Thrust reverser comprising a deployable flow-deflection membrane and having a design that reduces its axial space requirement
The deployable deflection membrane in the thrust reverser reduces the axial length and mass of the reversing unit, addressing the issues of increased drag and fuel consumption in existing systems, enhancing aircraft performance and environmental sustainability.
WO2026115225A1PCT designated stage Publication Date: 2026-06-04SAFRAN NACELLES
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN NACELLES
- Filing Date
- 2025-11-25
- Publication Date
- 2026-06-04
AI Technical Summary
Technical Problem
Existing thrust reversers in aircraft propulsion systems face challenges with increased mass and drag due to the use of deflection grids, necessitating longer components to achieve required back-thrust performance, which in turn increases specific fuel consumption.
Method used
A thrust reverser design incorporating a deployable deflection membrane that moves from a folded to a deployed configuration via rearward displacement, reducing the axial footprint and overall size of the reversing unit, thereby decreasing mass and drag.
Benefits of technology
The solution effectively reduces the axial length of the reversing unit, leading to decreased mass and drag, and improves aircraft performance by lowering specific fuel consumption and environmental impact.
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Smart Images
Figure FR2025051101_04062026_PF_FP_ABST
Abstract
The invention relates to a thrust reverser (30) for an aircraft propulsion assembly, the reverser comprising a fixed structure (31) and a movable structure (29), and at least one deployable deflection membrane (32) designed to deflect at least part (20B') of a secondary flow when this membrane is in a deployed configuration, the membrane comprising an opening contour (112) which has an opening contour rear portion (112b). According to the invention, the reverser is configured such that the membrane (32) changes from a collapsed configuration to the deployed configuration via a rearward movement of its opening contour rear portion (112b), driven by the movable structure (29) when the latter moves in translation from its direct-thrust forward position to its thrust-reversal retracted position.
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