Variable pitch blade of a static blade of a turbomachine

FR3152286A1Active Publication Date: 2025-02-28SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
FR2023008911
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2023-08-24
Publication Date
2025-02-28
Estimated Expiration
2043-08-24

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Abstract

The invention relates to a variable pitch blade (13) comprising a blade foot (21), a bracket (23) carrying the blade foot (21), and a hub (25), the blade foot (21), the bracket (23) and the hub (25) being configured to be mounted pivotally about a pitch axis Y of the blade (13), the bracket (23) being coupled to the hub (25) via a torque transmission system (29) configured to transmit a frictional torque between the hub (25) and the bracket (23), and to allow relative pivoting of the bracket (23) and the hub (25) about the pitch axis Y when the transmitted torque exceeds a predetermined value. The invention also relates to a static blade (11) comprising at least one such blade (13), a turbomachine (1) comprising at least one such static blade (11), and an aircraft (100) comprising at least one such turbomachine (1). Figure for the abstract: Fig. 3
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Claims

each second hub disc (59) and the hub (25) forming a sliding connection between them along the setting axis (Y), at least one first attachment disc (57) and at least one second hub disc (59) being in rubbing contact with each other to transmit a torque by friction between the hub (25) and the attachment (23).

6. Blade (13) according to any one of claims 1 to 5, in which the attachment (23) comprises a first angular stop (39) and the hub (25) comprises a second angular stop (41), the first angular stop (39) and the second angular stop (41) being angularly offset by a predetermined value around the setting axis (Y), in the absence of angular offset between the attachment (23) and the hub (25) resulting from a relative pivoting of the attachment (23) and the hub (25) around the setting axis (Y).

7. A blade (13) according to any one of claims 1 to 6, which comprises a visual indicator (47), which indicates the presence of an angular offset between the attachment (23) and the hub (25) resulting from a relative pivoting of the attachment (23) and the hub (25) about the setting axis (Y).

8. Static vane (11) of a turbomachine (1) comprising at least one blade (13) according to any one of claims 1 to 7, in which the blade root (21), the attachment (23) and the hub (25) are pivotally mounted around a setting axis (Y) of the blade (13).

9. Turbomachine (1) comprising at least one static blading (11) according to claim 8.

10. Aircraft (100) comprising at least one turbomachine (1) according to claim 9. [Fig. 1] [Fig. 2] [Fig. 3] [Fig. 4] 3 / 4

Citation Information

Patent Citations

  • Aircraft engine comprising blades fixed to the casing

    FR3132126A1

  • Propeller for an aircraft turbo engine, including safety means for controlling blade angle of attack

    US20170313404A1

  • System for controlling the pitch setting of a propeller vane for an aircraft turbine engine

    US20230257105A1

  • Impact absorbing blade mounts for variable pitch blades

    US4047840A

  • Method of guiding a blade having a variable pitch angle

    US7112040B2