MEASUREMENT INSTALLATION FOR BLADE FAILURE TESTING IN A TURBOMACHINE

• US 20140105727A1
• Filed: 10/11/2013
• Published: 04/17/2014
• Est. Priority Date: 10/12/2012
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: ROUSSELIN, Stephane, ADNOT, Jean-Francois, MARCELLIN, Patrick
• Granted Patent: US 9,909,444 B2
• Time in Patent Office: Days
• US Class Current: 415/118
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28

Abstract

Turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of said turbomachine, said device comprising a hollow cylindrical pipe positioned inside one of the rotating shafts of said turbomachine in order to guide at least one wire for transmitting this information, characterized in that said device further comprises a part for attaching said pipe to said rotating shaft.

Claims

1. Turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of said turbomachine, said device comprising a hollow cylindrical pipe positioned inside one of the rotating shafts of said turbomachine in order to guide at least one wire for transmitting this information,

characterized in that said device further comprises a part for attaching said pipe to said rotating shaft.

2. Turbomachine according to claim 1, wherein the attachment part bears a part for guiding the wire towards its ingress into said pipe, said guiding part comprising a region, for gathering the excess lengths of said wire, formed by a wall extending in the axial direction and at least one wall extending in the radial direction.

3. Turbomachine according to claim 1, wherein the disc bearing the fan blades is a disc-ring.

4. Turbomachine according to claim 3, wherein the rotating shaft is a low-pressure shaft (4), said shaft extending axially in the upstream direction until it is below said disc-ring.

5. Turbomachine according to claim 1, wherein said attachment part attaches to said rotating shaft by axially gripping splines which extend radially inside said shaft.

6. Turbomachine according to claim 2, wherein the guiding part extends axially in the upstream direction until it is in line with one of the axial ends of the fan disc.

7. Turbomachine according to claim 6, wherein the guiding part comprises an axial cylindrical portion from which a disc-shaped radial portion extends in the direction of said axial end of the fan disc.

8. Turbomachine according to claim 7, wherein said radial portion extends towards the inside of said cylindrical portion via a radial extension which forms a wall of said region for gathering the excess lengths of wire.

9. Turbomachine according to claim 7, wherein the radial portion of the guiding part comprises holes which allow the wire to pass from one of the faces of said disc to the opposite face.