Patent ID: 11499429

Abstract:
A rotor blade airfoil of a turbomachine, which rotor blade airfoil has: a leading edge, a trailing edge, and a profile chord length which is dependent on the height of the blade airfoil. In a side view of the blade airfoil, a maximum projected chord length his defined as the axial spacing between the axially foremost point of the leading edge and the axially rearmost point of the trailing edge of the blade airfoil in the side view under consideration. Here, the axial position of the leading edge varies in a manner dependent on the height of the blade airfoil above a front axial region. Provision is made whereby, furthermore, with respect to the side view under consideration, the axial position of the trailing edge of the blade airfoil varies in a manner dependent on the height of the blade airfoil above a rear axial region, wherein the variation of the axial position of the trailing edge in the rear axial region amounts to at least 10% of the maximum projected chord length, the trailing edge of the blade airfoil assumes the axially rearmost point at a height of the blade airfoil that lies in the range between 20% and 50% of the total height of the blade airfoil at the trailing edge, and the leading edge of the blade airfoil assumes the axially foremost point at a height of the blade airfoil that lies in the range between 15% and 35% of the total height of the blade airfoil at the leading edge.