Impeller having spoilers for a turbine engine turbine

Patent metadata

Field	Value
Publication number	US-2016169014-A1
Application number	US-201514965817-A
Country	US
Kind code	A1
Filing date	Dec 10, 2015
Priority date	Dec 11, 2014
Publication date	Jun 16, 2016
Grant date	—

Abstract

The invention relates to a turbine engine impeller, comprising a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc, the root of each vane being connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades, the impeller further comprising two independent annular plates which are fixed to the disc, a first of said plates being mounted upstream of the disc and comprising a transverse annular portion which is supported on an upstream face of the roots of the vanes, and a second of said plates being mounted downstream of the disc and comprising a transverse annular portion which is supported on a downstream face of the roots of the vanes, characterised in that the integrated platform of each vane stops axially, upstream and downstream, to the right of the upstream and downstream transverse faces of the root, in that said transverse annular portion of each of said plates radially covers at least a space separating the integrated platforms and the disc, and bears, between the integrated platforms and the disc, an annular spoiler which is intended to extend in an axial space between the impeller and an adjacent module of the turbine engine without rubbing against an element of said module.

First claim

1 . Turbine engine impeller, comprising a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc, the root of each vane being connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades, the impeller further comprising two independent annular plates which are fixed to the disc, a first of said plates being mounted upstream of the disc and comprising a transverse annular portion which is supported on an upstream face of the roots of the vanes, and a second of said plates being mounted downstream of the disc and comprising a transverse annular portion which is supported on a downstream face of the roots of the vanes, wherein the integrated platform of each vane has no spoiler and stops axially to the right of the upstream and downstream transverse faces of the root, in that said transverse annular portion of each of said plates radially covers at least a space separating the integrated platforms and the disc, and bears, between the integrated platforms and the disc, an annular spoiler which is intended to extend in an axial space between the impeller and an adjacent module of the turbine engine without rubbing against an element of said module.

2 . Impeller according to claim 1 , wherein said annular spoiler of each of said plates has a substantially cylindrical general shape.

3 . Impeller according to claim 1 , wherein the outer radial end of said transverse annular portion of at least one of said plates is axially supported on said integrated platforms and/or is flush with a radially outer surface of said integrated platforms.

4 . Impeller according to claim 1 , wherein the transverse annular portion of at least one of said plates covers the root of each vane over the entire radial dimension thereof.

5 . Impeller according to claim 1 , wherein at least one of the plates comprises a scalloped portion which is shaped so as to cooperate in a form-fitting manner with a complementary scalloped portion of the disc, so as to fix said plate to the disc.

6 . Impeller according to claim 1 , wherein at least one of said plates comprises at least one finger extending substantially axially from the side of the disc, said finger being inserted in a groove for receiving a vane root of the disc or a cavity of the disc, such as a cavity in a tooth of the disc.

7 . Impeller according to claim 6 , wherein said finger is axially inserted under the root of a vane and is designed so as to be able to be radially supported under said root so as to create with the spoiler, during a rotation of the impeller, a torque driving said transverse annular portion towards the roots of the vanes.

8 . Impeller according to claim 6 , wherein said finger is designed so as to be able to be radially and/or circumferentially supported on at least one tooth portion of the disc.

9 . Impeller according to claim 1 , wherein at least one of said plates comprises a radially inner annular flange for fixing to the disc.

10 . Impeller according to claim 1 , wherein at least one of said plates comprises annular knife-edge seals of a labyrinth sealing joint.

11 . Impeller according to claim 10 , wherein said at least one plate is arranged so as to form an airtight wall connecting the integrated platforms to the annular knife-edge seals.

12 . Impeller according to claim 10 , wherein at least one plate comprises a portion bearing the knife-edge seals which is located between the transverse annular portion and a radially inner annular flange for fixing to the disc.

13 . Turbine engine turbine comprising at least one impeller according to claim 1 .

Assignees

• Snecma

Inventors

• Beaujard Jean-Philippe Antoine
• Brault Roland Gilbert Michel
• Nowakowski Nathalie

Classifications

• F01D11/00

  Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) · CPC title

• F01D5/303

  in a circumferential slot · CPC title

• F01D5/3015 Primary

  with side plates · CPC title

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title