Rotor for a compressor

Details Rotor for a compressor Rotor for a compressor

F - Mech Eng,Light,Heat,Weapons

04

D

F04D 29/32 (2006.01) F01D 5/30 (2006.01)

Patent

CA 2548642

A rotor (20) for a compressor, in particular in a gas turbine, has a number of rotor blades (25) which are arranged around the rotation axis of the rotor (20) in the form of a rim and are each held in a circumferential recess (21) on the rotor (20) by means of a blade root (26), with the blade root (26) having a widening lower part (27) which engages behind two shoulders (24) that are formed on the side walls of the recess (21). In such a rotor, the life is lengthened in that the recess depth (T) of the recess (21) is considerably greater than a minimum recess depth (T min) which results in the rotor (20) having sufficient strength in the area of the blade attachment for starting, based on the predetermined material characteristics of the rotor (20) and the operating conditions of the compressor.

L'invention concerne un rotor (20) pour un compresseur, en particulier une turbine à gaz, comprenant une pluralité d'aubes mobiles (25), agencées en couronne autour de l'axe de rotation du rotor (20) et maintenues chacune dans une gorge tournée périphérique (21) sur le rotor (20) au moyen d'une emplanture (26) d'aubes, une partie inférieure élargie (27) de ladite emplanture (26) s'engageant derrière deux épaulements (24) formés sur les parois latérales de la gorge tournée (21). L'objectif de cette invention est d'allonger la durée de vie d'un rotor de ce type. A cet effet, la profondeur (T) de la gorge tournée (21) est sensiblement supérieure à une profondeur minimale (T¿min?) de gorge, ce qui permet d'obtenir une résistance du rotor (20) suffisante pour le démarrage, au niveau de la fixation des aubes, selon les caractéristiques prédéfinies du matériau constituant le rotor (20) et dans les conditions de fonctionnement prescrites du compresseur.

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