The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Mar. 25, 2025

Filed:

May. 20, 2022
Applicant:

Safran Aircraft Engines, Paris, FR;

Inventors:

Bruno Albert Beutin, Moissy-Cramayel, FR;

Alexis Pereira, Moissy-Cramayel, FR;

Zoltan Zsiga, Moissy-Cramayel, FR;

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64D 27/40 (2024.01); F02C 7/20 (2006.01); F02C 7/32 (2006.01); F02C 7/36 (2006.01);
U.S. Cl.
CPC ...
B64D 27/406 (2024.01); B64D 27/402 (2024.01); F02C 7/20 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01); F05D 2220/76 (2013.01); F05D 2260/4031 (2013.01);
Abstract

A support assembly for supporting a main accessory gearbox of an aircraft turbine engine, the accessory gearbox including gears and supporting at least one item of equipment driven by the gears. The support assembly can include a structure for connecting and supporting the turbine engine to a pylon of the aircraft including: an intermediate axial portion for attachment to the pylon, having an upper end that defines a linking interface with the pylon, the intermediate axial portion bearing suspension rods, which are intended to be connected to the turbine engine; a front axial portion extending forward of the intermediate portion and having at least one suspension member configured to be connected to the turbine engine; and a rear axial portion extending rearwards of the intermediate portion and supporting the main accessory gearbox.


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