TURBOJET COMPRESSOR Russian patent published in 2013 - IPC F01D5/02 F01D5/14 F01D5/30 F04D29/32 F02K3/04 

Abstract RU 2476678 C2

FIELD: engines and pumps.

SUBSTANCE: hub has outer chamfer 38 and inner chamfer 40 in the area of blade root extending from blade rear edge 30 to front edge 28. Said inner and outer chamfers converge at blade face edge entry to make extending bulge 42 shaped to spiral around hub axis to ensure forced gas flow into every passage for enveloping blade root from its outer side. Outer chamfer profile is inclined to spiral outer surface to deflect gas flow flowing in appropriate passage from blade outer side to inner surface of adjacent blade.

EFFECT: higher efficiency.

9 cl, 4 dwg

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RU 2 476 678 C2

Authors

Obehn Stefan

Bel'Mont Oliv'E

Dates

2013-02-27Published

2009-01-29Filed