Sealing arrangement for a turbomachine, seal carrier element for the sealing arrangement, guide blade element, and turbomachine

Patent metadata

Field	Value
Publication number	US-12584417-B2
Application number	US-202519201295-A
Country	US
Kind code	B2
Filing date	May 7, 2025
Priority date	May 8, 2024
Publication date	Mar 24, 2026
Grant date	Mar 24, 2026

Abstract

A sealing arrangement for a turbomachine, including a seal carrier element, an integral annular body element, and at least three protrusions. Guide blade element includes an opening that points radially inwardly for accommodating a protrusion of seal carrier element for spoke centering, and a radially inwardly extending sealing web. In the operating state, when there is sealing contact, each protrusion is accommodated in respective opening so that it is movable in axial direction A. Either seal carrier element includes a seal carrier web that extends in circumferential direction, with a sealing surface that points toward sealing web and that is offset in the axial direction, or sealing web of guide blade element extending in circumferential direction includes a sealing surface that points toward seal carrier web, and that is offset relative to an axial rear face of opening.

First claim

What is claimed is:

1 . A sealing arrangement for a turbomachine, the sealing arrangement comprising:
a seal carrier element with an inlet coating at a radially inner end; an integral annular body element; and at least three protrusions for spoke centering of the seal carrier element radially within guide blade elements, with at least three respective openings for the at least three protrusions, the seal carrier element being configured so that the spoke centering is achieved via radial guiding of the at least three protrusions in the at least three openings, each protrusion of the at least three protrusions, in each case in an axial direction, having a front face in a flow direction and a rear face in the flow direction, the guide blade element including the opening pointing radially inwardly for accommodating one of the at least three protrusions of the seal carrier element for spoke centering, and including a radially inwardly extending sealing web forming a radially innermost section of the guide blade element, when there is sealing contact between the seal carrier element and the guide blade element, each protrusion being movably accommodated in an axial direction in the respective opening, and the seal carrier element including a seal carrier web extending in a circumferential direction, with a sealing surface pointing toward the sealing web offset relative to axial front faces as well as axial rear faces of the protrusions in the axial direction, or the sealing web extending in the circumferential direction and including a web sealing surface pointing toward the seal carrier web and offset relative to an axial rear face of the opening in the axial direction.

2 . The sealing arrangement as recited in claim 1 wherein the protrusions are guided axially or in the circumferential direction in the openings with play.

3 . The sealing arrangement as recited in claim 2 wherein the protrusions are guided with axial play in the axial direction being greater than play in the circumferential direction.

4 . The sealing arrangement as recited in claim 1 wherein for at least one of the guide blade elements, the sealing web extends in the circumferential direction over a full circumferential length of the guide blade element.

5 . The sealing arrangement as recited in claim 1 wherein the protrusions in the radial guiding have axial play in the opening in the guide blade element so that during operation, the seal carrier element may be pressed against the sealing web in the flow direction.

6 . The sealing arrangement as recited in claim 1 wherein the protrusions in the radial guiding have axial play in the opening in the guide blade element or are axially spaced apart in the opening when the sealing surface and the web sealing surface are in sealing contact.

7 . The sealing arrangement as recited in claim 1 wherein that the sealing arrangement has a sliding block-free design.

8 . The sealing arrangement as recited in claim 1 wherein that the at least one opening opens into at least one cavity of the at least one guide blade element.

9 . The sealing arrangement as recited in claim 8 wherein the at least one protrusion is spaced apart from at least one cavity base of the at least one cavity in a radial direction.

10 . A turbomachine comprising the sealing arrangement as recited in claim 1 .

11 . The turbomachine as recited in claim 10 wherein the turbomachine is designed as an aircraft engine.

12 . A seal carrier element comprising:
an inlet coating at a radially inner end; an integral annular body element; and at least three protrusions for spoke centering of the seal carrier element radially within guide blade elements, which include at least three respective openings for the at least three protrusions, the seal carrier element being configured so that the spoke centering is achieved via radial guiding of the at least three protrusions in the at least three openings, each protrusion of the at least three protrusions, in each case in an axial direction, having a front face in a flow direction and a rear face in the flow direction, and each protrusion being configured, when there is sealing contact between the seal carrier element and the guide blade element, to be accommodated movably in the axial direction in the opening; and a seal carrier web extending in a circumferential direction and including a sealing surface pointing toward the sealing web and offset relative to the axial front faces as well as the axial rear faces of the protrusions in the axial direction.

13 . A guide blade element comprising:
a radially inwardly pointing opening for accommodating one protrusion of at least three protrusions of a seal carrier element for the spoke centering, and including a radially inwardly extending sealing web forming a radially innermost section of the guide blade element, the opening is configured so that, when there is sealing contact between the seal carrier element and the guide blade element, the opening accommodates the protrusion in the opening so that the protrusion is movable in an axial direction, and the sealing web extends in a circumferential direction and includes a sealing surface pointing toward the seal carrier web offset relative to an axial rear face of the opening in the axial direction.

Assignees

• MTU Aero Engines AG

Inventors

• Ostermeir Oskar

Classifications

• F05D2240/59

  Lamellar seals · CPC title

• F05D2300/611

  Coating · CPC title

• F05D2220/323

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

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title