Patent ID: 11927109
Assignee: MTU AERO ENGINES AG
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A blade for a gas turbine of an aircraft engine, comprising:
a blade airfoil, having a leading edge and a trailing edge, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, wherein the stagger angle comprises a change over the height that does not decrease with increasing height at least over certain portions, and in an adjoining second region between the second height and a third, greater height, the change in the stagger angle decreases with increasing height at least over certain portions, the first height representing at least 30% and at most 60% of the blade airfoil height, the second height representing at least 50% and at most 80% of the blade airfoil height, and the third height representing at least 80% and at most 100% of the blade airfoil height;
wherein the blade airfoil has a portion with an S-shaped profile in at least one cross-sectional portion at the third height of the airfoil.