ROTOR OF GAS TURBINE ENGINE, COMPRISING BLADES WITH ATTACHABLE PLATFORMS, AND GAS TURBINE ENGINE CONTAINING SUCH ROTOR Russian patent published in 2019 - IPC F01D5/30 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine rotor comprises a disc, multiple blades and multiple platforms. On its periphery, the disk has primary slots, and each blade comprises a leg having a bulge in the lower part, which is locked in axial direction in primary slots. Each platform is located between two successive blades and comprises rectilinear platform, thickening passing radially under the platform, and spout. Thickening is made with possibility of blocking in axial direction in secondary slots made on periphery of disk, at that secondary slots are located between two successive primary slots. Spout passes in axial direction of rotor and forms annular sector located opposite at least two consecutive blades. Another invention of the group relates to a gas turbine engine comprising the above rotor.

EFFECT: group of inventions allows reducing stresses in the rotor bulge, increasing the number of blades, and also simplifying the rotor assembly and dismantling.

11 cl, 6 dwg