TOOLS FOR FIXING TWO HOLLOW TREES TOGETHER

FR3168625A1Pending Publication Date: 2026-05-22SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
SAFRAN AIRCRAFT ENGINES SAS
Filing Date
2024-11-19
Publication Date
2026-05-22

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Abstract

The present invention relates to a tool (4) for fixing two hollow shafts (10, 20) together, the tool being configured to be engaged in the two shafts which respectively comprise first and second annular flanges (100, 200) adapted to be fixed together by screws (70), the tool comprising: - a guide (6) adapted to be engaged in the two shafts (10, 20), - a sleeve (5) mounted on the guide and comprising a body (50) having an end (51) adapted to be applied axially against one of the shafts, - at least one arm (53) which comprises a series of holes (532), and - several rods (7) each comprising a portion (72) which can include one of the screws, the rods being adapted to slide axially in the holes (532) to a position in which the portions (72) are at an axial distance from the end (51). Figure for the summary: Figure 10
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Claims

8. A method according to claim 7 in combination with claim 4, characterized in that step (f) comprises a substep of sliding the centering pads (530) so as to axially align the screws (70) in the holes (101, 201) of the first and second flanges (100, 200).

9. Assembly (40) comprising tooling (4) according to any one of claims 1 to 6, and a module for an aircraft turbomachine (1), this module comprising a first hollow shaft (20) having a first annular flange (200), and a second hollow shaft (10) having a second annular flange (100), the first and second annular flanges (100, 200) being connected axially to each other and extending radially outwards from the corresponding shaft (10, 20).

10. Assembly according to claim 9, characterized in that the module further comprises a speed reducer (2) which includes a solar (21) rotationally fixed to the first shaft (20), an annular ring (22) extending around the solar (21), and a plurality of satellites (23) meshed with the solar (21) and the ring (22) and carried by a satellite carrier (24), the satellite carrier (24) comprising axial through slots (25), and in which the satellite carrier (24) is located between the body (50) of the sleeve (5) and the first and second flanges (100, 200), the rods (7) being able to slide through the slots (25) so as to fix the first and second annular flanges (100, 200) together by the screws (70). [Fig. 2] 10 in [Fig. 7] -40 > [Fig. 8] [Fig. 12] (a)