Turbine ring and turbomachine

Patent metadata

Field	Value
Publication number	US-9963993-B2
Application number	US-201314066121-A
Country	US
Kind code	B2
Filing date	Oct 29, 2013
Priority date	Oct 30, 2012
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

A turbine ring of a turbomachine is described, having a one-piece ring structure which has an outer ring which is continuous in the circumferential direction of the turbine ring and has a fastening section for fastening the turbine ring on a housing section of the turbomachine, an inner ring which is segmented in the circumferential direction and has a plurality of inner ring segments which are mutually displaceable in the circumferential direction for guiding the hot gas and has front sealing segments and rear sealing segments, as seen in the axial direction of the turbine ring, these sealing segments being spaced a distance apart from one another in the axial direction and extending between the inner ring and the outer ring, as well as a turbomachine having such a turbine ring.

First claim

What is claimed is:

1. A turbine ring of a turbomachine having a one-piece ring structure, the turbine ring comprising:
an outer ring continuous in a circumferential direction of the turbine ring and having a fastening section for fastening the turbine ring on a housing section of the turbomachine;
an inner ring segmented in the circumferential direction and having a plurality of inner ring segments mutually displaceable in the circumferential direction for guiding hot gas; and
front sealing segments and rear sealing segments, with respect to an axial direction of the turbine ring, the front and rear sealing segments being spaced a distance apart from one another in the axial direction and extending radially between the inner ring and the outer ring, wherein the front and rear sealing segments are in fluid-tight contact with the inner ring and the outer ring.

2. The turbine ring as recited in claim 1 further comprising at least one radial connector, the inner ring segments each connected to the outer ring at least with the aid of the radial connector.

3. The turbine ring as recited in claim 2 wherein the at least one radial connector is positioned centrally on the inner ring segments in the circumferential direction.

4. The turbine ring as recited in claim 1 wherein neighboring inner ring segments each form an overlap butt joint.

5. The turbine ring as recited in claim 4 further comprising at least one counterholder positioned in the butt joint area of the inner ring segments, the counterholder extending from the outer ring in the direction of the inner ring segments.

6. The turbine ring as recited in claim 5 wherein the at least one counterholder includes two counterholders spaced a distance apart from one another in the axial direction in the overlap butt joint areas.

7. The turbine ring as recited in claim 6 wherein the front and rear sealing segments extend away from the counterholders, and a radial gap is formed between the front and rear sealing segments and the outer ring and the inner ring.

8. The turbine ring as recited in claim 7 wherein the front and rear sealing segments are guided in circumferential grooves of the outer ring and of the inner ring.

9. The turbine ring as recited in claim 8 further comprising at least one radial connector, the inner ring segments each connected to the outer ring at least with the aid of the radial connector; and wherein a circumferential gap is formed between neighboring sealing segments in the area of the at least one radial connector.

10. A turbomachine comprising a turbine ring as recited in claim 1 .

11. The turbine ring as recited in claim 1 wherein the front and rear sealing segments fluidically seal the outer ring to the inner ring in the axial direction.

12. The turbine ring as recited in claim 1 wherein the front and rear sealing segments are curved plate-shaped bodies.

13. The turbine ring as recited in claim 1 wherein the front and rear sealing segments bound axially at least one fluid chamber between the inner ring and the outer ring.

14. A turbine ring of a turbomachine having a one-piece ring structure, the turbine ring comprising:
an outer ring continuous in a circumferential direction of the turbine ring and having a fastening section for fastening the turbine ring on a housing section of the turbomachine;
an inner ring segmented in the circumferential direction and having a plurality of inner ring segments mutually displaceable in the circumferential direction for guiding hot gas; and
front sealing segments and rear sealing segments, with respect to an axial direction of the turbine ring, the front and rear sealing segments being spaced a distance apart from one another in the axial direction and extending radially between the inner ring and the outer ring, wherein the front and rear sealing segments bound axially at least one fluid chamber between the inner ring and the outer ring.

15. The turbine ring as recited in claim 14 further comprising at least one radial connector, the inner ring segments each connected to the outer ring at least with the aid of the radial connector.

16. The turbine ring as recited in claim 14 wherein the front and rear sealing segments fluidically seal the outer ring to the inner ring in the axial direction.

17. A turbine ring of a turbomachine having a one-piece ring structure, the turbine ring comprising:
an outer ring continuous in a circumferential direction of the turbine ring and having a fastening section for fastening the turbine ring on a housing section of the turbomachine;
an inner ring segmented in the circumferential direction and having a plurality of inner ring segments mutually displaceable in the circumferential direction for guiding hot gas; and
front sealing segments and rear sealing segments, with respect to an axial direction of the turbine ring, the front and rear sealing segments being spaced a distance apart from one another in the axial direction and extending radially between the inner ring and the outer ring, wherein the front and rear sealing segments fluidically seal the outer ring to the inner ring in the axial direction.

18. The turbine ring as recited in claim 17 further comprising at least one radial connector, the inner ring segments each connected to the outer ring at least with the aid of the radial connector.

19. A turbine ring of a turbomachine having a one-piece ring structure, the turbine ring comprising:
an outer ring continuous in a circumferential direction of the turbine ring and having a fastening section for fastening the turbine ring on a housing section of the turbomachine;
an inner ring segmented in the circumferential direction and having a plurality of inner ring segments mutually displaceable in the circumferential direction for guiding hot gas;
front sealing segments and rear sealing segments, with respect to an axial direction of the turbine ring, the front and rear sealing segments being spaced a distance apart from one another in the axial direction and extending radially between the inner ring and the outer ring; and
at least one radial connector, the inner ring segments each connected to the outer ring at least with the aid of the radial connector.

Assignees

• MTU Aero Engines AG

Inventors

• Feldmann Manfred

Classifications

• F16J15/445

  with means for adjusting the clearance · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/18 Primary

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/55

  Seals · CPC title