FIELD: compressor engineering. SUBSTANCE: working wheel has double-set vane cascade mounted on the hub. The vane cascade has main vanes and shortened vanes mounted in the passageways between the main vanes. The outlet edges of the main and shortened vanes are arranged over one front line. The inlet edges are shifted in the axial direction. The optimal ratios of sizes of the main and shortened vanes are presented in the invention description. EFFECT: improved design. 2 dwg
Title | Year | Author | Number |
---|---|---|---|
CENTRIFUGAL FAN | 1993 |
|
RU2061188C1 |
TURBO-MACHINE STAGE | 1998 |
|
RU2148732C1 |
COMPRESSOR FAN STAGE (VERSIONS) | 2005 |
|
RU2294461C1 |
METHOD OF REMOVING HEAVY PARTICLES FROM AIR FLOW IN AXIAL COMPRESSOR STAGE AND DEVICE FOR AXIAL STAGE, REMOVING HEAVY PARTICLES | 2015 |
|
RU2594832C1 |
AXIAL-FLOW COMPRESSOR FOR TRANSPORTATION OF NATURAL GAS | 2004 |
|
RU2312254C2 |
DEVICE FOR REMOVING FOREIGN OBJECTS FROM AIR FLOW IN FIRST STAGE OF AXIAL COMPRESSOR OR SUB-ZONE OF GAS TURBINE ENGINE FAN | 2017 |
|
RU2672196C2 |
TURBOMACHINE DOUBLE-ROW VANE CASCADE | 0 |
|
SU1321838A1 |
TURBOMACHINE BLADE SYSTEM | 2016 |
|
RU2626285C1 |
SECOND STAGE IMPELLER WHEEL OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VARIANTS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2636998C1 |
TURBOJET LOW-PRESSURE COMPRESSOR ROTOR FOURTH-STAGE IMPELLER | 2015 |
|
RU2612282C1 |
Authors
Dates
1995-12-20—Published
1993-03-05—Filed