Turbomachine comprising a shaft sleeve and associated sleeve tube

Patent metadata

Field	Value
Publication number	US-10267154-B2
Application number	US-201415038732-A
Country	US
Kind code	B2
Filing date	Nov 25, 2014
Priority date	Nov 25, 2013
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

The turbine ( 1 ) has a rotor ( 2 ) with blades ( 4 ) arranged on a periphery of disks ( 5 ) in radial planes ( 3 ), and a tie rod ( 6 ) extending along slots ( 7 ) in the disks. An annular spacer ( 15, 15 ′) fixes a position of the tie rod relative to a center line (M) of the disks, and is arranged in a channel ( 10, 11 ). The spacer has through-openings, which are arranged radially relative to the tie rod or to its center line, and extend coaxially. The channel carries a cooling medium and is limited by a separating pipe ( 13, 14 ) radially outwards. The through-openings serve for flow of the medium.

First claim

The invention claimed is:

1. A turbine engine comprising
compressor stage and a turbine stage, each stage comprising at least one diskrotatably movable about an axis of the turbine engine, and
a tubular shaft sleeve extending around the shaft along the axis of the turbine engine, wherein the sleeve includes at least one tab extending from an outer radial surface of the sleeve and facing the disk of the compressor stage or the turbine stage, the tab ( 40 ) being configured to come into contact with the disk when only the sleeve is in rotation about the axis of the turbine engine.

2. The turbine engine according to claim 1 , wherein the tab comprises a base extending substantially radially from the outer radial surface of the sleeve and a contact portion extending from the base toward a free end of the tab, the contact portion being configured to deform elastically and come into contact with the disk when the sleeve is in rotation about the axis of the turbine engine.

3. The turbine engine according to claim 2 , wherein the contact portion is locally thinned in an area adjoining the base, wherein the contact portion comprises an outer surface extending facing the disk and forming, at the free end of the tab, a first contact area (A) designed to come into contact with the disk over a first range of rotation speeds of the sleeve, and wherein the outer surface of the contact portion comprises a first surface portion defined by the first contact area (A), and a second surface portion extending in the prolongation of the first surface portion and being radially offset toward the disk so as to define a peak, the peak forming a second contact area (B) designed to come into contact with the disk over a second range of rotation speeds of the sleeve.

4. The turbine engine according to claim 3 , wherein the outer surface of the tab comprises a protective coating.

5. The turbine engine according to claim 2 , wherein the contact portion extends substantially tangentially with respect to the sleeve.

6. The turbine engine according to claim 2 , wherein the contact portion extends parallel to the axis of the turbine engine.

7. The turbine engine according to claim 1 , wherein the tab comprises a base extending substantially radially from the outer radial surface of the sleeve, the base being configured to come into contact with the disk when the sleeve is in rotation about the axis and deforms radially with respect to the axis.

8. The turbine engine according to claim 1 , wherein the sleeve includes a first tube of which one end cooperates with one end of a second tube, the tab extending to the end of the first tube from an outer radial surface of the first tube.

9. The turbine engine according to claim 1 , wherein the disk includes a step, the tab of the sleeve being configured to come into contact with the step, when the sleeve is in rotation about the axis.

10. A tube of the shaft sleeve of a turbine engine extending along an axis, wherein the sleeve includes at least one tab extending from an outer radial surface of the tube, and in that the tab is configured to come into contact with a disk of a compressor or turbine stage of a turbine engine, when only the sleeve is in rotation about the axis.

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Judet Maurice Guy
• Alirot Cecile Marie Emilienne
• Bossaert Alexandre Xavier
• Garin Fabrice Marcel Noel
• Gosselin Christian Michel Jacques
• Thomas Axel Sylvain Loic

Classifications

• F05D2220/30

  in turbines · CPC title

• F01D5/02 Primary

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2300/501

  Elasticity · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title