AXIAL-FLOW MULTISTAGE COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering. SUBSTANCE: invention relates to axial-flow compressors of gas-turbine engines of aircraft and ground application. In proposed axial-flow compressor of gas -turbine engine first working blade from inlet is provided with shroud strip, second working blade is also provided with shroud strip and third and fourth blades are provided with thickened air portion in peripheral and root sections at where C_max.per1 is maximum thickness of airfoil portion profile of first working blade in peripheral section; C_max.root1 is maximum thickness of airfoil portion profile of first working blade in root section; C_max.per2 is maximum thickness of airfoil portion profile of second working blade in peripheral section; C_max.root2 is maximum thickness of airfoil portion profile of second working blade in root section; C_max.root3 - is maximum thickness of airfoil portion profile of third working blade in root section; C_max.per4 - is maximum thickness of airfoil portion profile of fourth working blade in peripheral section. EFFECT: reduced weight and axial length of compressor and improved reliability owing to prevention of resonance, torsional and linear oscillations of working blades. 3 dwg