Patent ID: 8152473
Filing Date: 2012-04-10
Classification: F01D,F04D,F05D,Y10S

Abstract:
1. An airfoil design for rotor and stator blades of a turbomachine, which is defined by a course of a skeleton line established by a skeleton line angle (α) over a chord length and by a course of a leading edge and a blade height as well as a blade tip ending at an air gap, wherein the skeleton line in blade profile sections which lie in an area starting at the blade tip and extending up to 30 percent of the blade height, runs in a skeleton line angle distribution range between an upper limiting curve and a lower limiting curve in which a uniformed pressure load is generated along a blade surface, with the dimensionless skeleton line angle (α) at a respective point (l x ), wherein (l x ) is a percentage of a chord length, (l) being: for the upper limiting curve, and: for the lower limiting curve.