DAWN EQUIPPED WITH A VISUAL WEAR INDICATOR

FR3161707A1Pending Publication Date: 2025-10-31SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
FR2024004493
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-04-30
Publication Date
2025-10-31

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Abstract

The invention relates to a turbomachine blade comprising: - a blade (16) extending from a proximal end and a distal end (15.2) of the blade, - a foot located at the proximal end of the blade and intended to be fixed to a turbine disk, and - a heel (19) located at the distal end (15.2) of the blade, said heel (19) comprising a first lateral edge (25) and a second lateral edge (26), each lateral edge (25, 26) comprising an inter-blade contact face (31) with a heel (19) of an adjacent blade, at least one inter-blade contact face (31) being covered at least partially by a wear-resistant coating (34), - at least one inter-blade contact face (31) comprising a visual wear indicator (37). Figure 5a
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Claims

Demands

1. Turbomachine blade (15) comprising: - a blade (16) extending from a proximal end (15.1) to a distal end (15.2) of the blade (15), - a foot (18) located at the proximal end (15.1) of the blade and intended to be fixed to a turbine disk, - a heel (19) located at the distal end (15.2) of the blade (15), said heel (19) comprising a first lateral edge (25) and a second lateral edge (26), each lateral edge (25, 26) comprising an inter-blade contact face (31) with a heel (19) of an adjacent blade, at least one inter-blade contact face (31) being at least partially covered by a wear-resistant coating (34), characterized in that at least one inter-blade contact face (31) comprises a visual wear indicator (37).

2. Blade according to claim 1, characterized in that the visual wear indicator (37) has a simple shape selected from: a longitudinally traversing groove (38), a non-longitudinally traversing groove (38), a blind cylindrical hole (39).

3. Blade according to claim 1, characterized in that the visual wear indicator (37) has a complex shape selected from: a longitudinally traversing groove (38) having a bottom provided with a step (40) between two bottom faces of groove (41, 42), a non-longitudinally traversing groove (38) having a bottom provided with a step (40) between two bottom faces of groove (41, 42), or a set of two blind holes (39.1, 39.2) arranged in the extension of each other.

4. Blade according to claim 1, characterized in that the visual wear indicator (37) comprises at least one groove (38) having a longitudinal extension direction (Dl) along a straight line passing through two points of an inter-blade contact face (31), said longitudinal extension direction (Dl) extending horizontally or vertically or obliquely.

5. Blade according to claim 4, characterized in that a section of the groove (38) can have a shape selected from a polygonal shape, such as a triangular or rectangular shape, or a circular shape, or a slotted shape.

6. Blade according to any one of claims 1 to 5, characterized in that the inter-blade contact faces (31) of the first lateral edge (25) and of the second lateral edge (25) have visual wear indicators (37) having different orientations and / or shapes.

7. Blade according to any one of claims 1 to 6, characterized in that each of the lateral edges (25, 26) has a substantially "Z" shaped profile.

8. Blade according to any one of claims 1 to 7, characterized in that the heel (19) has at least one sealing lip (29, 30).

9. Method for inspecting the wear level of a blade (15) as defined according to any one of the claims, characterized in that said method comprises a step of measuring a dimension, in particular a depth, of the visual wear indicator (37) representative of a wear of the blade (15).

10. Method according to claim 9, characterized in that in the case where the visual wear indicator (37) is no longer visible, said method comprises a step of depositing an anti-wear coating on the inter-blade contact face (31).

Citation Information

Patent Citations

  • Shroud connection of a turbine blade

    EP1970535A1

  • Aube mobile de turbomachine

    FR2985759A1

  • ROTOR BLADE FOR A TURBOMACHINE

    FR3071537A1

  • METHOD FOR MANUFACTURING A METAL BLADE COMPONENT FOR AN AIRCRAFT TURBOMACHINE

    FR3079847A1

  • NON-INVASIVE METHOD FOR WEARING A TURBOMACHINE BLADE

    FR3149375A1