TURBOMACHINE ROTOR WHEEL

Abstract

A turbomachine rotor wheel comprises a disk carrying blades having roots engaged and held in an annular recess of the disk, the roots being connected to platforms for co-operating with an annular gasket mounted in an annular groove of the disk, the annular sealing gasket exerting a resilient force on the blade platforms holding the blades in a proper position for operation while the turbomachine is at rest.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

The invention can be better understood and other characteristics, details, and advantages of the invention appear on reading the following description made by way of non-limiting example with reference to the accompanying drawings, in which:

FIG. 1 is a diagrammatic half-view in axial section of a low pressure compressor of a turbomachine, including a prior art rotor wheel;

FIG. 2 is an enlarged view of detail 12 of FIG. 1;

FIG. 3 is a diagrammatic view corresponding to FIG. 2 and showing an embodiment of a rotor wheel of the invention;

FIG. 4 is an enlarged view of detail 14 of FIG. 3; and

FIG. 5 is a diagrammatic view corresponding to FIG. 4 and showing a variant embodiment of the invention.

Claims

1. A rotor wheel, in particular for a turbomachine, the wheel comprising a disk carrying blades having roots engaged and held in an annular recess in an outer peripheral surface of the disk, the roots being connected to platforms surrounding the outside of the outer peripheral surface of the disk and designed to co-operate with an annular sealing gasket mounted in an annular groove of the outer peripheral surface of the disk, wherein, at rest, the annular gasket exerts a resilient force on the blade platforms holding the blades in a proper position for operation, the annular gasket in the free state having an outside diameter greater than that of its mounting groove, and its hardness being determined so as to urge the blades into their proper position for operation and so as to allow the blades to be moved circumferentially in their annular mounting recess.

2. A wheel according to claim 1, wherein the annular gasket is upstream of the blades.

3. A wheel according to claim 1, wherein the annular gasket is downstream of the blades.

4. A wheel according to claim 1, wherein the gasket is symmetrical in shape about its transverse midplane.

5. A wheel according to claim 1, wherein the gasket includes at least one outer peripheral lip for projecting out from the groove when the gasket is mounted in the groove.

6. A wheel according to claim 1, wherein the gasket includes at least one inner peripheral lip for bearing against the bottom of the groove when the gasket is mounted in the groove.

7. A wheel according to claim 1, wherein the gasket has a section that is substantially lozenge-shaped, with the vertices thereof forming radially inner and outer lips of the gasket.

8. A wheel according to claim 1, wherein the gasket has a section that is substantially X-shaped or H-shaped.

9. An annular sealing gasket for a rotor wheel according to claim 1, the gasket having, in the free state, an outside diameter greater than the outside diameter of its annular mounting groove and presenting hardness on the Shore A scale lying in the range 50 to 100.

10. A turbomachine compressor including at least one rotor wheel according to claim 1.

11. A turbomachine such as an airplane turbojet or turboprop, the turbomachine including at least one rotor wheel according to claim 1.