Invention Application
- Patent Title: TURBOJET ENGINE NACELLE INCLUDING A SINGLE MOVABLE FRAME OF A CASCADE THRUST REVERSER AND PASSAGES OF ANCILLARIES
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Application No.: US16884948Application Date: 2020-05-27
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Publication No.: US20210003096A1Publication Date: 2021-01-07
- Inventor: Sébastien Michel Thierry GUILLEMANT , Pierre CARUEL , Olivier KERBLER , Olivier HEAU , Mathieu LEROUVREUR , Antoine Elie HELLEGOUARCH
- Applicant: Safran Nacelles , Safran Aircraft Engines
- Applicant Address: FR GONFREVILLE L'ORCHER; FR Paris
- Assignee: Safran Nacelles,Safran Aircraft Engines
- Current Assignee: Safran Nacelles,Safran Aircraft Engines
- Current Assignee Address: FR GONFREVILLE L'ORCHER; FR Paris
- Priority: FR17/61239 20171127
- Main IPC: F02K1/72
- IPC: F02K1/72 ; F01D9/06

Abstract:
A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.
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