Adjustable guide vane with convexly shaped, radially inner storage section for a gas turbine, in particular an aircraft gas turbine

Patent metadata

Field	Value
Publication number	US-11892012-B2
Application number	US-202218052924-A
Country	US
Kind code	B2
Filing date	Nov 6, 2022
Priority date	Nov 8, 2021
Publication date	Feb 6, 2024
Grant date	Feb 6, 2024

Abstract

An adjustable guide vane for a compressor, in particular a high-pressure compressor, of a gas turbine, in particular an aircraft gas turbine is described, the vane comprising a radially outer bearing section, a radially inner bearing section, and 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 designed in such a way that the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner bearing section is configured like a journal (cone-shaped) and has a lateral surface that is formed circumferentially about the vane axis, the lateral surface being of convex shape. In this way, it is provided that the radius of curvature of the convex lateral surface is at least double the maximum diameter of the bearing section.

First claim

What is claimed is:

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.

2. The adjustable guide vane according to claim 1 , wherein the radius of curvature of the convex lateral surface is three to ten times the maximum diameter of the radially inner bearing section.

3. The adjustable guide vane according to claim 1 , wherein the adjustable guide vane is mounted exclusively over the bearing section on its radially inner-lying side relative to the vane section.

4. An aircraft gas turbine, comprising:
at least one adjustable high-pressure compressor,
wherein the high-pressure compressor has a plurality of adjustable guide vanes arranged next to one another in the peripheral direction according to claim 1 .

5. The aircraft gas turbine according to claim 4 , wherein the compressor has a radially inner bearing ring with a plurality of cylindrical drill holes that are arranged next to one another in the peripheral direction, wherein an inner bearing section with convex lateral surface is taken up in each cylindrical drill hole.

6. The aircraft gas turbine according to claim 4 , further comprising a radially outer adjustable ring device that is joined with the radially outer bearing sections of the adjustable guide vanes so that all adjustable guide vanes are simultaneously rotatable about their respective vane axis.

Assignees

• MTU Aero Engines AG

Inventors

• Hoelzel Andreas
• Roth Christian
• Prieschl Franz
• Eichner Josef
• Mosbacher Mike
• Mairhanser Vitalis

Classifications

• F04D29/563 Primary

  specially adapted for elastic fluid pumps · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F04D19/022

  with concentric rows of vanes; · CPC title

• F02C3/064

  the compressor having concentric stages · CPC title

• F05D2220/3216

  for a special compressor stage · CPC title