Mechanical reduction gear for an aircraft turbine engine
A lubrication circuit with radially oriented oil inlet and axially oriented oil outlet ports, connected by a one-piece device, addresses the challenge of maintaining reducer size and assembly complexity in turbomachines, enhancing maintenance efficiency.
WO2026132734A1PCT designated stage Publication Date: 2026-06-25SAFRAN AIRCRAFT ENGINES SAS +1
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2025-12-16
- Publication Date
- 2026-06-25
Smart Images
Figure FR2025051186_25062026_PF_FP_ABST
Abstract
The invention relates to a mechanical reduction gear (10) for a turbine engine (1), in particular for an aircraft, comprising a sun gear (11), a ring gear (14), planet gears (12) meshing with the sun gear (11) and the ring gear (14), and a lubrication circuit (C2) for lubricating the reduction gear (10), the lubrication circuit comprising an oil pipe (28) having an oil inlet port (18) connected to an oil supply circuit (1) which comprises an oil outlet port (22), the connection device (126) comprising a body (132) formed as a single piece.
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