AXIAL DISPLACEMENT COMPRESSOR AND GAS TURBINE ENGINE Russian patent published in 2012 - IPC F04C18/107 F02C5/06 

FIELD: engines and pumps.

SUBSTANCE: proposed compressor 8 has inlet 20 spaced axially apart from outlet 22 and arranged upstream thereof. Compressor 8 has continuous axial flow from inlet 20 via outlet 22. Inner and outer cases 12 and 14 have inner and outer axes 16, 18 displaced relative to each other to extend from inlet 20 to outlet 22 via first and second sections 24, 26 of compressor assembly 15 in downstream direction. At least one of said cases may revolve around its axis. Inner and outer cases incorporate alternating inner and outer screw vanes 17, 27 revolving around inner and outer axes 16, 18, respectively. Said inner and outer screw vanes 17, 27 extend along radius outward and inward, respectively. Screw vanes have first and second angles of twist at first and second sections 24, 26, respectively. First twist angles exceed second twist angles. Engine comprises said compressor 8, combustion chamber, high-pressure turbine jointed to drive said compressor by high-pressure shaft.

EFFECT: light, compact and efficient axial-flow compressor.

19 cl, 11 dwg