Sealing apparatus for a turbomachine, seal-carrier ring element for a sealing apparatus, and turbomachine

Patent metadata

Field	Value
Publication number	US-11499437-B2
Application number	US-202117190984-A
Country	US
Kind code	B2
Filing date	Mar 3, 2021
Priority date	Mar 6, 2020
Publication date	Nov 15, 2022
Grant date	Nov 15, 2022

Abstract

A sealing apparatus for a turbomachine, including a stator vane component, which includes an inner shroud element and a flow-directing element connected to the inner shroud element. The sealing apparatus includes a sealing component, which has a seal-carrier ring element coupled to the stator vane component. The seal-carrier ring element includes at least one ring body element and at least one projection, which is connected in one piece to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing apparatus, and is inserted into at least one opening, which extends through the inner shroud element. Other aspects relate to a seal-carrier ring element for a sealing apparatus, and to a turbomachine which includes at least one sealing apparatus and/or at least one seal-carrier ring element.

First claim

What is claimed is:

1. A sealing apparatus for a turbomachine, the sealing apparatus comprising:
at least one stator vane component including at least one inner shroud element and at least one flow-directing element connected to the at least one inner shroud element; and
at least one seal component having at least one seal-carrier ring element coupled to the at least one stator vane component;
the at least one seal-carrier ring element including at least one ring body element and at least one projection connected in one piece to the at least one ring body element, the at least one projection including a first projection protruding from the at least one ring body element in a radial direction of the sealing apparatus, and being inserted into a first opening of at least one opening of the at least one stator vane component so as to create an interlocking fit between the first projection and the first opening in both the circumferential and the axial direction.

2. The sealing apparatus as recited in claim 1 wherein at least the sealing component is formed without slide blocks.

3. The sealing apparatus as recited in claim 2 wherein the at least one opening leads into at least one cavity of the at least one flow-directing element.

4. The sealing apparatus as recited in claim 3 wherein the at least one projection is spaced apart in the radial direction of the sealing apparatus by at least a cavity bottom of the at least one cavity.

5. The sealing apparatus as recited in claim 1 wherein the at least one projection includes at least three projections.

6. The sealing apparatus as recited in claim 1 wherein the at least one projection includes at least as many projections as a number of the at least one stator vane component, the at least one stator vane component being designed as integrally formed stator vane cluster segments, and the seal-carrier ring element is spoke-centered by the projections radially within the at least one stator vane component.

7. The sealing apparatus as recited in claim 1 wherein wall regions of the sealing apparatus bounding the at least one opening and the at least one projection form at least one interlocking fit preventing a relative movement between the at least one stator vane component and the at least one sealing component in a circumferential direction or in a axial direction of the sealing apparatus.

8. The sealing apparatus as recited in claim 1 wherein the at least one seal-carrier ring element includes at least one sealing flange element connected to the at least one ring body element and, in an axial direction of the sealing apparatus, is spaced apart from the at least one projection, and/or the seal-carrier ring element is designed as an integral, full ring or includes such a ring.

9. The sealing apparatus as recited in claim 8 wherein the at least one stator vane component includes a stator vane flange protruding from the at least one inner shroud element in the radial direction and inserted into an intermediate space extending in an axial direction of the sealing apparatus between the at least one sealing flange element and the at least one projection.

10. The sealing apparatus as recited in claim 9 wherein the at least one stator vane component includes an additional stator flange protruding from the at least one inner shroud element in the radial direction and spaced apart from the stator vane flange in the axial direction forming at least one gap space.

11. The sealing apparatus as recited in claim 10 wherein the at least one projection is inserted into at least one gap space.

12. The sealing apparatus as recited in claim 1 wherein the seal-carrier ring element includes an integral, full ring.

13. A turbomachine comprising at least one sealing apparatus as recited in claim 1 .

14. An aircraft engine comprising the turbomachine as recited in claim 13 .

15. A turbomachine comprising at least one sealing apparatus as recited in claim 1 .

16. An aircraft engine comprising the turbomachine as recited in claim 15 .

17. The sealing apparatus as recited in claim 1 wherein the at least one stator vane component has two axially spaced apart wall regions defining the first opening, the first projection being located between the two axially spaced apart wall regions.

18. The sealing apparatus as recited in claim 17 wherein the first projection contacts the wall regions to limit relative motion in the axial direction.

19. The sealing apparatus as recited in claim 17 wherein the at least one stator vane component has two circumferentially spaced apart wall regions further defining the first opening, the first projection being located between the two circumferentially spaced apart wall regions.

20. The sealing apparatus as recited in claim 19 wherein the first projection contacts the two circumferentially spaced wall regions to limit relative motion in the circumferential direction.

Assignees

• MTU Aero Engines AG

Inventors

• Schmidt-Petersen Julia
• Schlemmer Markus

Classifications

• F01D9/042 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title