FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine building, particularly, to design of turbomachinery axial compressor stator blades. Stator unit of axial compressor comprises outer shell ring 1, inner shell ring 2 and blades 3 with outer 4 and inner 5 shelves fixed in external 1 and inner 2 rings, respectively. Inner flanges 5 of blades 3 are conjugated with inner shell 2 with tightness along conical surface 7 and fixed therein by fastening elements 13 installed in coaxial holes 10 and 12, made respectively in inner flanges 5 and ledges 9 of inner shell. Axes of holes 10 and 12 are located radially relative to axis of vane assembly.
EFFECT: invention is aimed at enlarging the range of technical means – efficient and reliable blade blades of stator of axial compressor.
1 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614709C1 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| AXIAL-FLOW FAN OR COMPRESSOR IMPELLER AND FAN OF BYPASS FANJET INCORPORATING SAID IMPELLER | 2010 |
|
RU2460905C2 |
| ROTOR FORTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630919C1 |
| ROTOR SIXTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630922C1 |
| IMPELLER WHEEL OF SEVENTH STAGE OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VERSIONS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630923C1 |
| FIFTH STAGE IMPELLER WHEEL OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VERSIONS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630920C1 |
| TURBOMACHINE AXIAL-FLOW COMPRESSOR | 2003 |
|
RU2295656C2 |
| ROTOR EIGHTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630924C1 |
| IMPELLER WHEEL OF FIRST STAGE 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 |
|
RU2630918C1 |
