FIELD: engines and pumps.
SUBSTANCE: gas turbine engine turbo compressor consists of compressor, turbine incorporating rear support with bearing arranged between aforesaid compressor and turbine, the said rear support being arranged above the combustion chamber. First cooling stage is arranged around oil chamber. Second cooling stage is arranged above the chamber located between inner and outer flanges. Decompression chamber is arranged between the first and second chambers. Third cooling chamber is formed by ring casings between the second and decompression chambers to communicate with the chamber via cooling channels made in inner flange above inner labyrinth. Cooling chambers are arranged around oil pipes form fourth cooling chamber.
EFFECT: reduced gaps in labyrinth seals that adds to higher reliability and efficiency.
3 dwg, 3 cl
| Title | Year | Author | Number |
|---|---|---|---|
| DEVICE FOR SHAFT COOLING OF FREE TURBINE OF GAS TURBINE UNIT | 2014 |
|
RU2572515C2 |
| FREE TURBINE SHAFT COOLING DEVICE OF GAS-TURBINE PLANT | 2018 |
|
RU2701424C1 |
| GAS-TURBINE ENGINE TURBOCOMPRESSOR | 2005 |
|
RU2296873C2 |
| TURBOCOMPRESSOR OF GAS-TURBINE ENGINE | 2005 |
|
RU2300003C2 |
| TURBO-JET ENGINE WITH COMBINED SUPPORT OF LOW AND HIGH PRESSURE TURBINE | 2009 |
|
RU2414614C1 |
| BY-PASS GAS-TURBINE ENGINE | 2001 |
|
RU2224905C2 |
| GAS TURBINE ENGINE | 2001 |
|
RU2211935C2 |
| COMPRESSOR AND GAS-TURBINE ENGINE | 1989 |
|
RU2110700C1 |
| GAS-TURBINE ENGINE | 2002 |
|
RU2225523C2 |
| GAS-TURBINE ENGINE | 2005 |
|
RU2307947C2 |
