FIELD: machine building.
SUBSTANCE: present invention relates to an apparatus for cooling oil in a gas turbine engine, such as a turbojet or turboprop aircraft engine. It comprises a pipeline for circulation of cooling air, means for injecting oil into said pipeline and means for extracting the oil mixed with the cold air flow located in the pipeline downstream of the injection means.
EFFECT: technical result of the invention is simplification of the device and an increase of its efficiency.
9 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE, CONTAINING PRIMARY AND SECONDARY COOLERS OF LUBE OIL | 2013 |
|
RU2625391C1 |
| TURBINE ENGINE OIL CIRCUIT COOLING | 2016 |
|
RU2709761C2 |
| LUBRICATING SYSTEM OF GAS COMPRESSOR UNIT WITH STATIONARY GAS TURBINE ENGINE | 2019 |
|
RU2742591C1 |
| COMPRESSOR WITH OIL INJECTION COMPRISING THERMOSWITCH | 2006 |
|
RU2362052C1 |
| METHOD AND SYSTEM TO GENERATE POWER TO DRIVE ENGINE AUXILIARY COMPONENTS | 2004 |
|
RU2352800C2 |
| METHOD AND SYSTEM OF GAS-TURBINE ENGINE LUBRICATION | 2009 |
|
RU2498096C2 |
| AIRCRAFT GAS TURBINE ENGINE | 2011 |
|
RU2458237C1 |
| AIRCRAFT GAS TURBINE ENGINE | 2011 |
|
RU2458235C1 |
| METHOD FOR REDUCTION OF DEGREE OF DILUTION OF OIL IN ENGINE (VERSIONS) | 2015 |
|
RU2692605C2 |
| BIROTATING BYPASS GAS TURBINE ENGINE | 2023 |
|
RU2803681C1 |
