each cylinder including a body fastened to the upstream stator structure and a rod that is movable and connected to the synchronisation ring; and
connecting rods configured to control positions of the divergent flaps based on positions of the convergent flaps, the connecting rods comprising a first connecting rod having a first end portion hinged to the corresponding convergent flap according to a third hinge axis distinct from the first and second hinge axes and an opposite second end portion, a second connecting rod having a first end portion hinged to the corresponding divergent flap according to a fourth hinge axis and an opposite second end portion, and a third connecting rod having a first end portion hinged to the synchronisation ring and an opposite second end portion,
wherein the second end portion of the first connecting rod is hinged to at least one of the second end portion of the second connecting rod and the second end portion of the third connecting rod,
wherein the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod, and
wherein the second end portion of the first connecting rod is hinged together to the second end portion of the second connecting rod and to the second end portion of the third connecting rod, according to a common hinge axis.

2. The turbojet engine rear portion according to claim 1 , wherein an A9/A8 ratio, equal to the quotient of a section A9 of the nozzle at a downstream end of the divergent flaps by a section A8 of the nozzle at a neck formed at a junction between the convergent flaps and the divergent flaps, varies by 0.35.

3. A turbojet engine for an aircraft, comprising a rear portion according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Kohn Thierry
• Krajka Dimitri Thomas

Classifications

• F05D2260/57

  using servos, independent actuators, etc. · CPC title

• F05D2250/90

  Variable geometry · CPC title

• F05D2220/80

  in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion · CPC title

• F05D2250/41

  with one degree of freedom · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title