MODULE FOR AN AIRCRAFT TURBOMACHINE
The annular sealing skirt with axially oriented clamping elements addresses the risk of oil leakage by maintaining a seal between bearing supports, ensuring clean air intake in aircraft turbomachines.
FR3164742B1Active Publication Date: 2026-06-26SAFRAN AIRCRAFT ENGINES SAS
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-07-16
- Publication Date
- 2026-06-26
Abstract
Module (30) for an aircraft turbomachine (10), this module (30) comprising: - a lubrication chamber (38) which is at least partially delimited by bearing supports (32, 34), - an oil supply circuit (40) for the chamber (38), and - an annular sealing skirt (80) which includes a first axial end (80a) hermetically fixed to the first bearing support (32) and a second axial end (80b) hermetically fixed to the second bearing support (34), this skirt (80) being made of a deformable material and being capable of providing a seal around flanges (32a, 34a) of the bearing supports (32, 34), particularly in the event of failure of shear screws (42) securing these bearing supports (32, 34). Figure for the abbreviation: Figure 5
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