Bladed assembly equipped with a blade disengagement detection ring

FR3158759B1Active Publication Date: 2026-01-09SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
FR2024000719
Authority / Receiving Office
FR · FR
Patent Type
Patents
Current Assignee / Owner
Filing Date
2024-01-25
Publication Date
2026-01-09
Estimated Expiration
2044-01-25

AI Technical Summary

Technical Problem

The issue of blade disengagement due to axial offset and oscillation in turbomachines, leading to increased friction and potential rubbing against abradable elements, is not effectively addressed by existing technologies, posing a risk of mechanical failure and requiring frequent maintenance.

Method used

A conductive ring is integrated across the heels of adjacent blades, designed to break under shear stress when axial offset occurs, with detection means to identify the break, thereby preventing further offset and alerting the system to potential disengagement.

Benefits of technology

The solution provides mechanical resistance to axial offset, reduces the risk of blade dislocation, and enables automatic detection of disengagement, enhancing engine robustness and minimizing maintenance needs.

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Abstract

The invention relates to a bladed turbomachine assembly extending around an axis of rotation and comprising blades (11a, 11b), each blade (11a, 11b) extending in a radial direction with respect to the axis of rotation up to a heel (14a, 14b), characterized in that it comprises: – an electrically conductive rod (26) which passes through the heels (14a, 14b) of the blades (11a, 11b), this rod (26) being subjected to shear stress if a heel (14a, 14b) shifts along the direction of the axis of rotation relative to another circumferentially adjacent heel (14a, 14b); – detection means connected to the ends of the rod (26) to identify that this rod (26) is broken when it is no longer electrically conductive. Figure for the summary: Figure 8
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