DUAL-CURVATURE VANE FOR TURBINE GUIDE VANES Russian patent published in 2008 - IPC F01D5/14 

FIELD: mechanics.

SUBSTANCE: turbine compressor guide vanes feature orthogonal longitudinal, tangential and radial axes. Inner and outer surfaces are located between the vane inner and outer edges in radial direction, while, in lengthwise direction, they are arranged between the front and rear edges. Note that multiple sections are arranged along radial direction with their centers of gravity being located along the structural design axis. Note here that vanes feature inner, central and outer parts. The inner part is arranged radially between the vane inner edge and central part inner edge. Outer part is arranged radially between the central part outer edge and vane outer edge. Structural design axis has in its central part a tangential component with dual curvature, while the vane inner and outer parts feature a tangential component parallel to the vane radial axis.

EFFECT: vane with lower longitudinal bending resistance not deteriorating aerodynamic properties of guide vanes.

8 cl, 3 dwg