Multi-stage impeller

Details Multi-stage impeller Multi-stage impeller

F - Mech Eng,Light,Heat,Weapons

04

D

F04D 29/28 (2006.01) F01D 5/04 (2006.01)

Patent

CA 2420767

A multi-stage compressor rotor (10) for a gas turbine engine comprises an axial-flow rotor (12) followed by a centrifugal rotor (14). The axial-flow rotor (12) and the centrifugal rotor (14) are diffusion bonded together to form a unitary dual flow impeller having blades (22, 96) with continuos axial- flow and centrifugal stage sections. By eliminating the gap between the axial flow and centrifugal stages, unsynchronized air deflection between the successive arrays of blades is prevented, thereby improving the aerodynamic performance of the compressor rotor (10).

L'invention concerne un rotor de compresseur multiétagé (10) destiné à une turbine à gaz, comprenant un rotor à écoulement axial (12) suivi d'un rotor centrifuge (14). Le rotor à écoulement axial (12) et le rotor centrifuge (14) sont soudés ensemble par diffusion pour former un rouet unitaire à écoulement double comprenant des aubes (22, 96) à sections d'écoulement axial continu et centrifuge. L'élimination de l'espace entre les sections d'écoulement axial et centrifuge permet d'empêcher la déflexion d'air non synchronisée entre les séries d'aubes successives, améliorant ainsi les performances aérodynamiques du rotor de compresseur (10).

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