ROTOR OF AVIATION TURBOJET ENGINE COMPRESSOR, COMPRESSOR AND TURBOJET ENGINE Russian patent published in 2011 - IPC F04D29/34

Abstract RU 2423624 C2

FIELD: engines and pumps.

SUBSTANCE: disk (11) of a rotor comprises a flange (26) of axial retention opposite to seats (16), where blade roots are installed, at the same time the disk and the flange are arranged so that an outer circular cam system (34, 48) and an inner circular cam system (44, 50) are formed.

EFFECT: reduced rotor weight, in particular, weight of front braking system.

11 cl, 6 dwg

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RU 2 423 624 C2

Authors

Bjuisson Ehrve

Goga Zhan-Ljuk

Lefevr Ehrik

Dates

2011-07-10—Published

2007-04-26—Filed