Guide vane ring for a turbomachine

Patent metadata

Field	Value
Publication number	US-10677076-B2
Application number	US-201715497902-A
Country	US
Kind code	B2
Filing date	Apr 26, 2017
Priority date	Apr 28, 2016
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes, each having a vane airfoil and a vane disk, as well as an inner ring having an inner ring surface facing the plurality of guide vanes. Viewed in the direction of a designated primary flow streaming through the turbomachine, the vane disks have a front and a rear surface region. In a nominal and/or a maximum open position of the guide vanes, the front and/or the rear surface region of at least one of the vane disks has an offset from the inner ring surface that is radially disposed (relative to a central axis of the inner ring).

First claim

What is claimed is:

1. A guide vane ring for a turbomachine, the guide vane ring comprising:
a guide vane row having a plurality of pivotably mounted guide vanes, each having a vane airfoil and a vane disk;
an inner ring having an inner ring surface facing the plurality of pivotably mounted guide vanes;
viewed in a direction of a designated primary flow streaming through the turbomachine, the vane disks having a front and a rear surface region, wherein, in a nominal or a maximum open position of the plurality of pivotably mounted guide vanes, the front or rear surface region of at least one of the vane disks has an offset from the inner ring surface radially disposed relative to a central axis of the inner ring;
wherein the one of the front and rear surface regions is raised with respect to a plane of the inner ring surface, and the other of the front and rear surfaces is sunken with respect to the plane of the inner ring surface.

2. The guide vane ring as recited in claim 1 wherein the front surface region of the vane disk in the nominal or the maximum open position of the plurality of pivotably mounted guide vanes is sunken relative to the inner ring surface.

3. The guide vane ring as recited in claim 2 wherein the offset between the front surface region and the inner ring surface has a height 3% to 15% of the diameter of the vane disk or of a channel height.

4. The guide vane ring as recited in claim 1 wherein the rear surface region of the vane disk in the maximum open position of the guide vanes is raised relative to the inner ring surface.

5. The guide vane ring as recited in claim 4 wherein the offset between the rear surface region and the inner ring surface has a height 3% to 15% of the diameter of the vane disk or of a channel height.

6. The guide vane ring as recited in claim 1 wherein in the nominal or maximum open position of the plurality of pivotably mounted guide vanes, the front and the rear surface region have an offset of a same height from the inner ring surface.

7. The guide vane ring as recited in claim 1 wherein at a side facing the vane airfoil thereof, the vane disk having a plane, a convex, a concave or a corrugated surface.

8. An assembly for the guide vane ring as recited in claim 1 , the assembly having the inner ring and at least one guide vane insertable into a recess of the inner ring.

9. A turbomachine comprising the guide vane ring as recited in claim 1 .

10. A guide vane ring for a turbomachine, the guide vane ring comprising:
a guide vane row having a plurality of pivotably mounted guide vanes, each having a vane airfoil and a vane disk;
an inner ring having an inner ring surface facing the plurality of pivotably mounted guide vanes and defining an inner ring surface plane;
viewed in a direction of a designated primary flow streaming through the turbomachine, the vane disks having a surface region defining a surface region plane and a front and a rear surface region, the surface region plane being angled with respect to the inner ring surface plane and crossing the inner ring surface plane so that in a nominal or a maximum open position of the plurality of pivotably mounted guide vanes, the front or rear surface region of at least one of the vane disks has an offset from the inner ring surface radially disposed relative to a central axis of the inner ring.

11. The guide vane ring as recited in claim 10 wherein the front surface region of the vane disk in the nominal or the maximum open position of the plurality of pivotably mounted guide vanes is sunken relative to the inner ring surface.

12. The guide vane ring as recited in claim 11 wherein the offset between the front surface region and the inner ring surface has a height 3% to 15% of the diameter of the vane disk or of a channel height.

13. The guide vane ring as recited in claim 10 wherein the rear surface region of the vane disk in the nominal or the maximum open position of the plurality of pivotably mounted guide vanes is raised relative to the inner ring surface.

14. The guide vane ring as recited in claim 13 wherein the offset between the rear surface region and the inner ring surface has a height 3% to 15% of the diameter of the vane disk or of a channel height.

15. The guide vane ring as recited in claim 10 wherein in the nominal or maximum open position of the plurality of pivotably mounted guide vanes, the front and the rear surface region have an offset of a same height from the inner ring surface.

16. The guide vane ring as recited in claim 10 wherein at a side facing the vane airfoil thereof, the vane disk having a plane, a convex, a concave or a corrugated surface.

17. An assembly for the guide vane ring as recited in claim 10 , the assembly having the inner ring and at least one guide vane insertable into a recess of the inner ring.

18. A turbomachine comprising the guide vane ring as recited in claim 10 .

Assignees

• MTU Aero Engines AG

Inventors

• Wolf Hannes
• Halcoussis Alexander

Classifications

• F01D17/162

  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

• F05D2250/711

  convex · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D9/041 Primary

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

• F05D2220/32

  in gas turbines · CPC title