Turbomachine component assembly

Patent metadata

Field	Value
Publication number	US-11008946-B2
Application number	US-201916445482-A
Country	US
Kind code	B2
Filing date	Jun 19, 2019
Priority date	Jun 28, 2018
Publication date	May 18, 2021
Grant date	May 18, 2021

Abstract

A sealing assembly for sealing a first sealing bank of a first static component and a second sealing bank of a second static component of an axial turbomachine, the static components axially movable relative to each other, the sealing assembly including the two static components and a sealing element segmented in the circumferential direction, a first end of the sealing element being axially coupled in a groove at the first sealing bank facing an opposite second end bearing axially against the second sealing bank, as well as a stator vane assembly including a casing component of an axial turbomachine, which has at least one casing hook, and further including a stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook which projects from the platform and bears against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air.

First claim

What is claimed is:

1. A sealing assembly for sealing a first sealing bank of a first static component and a second sealing bank of a second static component of an axial turbomachine, the first and second static components being axially movable relative to each other, the sealing assembly being a stator vane assembly comprising:
the first and second static components and a sealing element segmented in a circumferential direction of the turbomachine, the first static component being one of a casing component having at least one casing hook and a stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook projecting from the platform and bearing against the casing hook, the second static component being the other of the casing component and the stator vane component, a first end of the sealing element being axially coupled in a groove at the first sealing bank of the first component, the groove facing an opposite second end of the sealing element, the second end bearing axially against the second sealing bank;
the stator vane hook having at least one through-hole extending radially through the stator vane hook for supply of cooling air.

2. The sealing assembly as recited in claim 1 wherein the second sealing bank has a stop for limiting radial movement of the sealing element.

3. The sealing assembly as recited in claim 1 wherein a groove width of the groove at the first component is no more than three times a wall thickness of the sealing element.

4. The sealing assembly as recited in claim 1 wherein the groove at the first component is formed by a deformation process, by a material-removal process, or by joining two groove legs, or by two groove legs not fixedly joined together.

5. The sealing assembly as recited in claim 1 wherein a centerline of the sealing element forms an average angle of no more than 45° with a radial direction of the turbomachine.

6. The sealing assembly as recited in claim 1 wherein the first sealing bank is disposed radially inwardly or outwardly of the second sealing bank.

7. The sealing assembly as recited in claim 1 wherein a stiffness of the first end of the sealing element and a stiffness of the second end of the sealing element differ by no more than 35%.

8. The sealing assembly as recited in claim 1 wherein first static component is the casing component and the second static components is the stator vane component.

9. The sealing assembly as recited in claim 1 wherein the second static component is the casing component and the first static component is the stator vane component.

10. A stator vane assembly comprising:
a casing component of an axial turbomachine, the casing component having at least one casing hook; and
a stator vane component of the axial turbomachine, the stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook projecting from the platform and bearing against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air, wherein the at least one through-hole extends radially through the stator vane hook.

11. The stator vane assembly as recited in claim 10 further comprising a sealing element segmented in a circumferential direction of the turbomachine, a first end of the sealing element being axially coupled in a groove at a first sealing bank of one of the casing component and the stator vane component, the groove facing an opposite second end of the sealing element, the second end bearing axially against a second sealing bank of another of the casing component or the stator vane component.

12. The stator vane assembly as recited in claim 11 wherein the casing hook has at least one cutout formed by a recess in the end face thereof and at least partially overlapping the through-hole, or wherein the sealing element forms a boundary for the flow of cooling air.

13. A gas turbine comprising at least one turbine or compressor stage having at least one sealing assembly as recited in claim 1 .

14. A gas turbine comprising at least one turbine or compressor stage having at least one stator vane assembly as recited in claim 10 .

15. A method for sealing the first sealing bank of the first static component and the second sealing bank of the second static component of a sealing assembly as recited in claim 1 comprising providing a positive pressure to press the second end of the sealing element against the second sealing bank.

16. A method for sealing the first sealing bank of the first static component and the second sealing bank of the second static component of a stator vane assembly as recited in claim 11 , the method comprising providing a positive pressure to press the second end of the sealing element against the second sealing bank.

17. A stator vane assembly comprising:
a casing component of an axial turbomachine, the casing component having at least one casing hook;
a stator vane component of the axial turbomachine, the stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook projecting from the platform and bearing against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air; and
a sealing element segmented in a circumferential direction of the turbomachine, a first end of the sealing element being axially coupled in a groove at a first sealing bank of one of the casing component and the stator vane component, the groove facing an opposite second end of the sealing element, the second end bearing axially against a second sealing bank of another of the casing component or the stator vane component; wherein the casing hook has at least one cutout formed by a recess in the end face thereof and at least partially overlapping the through-hole, or wherein the sealing element forms a boundary for the flow of cooling air.

Assignees

• MTU Aero Engines AG

Inventors

• Feldmann Manfred
• Sangl Janine
• Kammerer Armin

Classifications

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title