Component joint

Patent metadata

Field	Value
Publication number	US-10731492-B2
Application number	US-201615373130-A
Country	US
Kind code	B2
Filing date	Dec 8, 2016
Priority date	Dec 15, 2015
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A component joint including a turbomachine component ( 10 ) having at least one component flange ( 11 ); a mating turbomachine component ( 20 ) connected thereto and having at least one mating component flange ( 21 ); and at least one seal ( 30 ) to provide a seal against an overpressure (p 2 −p 1 ) on the component side, the at least one seal ( 30 ) having a sealing surface ( 31 ) that engages into a groove ( 12 ) of the turbomachine component ( 10 ), the groove ( 12 ) being disposed on a mating-component-flange-facing side of the component flange ( 11 ) and having a contact surface ( 13 ) for sealingly axially supporting the sealing surface ( 31 ).

First claim

What is claimed is:

1. A component joint comprising:
a turbomachine component having at least one component flange;
a mating turbomachine component connected to the turbomachine component and having at least one mating component flange; and
at least one seal to provide sealing against an overpressure on a side of the turbomachine component, the at least one seal having a sealing surface engaging into a groove of the turbomachine component, the groove being disposed on a mating-component-flange-facing side of the component flange and having a contact surface for axially supporting the sealing surface; wherein the component flange and the mating component flange are connected together by at least one bolt extending through an opening in the seal to limit axial movement of the component flange away from the mating component flange, wherein the at least one bolt extends through through-holes of the component flange and the mating component flange.

2. The component joint as recited in claim 1 wherein the bolt is threaded.

3. The component joint as recited in claim 1 wherein the bolt extends through a sleeve extending through the opening in the seal.

4. The component joint as recited in claim 1 wherein the seal has at least one opening secured radially on a shoulder fixed relative to the turbomachine component.

5. The component joint as recited in claim 4 wherein a radial height of a sealing element portion extending into the groove is no greater than a radial height of the shoulder.

6. The component joint as recited in claim 1 wherein the seal is disposed axially between the at least one component flange and the at least one mating component flange.

7. The component joint as recited in claim 1 wherein the seal has a mating sealing surface for axially bearing against a mating contact surface of the mating turbomachine component.

8. The component joint as recited in claim 7 wherein the contact surface of the groove and the mating contact surface are parallel and at a same axial location.

9. The component joint as recited in claim 1 wherein the seal contains metal.

10. The component joint as recited in claim 1 wherein the seal is plate-shaped.

11. The component joint as recited in claim 1 wherein the seal is straight or curved.

12. The component joint as recited in claim 1 wherein the seal is annular segment-shaped.

13. The component joint as recited in claim 1 wherein the at least one component flange includes a plurality of spaced-apart component flanges or the at least mating component flange includes a plurality of spaced-apart mating component flanges.

14. The component joint as recited in claim 1 further comprising a further seal circumferentially adjacent to the seal and spaced by a radially extending gap.

15. The component joint as recited in claim 1 wherein the sealing surface axially bears against the contact surface under the overpressure on the side.

16. The component joint as recited in claim 1 wherein the turbomachine component is a component for a gas turbine.

17. The component joint as recited in claim 16 wherein the turbomachine component is a component for a compressor or turbine stage or a casing or an aircraft engine.

18. A turbomachine comprising the component joint as recited in claim 1 .

19. A gas turbine comprising the turbomachine as recited in claim 18 .

20. A method for assembling a component joint as recited in claim 1 , comprising the steps of:
inserting the sealing surface of the at least one seal into the groove of the turbomachine component; and
connecting the at least one component flange to the at least one mating component flange.

21. The component joint as recited in claim 7 wherein the seal has a thickness no greater than 1 mm.

22. The component joint as recited in claim 1 further comprising a nut, the bolt being screwed into the nut, and a head of the bolt and the nut limiting the axial movement of the component flange away from the mating component flange.

Assignees

• MTU Aero Engines AG

Inventors

• Kloetzer Alexander
• Feldmann Manfred

Classifications

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F05D2240/57

  Leaf seals · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F16B33/004

  Sealing; Insulation (by means of washers F16B43/001) · CPC title

• F16B37/122

  Threaded inserts, e.g. "rampa bolts" · CPC title