Patent ID: 7118330
Filing Date: 2006-10-10
Classification: F01D,F05D,Y02T,Y10S

Abstract:
1. A turbine nozzle, comprising: airfoils stacked along a stacking axis, wherein high curvature portions on a suction surface in airfoil sections successively formed along the stacking axis describe a parabola line that curves toward a pressure side of the airfoil when seen from a front or a rear of the turbine nozzle, wherein a point of maximum curvature in each airfoil is located at a midpoint along the stacking axis of a straight line that connects a first intersection between the parabola line and an inner band in the turbine nozzle with a second intersection between the parabola line and an outer band in the turbine nozzle, and wherein a distance of the point of maximum curvature to the straight line is within a range from 2 to 3% of a distance between the first and second intersections along the stacking axis of the airfoil.