STATOR BLADE FOR AN AIRCRAFT TURBOMACHINE

FR3159819A1Pending Publication Date: 2025-09-05SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Application Number
FR2024002045
Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-02-29
Publication Date
2025-09-05
Patent Text Reader

Abstract

Stator vane (40) for an aircraft turbomachine (10), comprising a blade (42) which extends between a platform (44) and fixing lugs (46), the blade (42) comprising a lower surface (42a) and an upper surface (42b) which are connected together at a leading edge (50) and a trailing edge (52) of the blade (42), the leading edge (50) being connected to the platform (44) and being at a distance from the fixing lugs (46), characterized in that the blade (42) comprises a body (60) which is in one piece with the platform (44) and the fixing lugs (46), and a removable bar (70) which is attached and fixed to the body (60), one of the elements among the body (60) and the bar (70) comprising the leading edge (50), and the other of these elements comprising the trailing edge (52). Figure for abstract: Figure 3
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Citation Information

Patent Citations

  • DAWN FOR AN AIRCRAFT TURBOMACHINE

    FR3101107A1

  • Metal / ceramic composite blade

    DE3821005A1

  • Airfoil for turbine system

    EP2578807A2

  • Exit steering vane for turbomachine, made from several assembled parts

    FR3110630A1

  • STATOR BLADE FOR A TURBOMACHINE WITH A METAL SHIELD

    FR3121475A1