IMPELLER FOR TURBOMASHINERY Russian patent published in 2017 - IPC F01D5/30 F01D11/02 

FIELD: machine engineering.

SUBSTANCE: impeller for turbomachine, such as a turbojet engine or an aircraft turboprop engine, comprises a rotor disk (50) including, on its outer periphery, stiffeners (14) defining axial mounting seats (18) and radial holding of blade locks. The blades have shelves arranged side by side along the circumference to limit the annular airflow path. A ring peak (48) extending substantially axially in the upstream direction is mounted on the upstream side of the disc (50) to restrict the passage of air outside the annular path. Sealing means (84) are provided between the annular lip (48) and the upstream ends of the blade flanges. The annular lip (48) comprises an annular projection (52) extending axially in the downstream direction and radially inwardly of the radial retention means (70) of the circular peak (48) on the disc (50). These retaining means (70) are formed protruding axially on the upstream side of the disc (50). The sealing means (84) are located radially inside the annular lip (48) and the upstream ends of the blade flanges.

EFFECT: reduction of the radial forces applied to the blades.

12 cl, 5 dwg