Guide vane ring element for a turbomachine

Patent metadata

Field	Value
Publication number	US-11066949-B2
Application number	US-201615223262-A
Country	US
Kind code	B2
Filing date	Jul 29, 2016
Priority date	Aug 3, 2015
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

The present invention relates to a guide vane ring element for a turbomachine, such as a gas turbine, with at least one drilled hole for the at least partial uptake of a flange of a rotatable guide vane, wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion and, in particular, has a radius.

First claim

What is claimed is:

1. A guide vane ring element for a turbomachine, comprising:
a vane ring element defining at least one drilled hole therein;
the at least one drilled hole being configured for the at least partial uptake of a flange of a rotatable guide vane, wherein an edge of the at least one drilled hole on the vane ring element side is designed convexly in a first circumferential portion along the edge,
wherein the convexly designed first circumferential portion has an edge that is curved towards the rotatable guide vane,
wherein the first circumferential portion is configured and arranged to reduce any leakage between the vane element and the rotatable guide vane, and the rotatable guide vane is partially shaped such that it corresponds to a shape of the first circumferential portion,
wherein a radius of the convexly designed first circumferential portion is at least 1% and/or at most 50% of a radius and/or a radial depth of the drilled hole,
wherein the radius varies along the edge in the first circumferential portion, and
wherein the radius increases along the edge in a first subregion of the first circumferential portion and decreases in an adjoining, shorter, second subregion of the first circumferential portion.

2. The guide vane ring element according to claim 1 , wherein the edge has a constant radius along the edge in a second circumferential portion.

3. The guide vane ring element according to claim 2 , wherein a maximum radius of the second circumferential portion is smaller than a radius, a maximum or a minimum, of the first circumferential portion.

4. The guide vane ring element according to claim 1 , wherein the edge is processed by milling at least in the first circumferential portion, by means of a form milling cutter.

5. The guide vane ring element according to claim 1 , wherein the convex edge is formed by a ruled surface.

6. The guide vane ring element according to claim 1 , wherein the rotatable guide vane is configured as a guide vane cascade element, wherein the flange of the rotatable guide vane is mounted rotatably at least in part in one of the at least one drilled hole.

7. The guide vane ring element according to claim 6 , wherein a face end of the rotatable guide vane on the drilled hole side lies radially opposite the first circumferential portion, substantially in the middle thereof, in a neutral position of the rotatable guide vane.

8. The guide vane ring element according to claim 1 , wherein the element is configured and arranged in a turbomachine.

9. The guide vane ring element according to claim 1 ,
wherein the first circumferential portion extends over a portion of the edge in the range of 2%-50%, and
wherein a second circumferential portion extends over a remaining portion of the edge.

Assignees

• MTU Aero Engines AG

Inventors

• Mairhanser Vitalis
• Effner Birgit
• Halcoussis Alexander
• Wolf Hannes

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2240/129

  Cascades, i.e. assemblies of similar profiles acting in parallel · CPC title

• F05D2240/80

  Platforms for stationary or moving blades · 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