TURBINE ELEMENT OF GAS TURBINE ENGINE WITH MICROCHANNEL COOLING (VERSIONS) Russian patent published in 2017 - IPC F01D5/18 F01D5/20 

FIELD: engines and pumps.

SUBSTANCE: turbine element of the gas turbine engine comprises a substrate having an outer surface, an inner surface, and a butt. The inner surface defines at least one hollow inner space. The outer surface defines one or more grooves, wherein each groove extends at least partially along the outer surface of the substrate and has a base. The element also comprises a coating disposed over at least a portion of the outer surface of the substrate. The coating comprises at least a structural coating which extends radially so that the groove together with the structural coating bound one or more channels for cooling the elements. The butt includes a cover enclosing said hollow inner space and a rim located in the radial outer end of the substrate. The butt rim at least partially bounds at least one outlet channel being in fluid communication with at least one cooling channel.

EFFECT: increasing the blade butt cooling efficiency and service life.

31 cl, 14 dwg