B - Operations – Transporting – 64 – D
Patent
B - Operations, Transporting
64
D
B64D 29/00 (2006.01) B64D 33/02 (2006.01)
Patent
CA 2247176
The bay (12) of a turbofan engine (10) comprises a front structural element (30), whose external surface is continuous and extends over at least 50% of the geometrical chord of the bay. Said element (30) is installed on maintaining and guiding members (44), such as slides, which prevent a significant deformation in flight and allow a sliding to the front of the element (30) for maintenance purposes. A laminar air flow around the front half of the bay (12) is consequently ensured.
La nacelle (12) d'un turboréacteur (10) à double flux comprend un élément structural avant (30) dont la surface extérieure est continue et s'étend sur au moins 50 % de la corde géométrique de la nacelle. En outre, cet élément (30) est monté sur des organes (44) de maintien et de guidage, tels que des glissières, qui empêchent une déformation importante en vol et autorisent un coulissement vers l'avant de l'élément (30) pour la maintenance. On assure ainsi un écoulement laminaire de l'air autour de la moitié avant de la nacelle (12).
Aerospatiale Societe Nationale Industrielle
Goudreau Gage Dubuc
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