FIELD: engines and pumps.
SUBSTANCE: gas turbine engine transition compartment comprises first and second ends and housing extending there between. Said housing comprises inner and outer surfaces and turbulence promoter. Turbulence promoter extends continuously in spiral and make an integral structure over the entire outer surface. It features semicircular cross-section and is configured so that first part of air flow descends in spiral around transition compartment while second part is forced over spiral turbulence promoter to facilitate cooling of said compartment. Besides, this invention covers the gas turbine engine comprising combustion chamber unit and transition compartment described above and attached to combustion chamber to extend therefore.
EFFECT: higher engine efficiency and longer life.
10 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS-TURBINE COMBUSTION SYSTEM | 2013 |
|
RU2561956C2 |
| GAS TURBINE ENGINE (VARIANTS) | 2012 |
|
RU2688073C2 |
| GAS TURBINE ENGINE COOLING DEVICE | 2019 |
|
RU2799867C2 |
| GAS TURBINE ENGINE (VERSIONS) | 2014 |
|
RU2639921C2 |
| GAS-TURBINE UNIT AND UNIT WITH INJECTOR VANES (VERSIONS) | 2010 |
|
RU2531110C2 |
| HELICOPTER GAS TURBINE ENGINE WITH NOISE REDUCED BY EJECTOR NOISE KILLER | 2007 |
|
RU2451193C2 |
| GAS TURBINE ENGINE AND METHOD OF COOLING NOZZLE VANES | 2007 |
|
RU2453710C2 |
| GAS TURBINE ENGINE OPERATING METHOD AND GAS TURBINE ENGINE | 2019 |
|
RU2726861C1 |
| ROTOR OF COMPRESSOR OF GAS TURBINE ENGINE AND GAS TURBINE ENGINE | 2009 |
|
RU2500892C2 |
| GAS TURBINE ENGINE | 2014 |
|
RU2638709C2 |
