ROTOR FOR MULTI-STAGE COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2006 - IPC F04D29/28 

Abstract RU 2268399 C2

FIELD: mechanical engineering.

SUBSTANCE: rotor (10) of multi-stage compressor comprises axial section (12) of the rotor followed by the centrifugal section (14) of the rotor. Axial section (12) of the rotor and centrifugal section (14) of the rotor are interconnected by means of a diffusion junction to define a unit working wheel having blades (22) and (36). The sections of the axial stage and centrifugal stage go one into the other without discontinuities.

EFFECT: improved design.

21 cl, 1 dwg

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RU 2 268 399 C2

Authors

Bakon Izabel'

Belleros Mishel'

Trumper Ronal'D F.

Dates

2006-01-20Published

2001-09-21Filed