Bladed disk flexible in the lower part of the blades

Patent metadata

Field	Value
Publication number	US-11585229-B2
Application number	US-201916982171-A
Country	US
Kind code	B2
Filing date	Mar 19, 2019
Priority date	Mar 19, 2018
Publication date	Feb 21, 2023
Grant date	Feb 21, 2023

Abstract

The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.

First claim

The invention claimed is:

1. A blisk of a turbomachine, the blisk comprising:
a hub comprising a platform, the platform having an upstream edge, a downstream edge and a radially outer face configured to define an inner flowpath of a gas in the turbomachine,
a plurality of blades, said blades extending radially from the platform and being formed integrally and in one piece with said platform, each blade comprising a root connected to the platform, a leading edge and a trailing edge, wherein a downstream edge of the platform is downstream of the trailing edge of the blades,
a groove formed in at least one of the following portions of the platforms: in an area of the platform that surrounds the leading edge of a blade, in an area of the platform that surrounds the trailing edge of a blade, wherein the groove opens out onto a nearest edge of the platform among the upstream edge and the downstream edge, and
a seal placed in the groove to form an extension of the radially outer face of the platform and ensure a continuity of the inner flowpath.

2. The blisk of claim 1 , wherein the seal is configured to form a seal between the blisk and a stage downstream of the blisk.

3. The blisk of claim 1 , wherein the platform has a radially inner face opposite the radially outer face and the groove opens out into the radially inner face, and wherein the seal comprises an annular shroud configured to bear against the radially inner face of the platform and a protrusion configured to be housed in the groove.

4. The blisk of claim 1 , wherein the groove is a through groove.

5. The blisk of claim 4 , wherein the seal defines a radius of connection of the root of the blade.

6. The blisk of claim 1 , wherein the groove surrounds the trailing edge of the blade.

7. The blisk of claim 1 , wherein the groove extends along the blade over a distance comprised between 5% and 20% of a chord of the blade.

8. The blisk of claim 1 , wherein a stiffness of the seal is less than a stiffness of the platform.

9. The blisk of claim 8 , wherein the stiffness of the seal is at most equal to 50% of the stiffness of the platform.

10. A blisk of a turbomachine, the blisk comprising:
a hub comprising a platform, the platform having an upstream edge, a downstream edge and a radially outer face configured to define an inner flowpath of a gas in the turbomachine,
a plurality of blades, said blades extending radially from the platform and being formed integrally and in one piece with said platform, each blade comprising a root connected to the platform, a leading edge and a trailing edge,
a groove formed in at least one of the following portions of the platforms: in an area of the platform that surrounds the leading edge of a blade, in an area of the platform that surrounds the trailing edge of a blade, wherein the groove opens out onto a nearest edge of the platform among the upstream edge and the downstream edge, and
a seal placed in the groove to form an extension of the radially outer face of the platform and ensure a continuity of the inner flowpath, wherein the seal defines a radius of connection of a root of the blade.

11. The blisk of claim 10 , further comprising additional grooves and additional seals,
wherein each groove is formed in at least one of the following portions of the platforms: in an area of the platform that surrounds the leading edge of a corresponding blade, in an area of the platform that surrounds the trailing edge of the corresponding blade, wherein the groove opens out onto a nearest edge of the platform among the upstream edge and the downstream edge, and
wherein each additional seal is placed in a corresponding groove of the additional grooves to form an extension of the radially outer face of the platform and ensure a continuity of the inner flowpath, wherein each of the additional seals defines a radius of connection of a root of the corresponding blade.

12. The blisk of claim 10 , wherein the groove is a through groove.

13. An assembly comprising:
the blisk of claim 10 ; and
a stage of a low-pressure compressor that extends immediately downstream of the blisk.

14. The blisk of claim 1 , further comprising additional grooves and additional seals,
wherein each groove is formed in at least one of the following portions of the platforms: in an area of the platform that surrounds the leading edge of a corresponding blade, in an area of the platform that surrounds the trailing edge of the corresponding blade, wherein the groove opens out onto a nearest edge of the platform among the upstream edge and the downstream edge, and
wherein each additional seal is placed in a corresponding groove of the additional grooves to form an extension of the radially outer face of the platform and ensure a continuity of the inner flowpath.

15. An assembly comprising:
the blisk of claim 1 ; and
a stage of a low-pressure compressor that extends immediately downstream of the blisk.

Assignees

• Safran Aircraft Engines

Inventors

• Jablonski Laurent
• Comin François Jean
• Joly Philippe Gérard Edmond
• Perrollaz Jean-Marc Claude
• Lafitte Anthony
• Mercier Rémi Roland Robert

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title

• F04D29/321

  for axial flow compressors · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title