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Integrated thrust reverser device and aircraft engine nacelle equipped therewith

An aircraft engine and reverse thrust technology, which is applied in the direction of machines/engines, jet propulsion devices, etc., can solve problems such as structural deformation and uneven stress

Active Publication Date: 2016-04-20
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Such a solution would have disadvantages related to uneven stresses in the mechanism of the air flaps and a great risk of structural deformation while the movable fairing is moving downstream of the pod while the air flaps are still in the stowed position, the latter in the secondary Sudden appearance at air contact

Method used

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  • Integrated thrust reverser device and aircraft engine nacelle equipped therewith
  • Integrated thrust reverser device and aircraft engine nacelle equipped therewith
  • Integrated thrust reverser device and aircraft engine nacelle equipped therewith

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Embodiment Construction

[0043] figure 1 A detailed sequence of operations of the thrust reverser according to the invention is shown. The thrust reverser includes a plurality of cascade sets, a plurality of second secondary airflow blocking flap sets, a movable fairing, and various moving cylinders described later in the specification.

[0044] On its inner surface relative to the central axis of the nacelle, sets of cascades are fixed to a front frame generally located in the nacelle, and the blocking flaps are associated with the sets of cascades. In a first state called "state 1" of the sequence of operations, a plurality of cascade sets and blocking flaps are inserted inside the thrust reverser movable cowl. The inactive configuration of the thrust reverser produces a direct injection from the inlet portion of the pod to a downstream or outlet portion above the internal fixed structure of the pod in an aircraft engine. The movable fairing is pushed downstream of the pod by actuation of actuatin...

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PUM

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Abstract

A thrust reverser device is integrated in an aircraft engine nacelle. Blocking flaps (18) are stored inside a mobile cowl (10, 21) disposed in a downstream section of the nacelle, under deflection cascade assemblies (15) during direct-jet operation of the nacelle. Means are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: -the mobile cowl (10, 21) moves in translation towards the downstream end of the nacelle; -each flap (18) is then deployed in the main airflow path (46).

Description

technical field [0001] The invention relates to a thrust reverser for an aircraft engine pod. The invention also relates to an aircraft engine pod equipped with such a device. Background technique [0002] Specifically, the thrust reversers involved are of the "tandem" type, that is to say, the thrust reversers include fairings, such as "O-pipe" types, alternately between deployed and stowed positions movement, in the deployed position it opens a passage within the pod and exposes the secondary cascade vanes, and in the stowed position it closes the passage. Reorientation of the secondary air flow through the annular flow channel is ensured by cascades and complementary choke doors (also called flaps). [0003] The prior art is known from patent application EP1843031, where the cascades are in normal operation and are stored in the space defined within the movable cowl. During the movement of the movable cowl, the blocking flaps are then driven in the flow path of the air...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/72F02K1/09F02K3/06F02K1/76
CPCF02K1/72F02K1/09F02K1/62F02K1/625F02K1/70F02K1/76F02K1/763F02K1/766F02K3/06
Inventor 菲利普·盖兰奥利维尔·凯尔布莱尓让-保罗·拉米
Owner AIRCELLE
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