A rear engine mounting structure 15, for connecting an engine system (fig.1,1) to an aircraft structure 2, has an elongate body 16 having a first end for connection to an aft side of a turbine exhaust case 6; and one or more mounting points 5 for connection to the aircraft structure. The mounting points are on the elongate body spaced apart from the first end in an axial direction, preferably on a surface of the elongate body. The first end may be connected to either an inner ring (fig.3,12) or an outer ring (fig.3,11) of the exhaust casing. The elongate body may have a polygonal cross-section (fig.8b), and include a lattice of beams (fig.10a). Alternatively, the mounting points are located on an annular body (fig.6c,17) with a number of radial struts (fig.6b,18) connecting it to the centrally located elongate body. The struts may be non-parallel and connect via an inner annular part (fig.6c,17b) of the elongate body, located between the elongate and annular bodies, the circumferential spacing of pairs of struts may be different. The struts may be hollow for conveying fluid. The annular portion may have a number of perforations.


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    Title :

    Rear engine mounting structure


    Contributors:

    Publication date :

    2025-04-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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