VARIABLE TIMING TURBINE ENGINE VANES

FR3168621A1Pending Publication Date: 2026-05-22SAFRAN SA
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Patent Information

Application Number
FR2024012641
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-11-19
Publication Date
2026-05-22

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Abstract

Variable pitch turbine blade (116) for a turbomachine, particularly for aircraft, comprising: - a composite structure (122) including a blade (120) connected to a base (118) which includes an attachment portion (130), - a metal splice (140) having an internal housing (144) through which the attachment portion (130) passes, - a metal sleeve (160) having an internal recess (164) through which the attachment portion (130) passes, and in which said splice (140) is at least partially engaged, - at least one shim (170) mounted between the sleeve (160) and the attachment portion (130) to prevent the structure (122) from moving in translation relative to the sleeve (160), and - at least one elastically deformable member (180) which forces the structure (122) in said direction so that its attachment portion (130) remains supported against said at least one wedge (170). Figure for the abbreviation: Figure 4
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Claims

11. Blade (116) according to any one of the preceding claims, wherein said at least one member (180) has an annular shape and / or is centered on the timing axis (Y).

12. Blade (116) according to any one of the preceding claims, wherein the second section (168) of the sleeve (160) comprises two lugs (169) extending radially into the interior of the sleeve (160) and diametrically opposed with respect to the alignment axis (Y), these two lugs (169) being engaged in two notches (148) of complementary shapes in the splice (140).

13. Blade (116) according to claim 12, wherein each of the notches (148) comprises a bottom (148a) axially supported on the corresponding lug (169), and two sides (148b) able to cooperate by direct circumferential support with this lug (169).

14. Blade (116) according to any one of the preceding claims, wherein the structure (122) comprises a multilayer protective coating (190) in bearing areas with the splice (140), or even with said at least one wedge (170).

15. Turbomachine (10), in particular aircraft turbomachine, comprising at least one blade (116) according to any one of the preceding claims. 120 [Fig. 3a-3b] 120 [Fig. 3c-3d] [Fig. 4] 122^ [y~Y 180 132 [Fig. 6] 160,170 [Fig. 11]

Citation Information

Patent Citations

  • Vane comprising a structure made of composite material, and associated manufacturing method

    WO2022208002A1

  • rotor blade with a separate force retention and load transfer system and rotor equipped with such blades

    FR3127472A1

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

    US20170313404A1

  • Aircraft turbine engine comprising variable-pitch propeller blades

    WO2022018353A1