Turbomachine case comprising a central part projecting from two lateral portions in a junction region

Patent metadata

Field	Value
Publication number	US-10934872-B2
Application number	US-201816166435-A
Country	US
Kind code	B2
Filing date	Oct 22, 2018
Priority date	Oct 23, 2017
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A support case for a turbomachine ring sector includes an annular body around a longitudinal axis of the case, and a downstream edge for attachment of the ring sector. The downstream edge extends from the body radially towards the inside of the case. The downstream edge extends circumferentially along a junction region between the body and a fixed vanes stage. The junction region includes a central portion and two lateral portions located on each side of the central portion, along a circumferential direction of the case with respect to its longitudinal axis. The central portion projects radially outwards from the case with respect to the lateral portions.

First claim

The invention claimed is:

1. A support case for turbomachine sealing ring sector, comprising:
an annular body which is annular around a longitudinal axis of the support case, wherein the annular body comprises an internal surface and an external surface which is opposite the internal surface, and wherein the internal surface and the external surface extend axially along the longitudinal axis,
a downstream edge configured for attachment of the ring sector, wherein the downstream edge extends from the annular body radially towards an inside of the support case and wherein the downstream edge extends from the annular body circumferentially along a junction region between the annular body and a guide vane assembly,
wherein the junction region comprises a first connection region configured to connect the annular body to the downstream edge, and wherein the junction region comprises a second connection region configured to be fixed to the guide vane assembly,
wherein the first connection region comprises a central portion and two lateral portions which are located on each side of the central portion, along a circumferential direction of the support case about the longitudinal axis of the support case, and
wherein the central portion extends from the external surface by projecting radially relative to the longitudinal axis of the support case outwards from the support case with respect to the lateral portions.

2. The support case according to claim 1 , wherein at least one of the lateral portions comprises a recess in the external surface of the annular body.

3. The support case according to claim 1 , wherein the central portion comprises a projecting portion projecting from the external surface of the annular body.

4. The support case according to claim 1 , further comprising an upstream edge for attachment of the ring sector, wherein the upstream edge extends from the annular body radially towards the inside of the support case, and wherein the upstream edge extends from the annular body circumferentially along the annular body,
wherein the second connection region comprises a downstream attachment edge to fix the support case to the guide vanes assembly, wherein the downstream attachment edge is located downstream from the central portion and from the lateral portions.

5. The support case according to claim 1 , wherein at least one of a maximum projection height of the central portion projecting above at least one of the lateral portions is between 3 mm and 30 mm, a circumferential length of the central portion with respect to a circumferential length of a ring sector is between ⅕ and ⅘, or a circumferential length of at least one lateral portion with respect to the circumferential length of the ring sector is between 1/10 and ⅖.

6. The support case according to claim 1 , wherein the junction region is substantially symmetric about a median longitudinal section plane of the support case.

7. The support case according to claim 1 , wherein the downstream edge comprises a lip which is configured to be in contact with a downstream leg of the ring sector.

8. A turbine ring assembly comprising:
a support case; and
a ring sector that is fixed to the support case,
wherein the ring sector comprises an upstream leg and a downstream leg, wherein the upstream leg is fixed to the upstream edge of the support case and wherein the downstream leg is fixed to the downstream edge of the support case,
wherein the support case comprises:
an annular body which is annular around a longitudinal axis of the support case, wherein the annular body comprises an internal surface and an external surface which is opposite the internal surface, and wherein the internal surface and the external surface extend axially along the longitudinal axis, and
a downstream edge configured for attachment of the ring sector, wherein the downstream edge extends from the annular body radially towards an inside of the support case and wherein the downstream edge extends from the annular body circumferentially along a junction region between the annular body and a guide vane assembly,

wherein the junction region comprises a first connection region configured to connect the annular body to the downstream edge, and wherein the junction region comprises a second connection region configured to be fixed to the guide vane assembly,
wherein the first connection region comprises a central portion and two lateral portions which are located on each side of the central portion along a circumferential direction of the support case about the longitudinal axis of the support case, and
wherein the central portion extends from the external surface by projecting radially relative to the longitudinal axis of the support case outwards from the support case with respect to the lateral portions.

9. The turbine ring assembly according to claim 8 , comprising a plurality of ring sectors adjacent to each other around the circumferential direction and fixed to the support case,
wherein the first connection region comprises one central portion along the circumferential direction for each ring sector, wherein each central portion is circumferentially located between two lateral portions, and
wherein each central portion projects radially outwards from the case with respect to the lateral portions that are adjacent to the each central portion along the circumferential direction.

10. A turbine for turbomachine, comprising the turbine ring assembly according to claim 8 .

11. The support case according to claim 2 , wherein the projecting portion comprises a boss.

12. The support case according to claim 6 , wherein the support case is substantially symmetric about a median plane.

13. The turbine ring assembly according to claim 8 , wherein the ring sector is fixed to the support case by studs.

14. The turbine ring assembly according to claim 8 , wherein the support case is made from a metallic material and wherein the ring sector is made from a ceramic matrix composite material.

15. The turbine according to claim 14 , wherein the turbine is a high pressure turbine.

16. The support case according to claim 1 , wherein the downstream edge extends radially inward from the internal surface of the annular body towards the inside of the support case.

17. The turbine ring assembly according to claim 8 , wherein the downstream edge extends radially inward from the internal surface of the annular body towards the inside of the support case.

Assignees

• Safran Aircraft Engines

Inventors

• Tableau Nicolas Paul
• Congratel Sebastien Serge Francis
• Danis Antoine Claude Michel Etienne
• Judet Maurice Guy
• Quennehen Lucien Henri Jacques

Classifications

• F05D2240/90

  Mounting on supporting structures or systems · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F01D25/243

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

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title