Guide vane segment with curved relief gap

Patent metadata

Field	Value
Publication number	US-10731489-B2
Application number	US-201816028749-A
Country	US
Kind code	B2
Filing date	Jul 6, 2018
Priority date	Jul 11, 2017
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

The invention relates to a guide vane segment for aircraft gas turbine, which extend along a respective circular arc and together form an annular section, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacently in the peripheral direction, the outer shroud and the two sealing walls form a trough-like profile in longitudinal section, wherein, at the axially front or/and rear sealing wall element(s), at least one relief gap with a main section is provided, which extends substantially radially inward, starting from a radial outer edge of the respective front or/and rear sealing wall element(s) along the sealing wall element. According to the invention, it is proposed that the relief gap has at least one additional section that adjoins the main section radially inward, wherein the additional section is formed by at least one curved subsection.

First claim

What is claimed is:

1. A guide vane segment for an aircraft gas turbine, comprising at least one radially outer shroud and one radially inner shroud, which extend along a respective circular arc and together form an annular section, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacently in the peripheral direction, which are joined, in a material-bonded manner and in one piece, to the inner shroud and to the outer shroud, wherein, in relation to an axial longitudinal direction, the outer shroud comprises an axially front sealing wall element and an axially rear sealing wall element configured so that the outer shroud and the two sealing walls form a trough-like profile in longitudinal section, wherein, at the axially front or/and rear sealing wall elements, at least one relief gap with a main section is provided, which extends substantially radially inward, starting from a radial outer edge of the respective front or/and rear sealing wall elements along the sealing wall element, wherein the relief gap has at least one additional section that adjoins the main section radially inward, wherein the additional section is formed by at least one curved subsection,
wherein the main section is joined to a second subsection by a third subsection and is joined to a radially outer end of the second subsection and the at least one additional section adjoins the third subsection, and
wherein the third subsection and the adjoining second subsection are S-shaped in configuration.

2. The guide vane segment according to claim 1 , wherein the relief gap extends in the peripheral direction in its radially innermost region or/and terminates in one end region or a plurality of end regions, which lies or lie further radially outward than a radially innermost region of the relief gap.

3. The guide vane segment according to claim 2 , wherein the additional section has at least one curved first subsection and the second subsection is at least one curved second subsection, which are joined to one another, or/and in that the first subsection is curved with a first radius, and in that the second subsection is curved with a second radius, wherein the first radius is greater than the second radius.

4. The guide vane segment according to claim 3 , wherein the first subsection is configured and arranged convexly so that it extends radially inward, starting from a region of the junction to the second subsection.

5. The guide vane segment according to claim 3 , wherein the second subsection is configured and arranged such that it has a tangent that runs parallel to the main section.

6. The guide vane segment according to claim 3 , wherein the second subsection is convexly designed in the peripheral direction away from the main section.

7. The guide vane segment according to claim 1 , wherein a first subsection is adjoined at the second subsection, which is joined to the third subsection.

8. The guide vane segment according to claim 1 , wherein the relief gap has the shape of a question mark without the dot and the main section is arranged in a middle region of the relief gap in the peripheral direction.

9. The guide vane segment according to claim 3 , wherein a respective transition is formed between the first subsection and the second subsection through a transition section, wherein the transition section has a transition radius that is less than the first radius and less than the second radius.

10. The guide vane segment according to claim 1 , wherein a plurality of guide vane segments are arranged adjacently in the peripheral direction to each other in a compressor arrangement and/or a turbine arrangement in of a gas turbine.

Assignees

• MTU Aero Engines AG

Inventors

• Uecker Markus

Classifications

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D9/041 Primary

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