Patent ID: 11892012
Assignee: MTU AERO ENGINES AG
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. An adjustable guide vane for a high-pressure compressor of an aircraft gas turbine, comprising:
a radially outer bearing section,
a radially inner bearing section,
a vane section, which extends in the radial direction between the outer bearing section and the inner bearing section,
wherein the outer and the inner bearing sections are configured and arranged so the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and
wherein the radially inner bearing section has a cylindrical or plate-shaped base and has a lateral surface that that is formed circumferentially around the vane axis, the lateral surface being of convex shape,
wherein a radius of curvature of the convex lateral surface is at least double the maximum diameter of the radially inner bearing section.