Method for manufacturing turbomachine member ring supports

Patent metadata

Field	Value
Publication number	US-10773296-B2
Application number	US-201515505967-A
Country	US
Kind code	B2
Filing date	Aug 26, 2015
Priority date	Aug 28, 2014
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

Turbomachine member ring supports extending over sectors of a circle can be constructed from at least one thick flat metal sheet that is curved and welded to form a cylindrical shroud and then formed by pressing into a conical shroud, the outer face of which is machined in order to shape the profile of a mounting rail therein, and the shroud is sectioned in order to divide it into the sectors. The supports have better cohesion and the manufacture thereof is simple and reliable compared with traditional manufacture using bossing of thin metal sheets for joining together the main portions of the supports. The application also relates to a use with stator rings of a turbomachine member that are provided with an abradable lining.

First claim

The invention claimed is:

1. A method of manufacturing ring supports for a member of a turbomachine, said supports extending around angular sectors of a cone, comprising a sealing lining on an inner face of the cone and a mounting rail on an outer face of the cone opposite the inner face, the mounting rail comprising a groove limited by at least one collar protruding in an outer radial direction of the cone, the method comprising:
a) starting from at least one plane metal sheet,
b) bending and welding the at least one metal sheet to form a closed cylindrical shroud,
c) bending the cylindrical shroud in a tooling to form a conical shroud,
d) cutting the conical shroud to divide the conical shroud into said angular sectors,
e) wherein the mounting rail is formed, after said bending of the cylindrical shroud and before the cutting of the conical shroud, by machining the outer face of the support to excavate the groove and carve the at least one collar out of a material of the conical shroud, and
wherein the tooling in which the cylindrical shroud is shaped comprises a circular row of jaws with radial expansion and an outer static ring surrounding the circular row.

2. The manufacturing method according to claim 1 , wherein the bending and shaping are done cold.

3. The manufacturing method according to claim 1 , wherein the cylindrical shroud is shaped in the tooling in two jaw expansion passes, and is turned by an angular step between the jaws between the two expansion passes.

4. The manufacturing method according to claim 1 , wherein said at least one plane metal sheet comprises at least two plates.

5. The method of claim 1 , wherein the conical shroud is a biconical shroud, and the biconical shroud is cut to divide it into two circles of the supports, by removing a center of the biconical shroud, before cutting the two circles of the supports into said angular sectors.

6. The method of claim 1 , wherein the outer face is excavated at the center with discontinuous milling operations.

7. The method of claim 1 , wherein a recess is machined at an end of the inner face, in which a second mounting rail, comprising a central concave part facing an axial direction of the turbomachine, is to be inserted by brazing.

8. The method of claim 1 , wherein the cutting includes cutting in a radial direction to form the angular sectors.

9. The method of claim 1 , wherein the cutting includes separating the angular sectors from each other.

10. A method of manufacturing ring supports for a member of a turbomachine, said supports extending around angular sectors of a cone, said supports comprising a sealing lining on an inner face of the cone and a mounting rail on an outer face of the cone opposite the inner face, the mourning rail comprising a groove extending between two collars protruding in an outer radial direction of the cone, the method comprising:
a) starting from at least one plane metal sheet,
b) bending and welding the at least one metal sheet to form a closed cylindrical shroud,
c) bending the cylindrical shroud in a tooling to form a conical shroud,
d) cutting the conical shroud to divide the conical shroud into said angular sectors,
e) wherein the mounting rail is formed, after said bending of the cylindrical shroud and before said cutting of the conical shroud, by machining the outer face of the support by turning the conical shroud in a lathe to excavate the groove and excavate the outer face at a center, so as to carve the two collars out of a material of the conical shroud.

11. The method of claim 10 , wherein the conical shroud is a biconical shroud, and the biconical shroud is cut to divide the biconical shroud into two circles of the supports, by removing a center of the biconical shroud, before cutting the two circles of the supports into said angular sectors.

12. The method of claim 10 , wherein the outer face is excavated at the center with discontinuous milling operations.

13. The method of claim 10 , wherein a recess is machined at an end of the inner face, in which a second mounting rail, comprising a central concave part facing an axial direction of the turbomachine, is to be inserted by brazing.

14. The method of claim 10 , wherein the bending and shaping are done cold.

15. The method according to claim 10 , wherein said at least one plane metal sheet comprises at least two plates.

16. The method according to claim 10 , wherein the cutting includes cutting in a radial direction to form the angular sectors.

17. The method according to claim 10 , wherein the cutting includes separating the angular sectors from each other.

18. The method of claim 10 , wherein the tooling in which the cylindrical shroud is shaped comprises a circular row of jaws with radial expansion and an outer static ring surrounding the circular row.

19. The method of claim 18 , wherein the cylindrical shroud is shaped in the tooling in two jaw expansion passes, and is turned by an angular step between the jaws between the two expansion passes.

Assignees

• Safran Aircraft Engines

Inventors

• Giardini Bruno
• Charrier Emmanuel Bernard Marie
• Hascoet Frederic
• Spire Didier

Classifications

• F05D2230/25

  by forging · CPC title

• B23P15/00 Primary

  Making specific metal objects by operations not covered by a single other subclass or a group in this subclass · CPC title

• B21K3/00

  Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D9/04

  forming ring or sector · CPC title