GAS TURBINE AXIAL COMPRESSOR IMPELLER (VERSIONS) Russian patent published in 2009 - IPC F04D29/34 F01D5/30 

FIELD: engines and pumps.

SUBSTANCE: invention relates to compressor production and can be used in impellers of gas turbine engine axial compressors. Proposed impeller comprises disk with slots arranged at an angle to compressor axis and accommodating vanes. Aforesaid vanes have thrust ledge whereto forces act resulted centrifugal forces originating in impeller rotation. There is metal plate fitted between impeller inlet face and thrust ledge face, its thickness equal to or exceeding 0.3 mm. Aforesaid plate features outer sizes exceeding those of disk slot, plate inner shape repeats that of the vane root. Disk face surfaces adjoining the said metal plate are arranged at an angle to compressor axis equal to or smaller than 90°. In compliance with the second version thrust ledge features sizes smaller than width and height of vane root. In this version, metal plate is arranged between impeller inlet face and thrust ledge face, its outer sizes exceeding those of disk slot to stop clearance in joint. Metal plate has closed slot with width equal to thrust ledge arranged on vane root inlet face and height that allows mounting the said plate on thrust ledge. Disk thrust surface and vane root inlet face adjoining the metal plate are arranged at an angle to compressor axis equal to or smaller than 90°.

EFFECT: uniform distribution of axial load, minimisation of gas overflows.

2 cl, 5 dwg