GAS TURBINE ENGINE Russian patent published in 2017 - IPC F01D9/04 F01D5/18 F01D5/28 

FIELD: engine.

SUBSTANCE: gas turbine engine comprises combustion chamber and unit of guide vanes. Unit of guide vanes comprises first and second assemblies of guide vanes, located along circumferential direction of turbine, as well as additional first assembly of guide vanes. First assembly of guide vanes containing first platform and first number of first airfoils, attached to first platform. Second assembly of guide vanes, containing second platform and second number of second airfoils, attached to second platform. First number of first airfoils differs from second one, wherein first assembly of guide vanes is made with higher heat resistance, than second assembly of guide vanes. First assembly of guide vanes is coated with first heat barrier coating, and second one is coated with second heat barrier coating, wherein first thickness of first thermal barrier layer exceeds second thickness of second thermal barrier layer. Additional first assembly of guide vanes comprises additional first number of additional first airfoils, it lies between first assembly of guide vanes and second assembly of guide vanes and has first thermal barrier coating. Additional first number of additional first airfoils differs from second number of second airfoils.

EFFECT: invention simplifies manufacturing of assembly of guide vanes of gas turbine engine with preservation of its service life.

7 cl, 2 dwg