Rear assembly of a turbojet engine nacelle including a fireproof sealing device
US10753315B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 14, 2019 |
| Grant date | Aug 25, 2020 |
| Priority date | — |
| Expiry date | Feb 23, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/55
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.