FIELD: mechanical engineering; gas turbines.
SUBSTANCE: invention relates to stator of gas-turbine axial-flow compressor containing rigid outer ring equipment 2, rings 4a, 4b, 4c axially adjoining each other and arranged inside relative to said equipment 2 and carrying rims of fixed guide vanes 5. Said rings are formed by ring sectors 7 secured on equipment 2 whose inner wall limits aerodynamic channel passing compressed gaseous medium in outer direction differing in that ring sectors 7 are essentially soldered sectors formed by filler of cellular structure 8 enclosed between inner sheet 10 limiting said aerodynamic channel and outer sheet 9 and that tie with equipment 2 is provided only by means of outer sheet 9.
EFFECT: improved reliability in operation.
5 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COMPRESSOR STATOR FOR TURBOMACHINE | 2012 |
|
RU2631585C2 |
| TURBOMACHINE STATOR BLADE CIRCULAR SECTOR AND AIRCRAFT TURBOMACHINE | 2010 |
|
RU2537997C2 |
| STATOR OF AIRCRAFT GAS TURBINE ENGINE AND AIRCRAFT GAS TURBINE ENGINE | 2015 |
|
RU2706098C2 |
| GAS TURBINE ENGINE GUIDE VANES SEALING DEVICE | 2012 |
|
RU2604777C2 |
| ANGULAR SECTOR OF A STATOR FOR A TURBINE ENGINE COMPRESSOR, A TURBINE ENGINE STATOR AND A TURBINE ENGINE INCLUDING SUCH A SECTOR | 2011 |
|
RU2584078C2 |
| AIRCRAFT GAS TURBINE ENGINE TURBINE STATOR WITH VIBRATION DAMPER | 2008 |
|
RU2474697C2 |
| SYSTEM FOR ROTATING THE ROTOR OF A GAS TURBINE ENGINE AND ROTOR OF A GAS TURBINE ENGINE | 2018 |
|
RU2767258C2 |
| JACKET OF TURBOJET ENGINE WITH MULTILAYER PANELS AND DRAINAGE SYSTEM | 2019 |
|
RU2716802C1 |
| DESIGN OF TURBOJET ENGINE WITH DOUBLED FAN IN FRONT PART | 2005 |
|
RU2357092C2 |
| SECTOR OF STATOR BLADES, AXIAL TURBOMACHINE STATOR, AXIAL TURBOMACHINE | 2014 |
|
RU2619914C2 |
