Epicyclic speed reducer designed for fitment to the transmission between the gas turbine and air compressor of an aircraft engine

An epicyclic speed reducer designed for fitment to a transmission between a gas turbine and air compressor of an aircraft turbine engine, said reducer comprising a sun gear (5) connected to said turbine;

• a planet carrier (6) connected to said air compressor coaxially to said sun gear (5) and supporting a number of planetary gear (7) meshing with one of said sun gear (5);
• and a ring gear (8) fitted to a mounting (9) of said engine and with which said planetary gear (7) mesh;
• characterized by the fact that said planet carrier (6) comprising a first annular element (10) having a number of pairs of seats (11) for pins (13) on each of which rotates one of said planetary gears (7), and a number of holes (16) each interposed between two continuous planetary gears (7);
• a second annular element (17) connected to said compressor and having a number of cantilever axial arms (18), each designed to fit inside one of said holes (16) on said first element (10);
• connecting means (19) for connecting the end of each said cantilever axial arms (18) to a portion (20) of said first element (10), which portion (20) is substantially equidistant in relation to these seats (11) in each said pair of seats of said pins (13);
• said connecting means comprising a hinge (19) having a proper axis which is positioned radially in relation to a reducer axis, and is equidistant in relation to the seats (11) in each said pair of seats of said pins (13).