FIELD: engines and pumps.
SUBSTANCE: turboprop gas turbine engine incorporates a propeller, an air intake, a compressor, a combustion chamber, a turbine and a jet nozzle. The engine represents a two-shaft design. Behind the turbine, the Stirling engine is arranged coupled by its inner shaft, via a reduction gear or a multiplexer, with the propeller. Air branch pipes are connected to the said Striling engine, their ends passing to atmosphere and being connected to either air intake or the output of the compressor first stages.
EFFECT: higher power plant efficiency and reliability.
4 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBOPROP GAS TURBINE ENGINE WITH NUCLEAR POWER PLANT | 2010 |
|
RU2424438C1 |
| NUCLEAR GAS-TURBINE AVIATION ENGINE | 2007 |
|
RU2349775C1 |
| NUCLEAR GAS TURBINE ENGINE | 2007 |
|
RU2336429C1 |
| GAS TURBINE LOCOMOTIVE AND ITS POWER PLANT | 2008 |
|
RU2363604C1 |
| DOUBLE-STAGE GAS TURBINE ENGINE | 2007 |
|
RU2334115C1 |
| COMBINED AIRCRAFT ENGINE | 2008 |
|
RU2373418C1 |
| DEVICE FOR HOT WATER INJECTION INTO WELL | 2008 |
|
RU2382878C1 |
| NUCLEAR GAS TURBINE AIRCRAFT ENGINE | 2008 |
|
RU2379532C1 |
| NUCLEAR TURBOPROP GAS TURBINE ENGINE | 2010 |
|
RU2424441C1 |
| NUCLEAR GAS TURBINE LOCOMOTIVE AND ITS POWER PLANT | 2008 |
|
RU2375219C1 |
