FIELD: engines and pumps.
SUBSTANCE: proposed gas turbine unit comprises compressor coupled with the drive consisting of the first and second stages, inner and outer shafts with the fan fitted on inner shaft and compressor fitted on outer shaft. It comprises also HP and LP turbines with cooling system, and primary combustion chamber arranged between compressor and HG pressure turbine. Gas turbine unit comprises outer combustion chamber mounted downstream of HP turbine, extra compressor and heat exchanger-heater communicated, via heat carrier circulation lines, with heat exchanger arranged downstream of said outer combustion chamber.
EFFECT: higher efficiency and reliability.
3 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE FOR GAS-COMPRESSOR PLANT | 2008 |
|
RU2374468C1 |
| NUCLEAR GAS TURBINE ENGINE WITH AFTERBURNING | 2008 |
|
RU2376483C1 |
| GAS TURBINE LOCOMOTIVE AND ITS POWER PLANT | 2008 |
|
RU2363604C1 |
| TURBOPROP GAS TURBINE ENGINE WITH NUCLEAR POWER PLANT | 2010 |
|
RU2424438C1 |
| POWER PLANT OF NUCLEAR GAS TURBINE LOCOMOTIVE | 2008 |
|
RU2392461C1 |
| POWER PLANT OF GAS-TURBINE LOCOMOTIVE WITH RECOVERY OF HEAT | 2006 |
|
RU2312231C1 |
| NUCLEAR GAS TURBINE LOCOMOTIVE AND ITS POWER PLANT | 2008 |
|
RU2375219C1 |
| LOCOMOTIVE POWER GAS TURBINE PLANT | 2006 |
|
RU2327890C1 |
| NUCLEAR GAS TURBINE AIRCRAFT ENGINE | 2008 |
|
RU2379532C1 |
| COMBINED NUCLEAR BOOST AIRCRAFT ENGINE | 2008 |
|
RU2391525C1 |
