Rotor of a turbomachine compressor, with an optimised inner end wall

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United States of America Patent

PATENT NO 9200638
SERIAL NO

13498696

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Abstract

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A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.

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Patent Owner(s)

Patent OwnerAddress
SAFRAN AIRCRAFT ENGINES2 BOULEVARD DU GÉNÉRAL MARTIAL VALIN 75015 PARIS

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Boston, Eric Jacques Cesson, FR 9 75
Chartoire, Alexandre Franck Arnaud Paris, FR 3 39
Iliopoulou, Vasiliki Ixelles, BE 3 25
Lepot, Ingrid Fraiture-en-Condroz, BE 1 16
Obrecht, Thierry Jean-Jacques Melun, BE 6 106

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