A turbine engine (10) comprising a fan section (18), a compressor section (22), a combustion section (28), and a turbine section (32) in serial flow arrangement. An an airfoil (132) assembly provided within one of the fan section (18), the compressor section (22), the combustion section (28), or the turbine section (32). The airfoil (132) assembly comprises: an airfoil (132) defining an interior (148); a spar (136, 236, 336, 436, 536, 636) having a portion located within the interior (148); and a trunnion (134, 234, 334, 434, 534, 634). The trunnion (134, 234, 334, 434, 534, 634) has an upper edge (144, 146) with an open top (156, 256, 356, 456, 556, 656), and a wall (138, 151, 251, 351, 451, 551, 651) having a set of interior surfaces (152, 252, 352, 452) defining a socket (154, 254, 354, 454, 554, 654) extending from the open top (156, 256, 356, 456, 556, 656), the spar (136, 236, 336, 436, 536, 636) extending through the open top (156, 256, 356, 456, 556, 656) and into the socket (154, 254, 354, 454, 554, 654), with a junction (158, 258, 358, 458, 558, 658) being formed between the spar (136, 236, 336, 436, 536, 636) and a portion of the upper edge (144, 146) defining the open top (156, 256, 356, 456, 556, 656). A stress relief (160, 260, 360, 460, 560, 660) is located at the junction (158, 258, 358, 458, 558, 658).
TURBINE ENGINE HAVING AN AIRFOIL ASSEMBLY WITH A TRUNNION AND A SPAR
TURBINENMOTOR MIT EINER SCHAUFELANORDNUNG MIT EINEM ZAPFEN UND EINEM HOLM
TURBOMACHINE AVEC UN ENSEMBLE DE PROFIL AÉRODYNAMIQUE AVEC UN TOURILLON ET UN LONGERON
2024-11-20
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Fan assembly for an engine having redundant trunnion retention
European Patent Office | 2025
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