METHOD OF FABRICATING A TURBOMACHINE COMPRESSOR DRUM

• US 20100172761A1
• Filed: 10/05/2009
• Published: 07/08/2010
• Est. Priority Date: 01/06/2009
• Status: Abandoned Application

• Current Assignee: Snecma (Safran SA)
• Original Assignee: Snecma (Safran SA)
• Inventors: Le Goff, Stevan
• Application Number:
  US12/573,265
• Publication Number:
  US 20100172761A1
• Time in Patent Office: Days
• US Class Current: 416/198.A
• CPC Class Codes: B23K 15/0053 Seam welding
• CPC Class Codes: B23K 20/129 specially adapted for particular articles or workpieces
• CPC Class Codes: B23K 2101/001 Turbines
• CPC Class Codes: B23K 2103/14 Titanium or alloys thereof
• CPC Class Codes: B23K 2103/18 Dissimilar materials
• CPC Class Codes: B23K 2103/26 Alloys of Nickel and Cobalt and Chromium
• CPC Class Codes: B23K 31/02 relating to soldering or welding dip or wave soldering in the manufacture of printed circuits H05K3/34
• CPC Class Codes: B23P 15/006 turbine wheels
• CPC Class Codes: B23P 6/005 using only replacement pieces of a particular form
• CPC Class Codes: F01D 5/005 Repairing methods or devices
• CPC Class Codes: F01D 5/026 Shaft to shaft connections
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F04D 19/02 Multi-stage pumps
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/644 especially adapted for elastic fluid pumps
• CPC Class Codes: F05B 2230/239 Inertia or friction welding
• CPC Class Codes: F05D 2230/232 by welding
• CPC Class Codes: F05D 2230/233 Electron beam welding
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: Y10T 29/49236 Fluid pump or compressor making

Abstract

A method of fabricating a turbomachine compressor drum comprising at least one rotor disk connected to an annular flange on the same axis via a wall of revolution, the method consisting in making said wall of revolution with a local annular extra thickness of material, and then once said wall of revolution has become deformed in use, in cutting through the extra thickness and in removing the wall, in positioning a new wall of revolution to take the place of the removed wall, and in welding the new wall to the drum.

Claims

1. A method of fabricating a turbomachine compressor drum comprising at least two rotor disks on a common axis connected to each other and to an annular flange on the same axis by substantially cylindrical or frustoconical walls of revolution, wherein the method comprises the steps consisting in:

making the wall of revolution interconnecting one of the disks and the annular flange so that it has a local annular extra thickness of material;

then, once said wall of revolution has become deformed in use, cutting through the extra thickness and removing the wall; and

positioning a new wall of revolution to take the place of the removed wall, and welding said new wall to the drum.

2. A method according to claim 1, wherein it consists in cutting the deformed wall in the middle of the local extra thickness, and in replacing it with a new wall that likewise includes a local extra thickness.

3. A method according to claim 1, wherein the new wall is welded to the drum by inertia friction welding or by electron beam welding.

4. A method according to claim 1, wherein, before or after the step of welding the wall, it includes a step consisting in machining the new wall so as to form thereon external annular wipers.

5. A method according to claim 1, wherein, after the welding step, it includes a step consisting in machining the welded zone so that its radial thickness is substantially equal to the radial thickness of the remainder of the wall.

6. A method according to claim 1, wherein the extra thickness is situated between outer annular wipers of the wall of revolution and a rotor disk.

7. A turbomachine compressor drum comprising at least two rotor disks on a common axis connected to each other and to an annular flange on the same axis via substantially cylindrical or frustoconical walls of revolution, wherein the wall of revolution connecting one of the disks to the annular flange includes at least one local annular extra thickness of material, through which the drum can be cut in the event of said wall becoming deformed, in order to remove and replace the wall.

8. A drum according to claim 7, wherein the extra thickness is situated between a rotor disk and outer annular wipers formed on the wall of revolution.

9. A drum according to claim 7, wherein the extra thickness presents a radial thickness lying in the range about 6 mm to 10 mm, with the radial thickness of the remainder of the wall being of the order of about 3 mm.

10. A drum according to claim 7, that is made of titanium.

11. A turbomachine, wherein the turbomachine includes at least one compressor drum according to claim 7.