BLADE PLATFORM, BLADED ROW, IMPELLER DISK AND GAS TURBINE ENGINE Russian patent published in 2023 - IPC F04D29/26 F01D5/02 F01D5/30 

FIELD: gas turbine engines.

SUBSTANCE: platforms (6, 7, 8) blades, blade ring (100), impeller disk and gas turbine engine) are proposed. The platform of the blade contains a pair of side edges (71, 72) and a pair of end edges (73, 74), and the first side edge (71) in the direction of its extension contains a linear section (700) and a curved section (800), while the linear section (700) contains the first linear section (701) and the second linear section (702), and the curved section (800) contains the first curved section (801) and the second curved section (802). The first and second linear sections (701, 702) are connected to two ends of the curved section (800) and extend tangentially to the curved section (800), while the bends of the first and second curved sections (801, 802) extend in the same direction, and the first and second curved portions (801), 802) are tangentially connected on the outside.

EFFECT: effective performance.

9 cl, 12 dwg