Guide vane segment with radical securing elements

Patent metadata

Field	Value
Publication number	US-10370989-B2
Application number	US-201615367752-A
Country	US
Kind code	B2
Filing date	Dec 2, 2016
Priority date	Dec 4, 2015
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

The invention relates to a guide vane segment for a gas turbine comprising at least one radially outer shroud and one radially inner shroud, which extend along a respective arc and together form an annular segment, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacent to one another in the peripheral direction and are joined to the inner shroud and to the outer shroud in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction, the outer shroud comprises an axially front end wall element and an axially rear end wall element in such a way that the outer shroud and the two end walls form a tub-like profile in lengthwise section.

First claim

What is claimed is:

1. A guide vane segment for a gas turbine, comprising at least one radially outer shroud and one radially inner shroud, which extend along a respective arc and together form an annular segment, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacent to one another in the peripheral direction and are joined to the inner shroud and to the outer shroud in a material-bonded manner and are joined in a one-piece manner, wherein, in an axial lengthwise direction, the outer shroud comprises an axially front end wall element and an axially rear end wall element in such a way that the outer shroud and the two end walls form a tub-like profile in lengthwise section, wherein, at the axially rear end wall, at least one radial securing element is provided, which secures the guide vane segment in the radial direction relative to a surrounding housing, wherein the radial securing element is a projection with a support section that rests against a corresponding counterpiece on the housing, wherein the support segment has a support surface area that lies in a plane, the normal vector of which has vector components in the peripheral direction as well as in the axial direction or/and in the radial direction.

2. The guide vane segment according to claim 1 , wherein the guide vane segment has, in the peripheral direction at the outer shroud, two lateral shroud surfaces arranged at a distance from each other, which are designed in such a way that they can come into contact with a lateral shroud surface of an adjacent guide vane segment, wherein the radial securing element is flush with at least one of the lateral shroud surfaces.

3. The guide vane segment according to claim 2 , wherein the guide vane segment comprises, in the peripheral direction, two radial securing elements arranged at a distance with respect to each other.

4. The guide vane segment according to claim 3 , wherein one radial securing element is flush with the lateral shroud surface and that the other radial securing element is arranged at a distance with respect to the other lateral shroud surface.

5. The guide vane segment according to claim 3 , wherein the distance between the two radial securing elements measured in the peripheral direction is smaller than the distance between the two lateral shroud surfaces measured in the peripheral direction.

6. The guide vane segment according to claim 1 , wherein the radial securing element is manufactured by linear grinding.

7. The guide vane segment according to claim 1 , wherein the support segment has a second surface area that lies in a second plane, the normal vector of which has vector components in the peripheral direction as well as in the axial direction or/and in the radial direction.

8. The guide vane segment according to claim 7 , wherein the second surface area and the support surface area are at an angle with respect to each other, wherein the angle formed between the first plane and the second plane in a sectional plane that is spanned by the radial direction and the axial direction lies in a range between 70° and 90°.

9. The guide vane segment according to claim 1 , wherein the guide vane segment comprises, in the peripheral direction, a peripheral securing element in a central region of the rear end wall.

10. A method for the manufacture of a guide vane segment for a gas turbine, comprising the following steps:
providing an unfinished guide vane segment with at least one radially outer shroud and one radially inner shroud, which extend along a respective arc and together form an annular segment, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacent to one another in the peripheral direction and are joined to the inner shroud and to the outer shroud in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction, the outer shroud comprises an axially front end wall element and an axially rear end wall element in such a way that the outer shroud and the two end walls form a tub-like profile in lengthwise section, and with at least one unfinished radial securing element;
aligning the unfinished guide vane segment relative to a linear grinding apparatus so that material can be removed from the unfinished radial securing element by means of the linear grinding apparatus;
grinding of the unfinished radial securing element by the linear grinding apparatus until the unfinished radial securing element has assumed the form of a radial securing element with a support segment that has a support surface area, which lies in a first plane, the normal vector of which has vector components in the peripheral direction as well as in the axial direction or/and in the radial direction.

11. The method according to claim 10 , wherein the step of aligning the unfinished guide vane segment and the step of grinding are each carried out one time for a respective unfinished radial securing element, when two or more unfinished radial securing elements are provided at the unfinished guide vane segment.

12. The method according to claim 10 , wherein the step of aligning the unfinished guide vane segment relative to the linear grinding apparatus is performed in such a way that the linear grinding apparatus can be guided or moved at a distance with respect to the other components of the unfinished guide vane segment during grinding of the unfinished radial securing element and can be guided or moved at a distance with respect to a peripheral securing element or a corresponding unfinished peripheral securing element provided in the peripheral direction in a central region on the rear end wall.

13. The guide vane segment according to claim 1 , wherein a plurality of the guide vane segments is configured and arranged in a peripheral direction to form a guide vane ring for at least one turbine stage.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Feldmann Manfred
• Stanka Rudolf
• Thiele Oliver
• Kislinger Bernd
• Hein Manuel

Classifications

• B24B19/14

  for grinding turbine blades, propeller blades or the like (using grinding belts B24B21/16) · CPC title

• F05D2230/10

  by removing material · CPC title

• F01D9/041 Primary

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

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title