Rotor section for a rotor of a turbomachine, and rotor blade...

F - Mech Eng,Light,Heat,Weapons – 01 – D

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Details

F01D 5/08 (2006.01) F01D 5/30 (2006.01) F16B 21/02 (2006.01) F16B 21/04 (2006.01) F16B 33/00 (2006.01) F16B 39/02 (2006.01) F16B 39/10 (2006.01)

Patent

CA 2752666

The invention relates to a rotor section (10) for a rotor of a gas turbine, to a rotor blade (18), and to a blocking element (46, 62). The rotor section (10) comprises a rotor disk (12) having rotor blades (18) that are inserted thereon in holding grooves (16) and that are secured against sliding along the holding grooves (16) by means of a sealing element (30) arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements (30), it is proposed that each sealing element (30) be secured by one blocking element (46, 62), which engages in a hole (58) arranged at the end face in the rotor blade root (20).

L'invention concerne un segment de rotor (10) pour le rotor d'une turbine à gaz, une aube mobile (18) et un élément de blocage (46, 62). Le segment de rotor (10) comprend un disque de rotor (12) avec des aubes mobiles (18) montées dans des rainures de maintien (16), qui sont immobilisées pour éviter un décalage dans les rainures de maintien (16) par un élément d'étanchéité (30) implanté sur la face. Afin d'obtenir une construction fiable, simple et facile à concevoir pour la fixation circonférentielle des éléments d'étanchéité (30), l'invention propose que chaque élément d'étanchéité (30) soit immobilisé par un élément de blocage (46, 62) qui s'engage dans un trou (58) ménagé dans la face avant du pied d'aube mobile (20).

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