Vane segment with peripheral securing

Patent metadata

Field	Value
Publication number	US-10428668-B2
Application number	US-201615350147-A
Country	US
Kind code	B2
Filing date	Nov 14, 2016
Priority date	Nov 19, 2015
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

The invention relates to a guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner shroud, a plurality of guide vanes are arranged next to one another in the peripheral direction (UR), the vanes being materially joined with the inner shroud and the outer shroud, in particular joined in one piece. At least two securing ribs are arranged next to one another are formed on the trailing end face for at least one guide vane, wherein an intermediate space delimited by the two securing ribs in the peripheral direction (UR) is formed, this space tapering from radially outside to radially inside.

First claim

What is claimed is:

1. A guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner shroud, a plurality of guide vanes are arranged in the peripheral direction next to one another, the vanes being materially joined with the inner shroud and the outer shroud, joined in one piece, wherein the outer shroud, in an axial longitudinal direction, comprises an axially forward or leading end face element and an axially rear or trailing end face element, such that the outer shroud and the two end faces form a tub-shaped profile in longitudinal section, wherein a reinforcement rib assigned to each guide vane is formed on the outer shroud and extends between the two end faces, wherein at least two securing ribs arranged next to one another are formed on the trailing end face for at least one guide vane,
wherein a gap is delimited by the two securing ribs in the circumferential direction, and
wherein a width of the gap decreases radially from the outside to the inside such that the gap tapers radially from the outside to the inside.

2. The guide vane segment according to claim 1 , wherein the two securing ribs are formed by a first securing rib and a second securing rib, wherein the first securing rib is joined with the reinforcement rib of the inner-lying, assigned guide vane in the peripheral direction.

3. The guide vane segment according to claim 2 , wherein the second securing rib only is formed in the trailing end face.

4. The guide vane segment according to claim 2 , wherein the first securing rib and the second securing rib have rib widths that differ from one another, referred to a width direction running along a peripheral direction tangent, wherein the peripheral direction tangent lies at the same radial distance from the center of the circular segment in each case.

5. The guide vane segment according to claim 4 , wherein the first securing rib or/and the second securing rib have a width increasing from radially outside to radially inside.

6. The guide vane segment according to claim 2 , wherein the first and the second securing ribs have rib heights that differ from one another, measured in the axial direction, at the same radial distance from the center of the circular segment.

7. The guide vane segment according to claim 6 , wherein the first securing rib has a greater rib height and a greater rib width than the second securing rib at the same radial distance from the center of the circular segment.

8. The guide vane segment according to claim 1 , further comprising at least three guide vanes, wherein the two securing ribs, referred to the peripheral direction, are assigned to an inner-lying guide vane, to a second or a third or a fourth guide vane.

9. The guide vane segment according to claim 1 , wherein the two securing ribs are configured in one piece with the trailing end face with the guide vane segment.

10. An aircraft gas turbine including a plurality of guide vane segments according to claim 1 .

11. The aircraft gas turbine according to claim 10 , wherein the plurality of guide vane segments are part of a turbine stage of a low-pressure turbine.

12. The aircraft gas turbine according to claim 11 , wherein a housing element of the low-pressure turbine is configured such that it is joined to the securing ribs of at least one guide vane segment in form-fitting or/and friction-fitting manner so that during operation of the gas turbine, the guide vane segment is held, at least in the peripheral direction, by the connection between housing and securing ribs, wherein the connection between housing and securing ribs is formed by a groove that accommodates the securing ribs.

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Thiele Oliver
• Kislinger Bernd
• Schuette Wilfried
• Hein Manuel

Classifications

• F05D2220/323

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

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2230/21

  by casting · CPC title

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title