Guide vane for rotary turbomachinery

Details Guide vane for rotary turbomachinery Guide vane for rotary turbomachinery

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/04 (2006.01) F01D 11/00 (2006.01)

Patent

CA 2602457

The invention relates to a guide vane for rotary turbomachinery, in particular for a gas turbine stage. Said guide vane comprises a blade (3), an outer platform (4), which is radially connected to the blade (3) and comprises an upper face (42) that faces radially away from the blade (3). Said upper face is provided with a connection structure (5) for fixing the blade (1) to a support structure (2), the latter comprising lateral wall sections (51, 52, 53, 54) that protrude radially from said upper face (42) and delimit an inner cavity (6). At least some parts of the lateral wall sections are provided with a joint contour (7), which can be inserted into a receiving section (2') in the support structure (2), the shape of the latter being adapted to said contour. In addition, at least one sealing element (12) is provided between the connection structure (5) and the support structure (2).

L'invention concerne une aube directrice destinée à une turbine à écoulement, notamment un étage turbine à gaz, et comprenant une ailettte (3), une plate-forme (4) qui est reliée radialement à l'extérieur à l'ailette (3) et qui possède une face supérieure (42) radialement opposée l'ailette (3) et présentant une structure de liaison (5) destinée à la fixation de l'aube directrice (1) à une structure porteuse (2). La structure porteuse présente des sections de paroi latérale (51, 52, 53, 54) dépassant radialement la face supérieure (42) de la plate-forme et délimitant une cavité (6) interne, ces sections présentant au moins sur certains segments un contour d'assemblage (7) qui s'emboîte dans un logement (2') de forme complémentaire réalisé dans la structure porteuse (2). Au moins un moyen d'étanchéité (12) est prévu entre la structure de liaison (5) et la structure porteuse (2).

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