Method for friction welding a blade onto a turbine engine rotor disc; corresponding integral blade disc

Patent metadata

Field	Value
Publication number	US-9869189-B2
Application number	US-201314647679-A
Country	US
Kind code	B2
Filing date	Nov 26, 2013
Priority date	Nov 28, 2012
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

A method of friction welding an airfoil ( 32 ) onto a rotor disk of a turbine engine, the disk having at its outer periphery a projecting stub ( 18 ) onto which the airfoil is to be welded, the method comprising a step consisting in mounting chocks ( 24 ) on leading and trailing edges of the stub, the method being characterized in that, before friction welding, the chocks are secured to the stub by welding, and in that during the friction welding operation, the beads of welding ( 28 ) between the chocks and the stub are expelled, at least in part, in seams of material ( 34 ) that form around the connection zone between the airfoil and the stub and that are subsequently to be removed or eliminated, e.g. by machining.

First claim

The invention claimed is:

1. A method of friction welding an airfoil onto a rotor disk of a turbine engine, the disk having at its outer periphery a projecting stub onto which the airfoil is to be welded, the method comprising a step consisting in mounting chocks on leading and trailing edges of the projecting stub, each chock including a recess in which the leading or trailing edge of the projecting stub is received and of a shape that is substantially complementary to the shape of that edge, the method comprising:
before friction welding, the chocks are secured to the projecting stub by welding;
during the friction welding operation, weld beads formed before the friction welding operation between the chocks and the projecting stub are expelled, at least in part, in seams of material that form around the connection zone between the airfoil and the projecting stub and that are subsequently to be removed or eliminated by machining; and
the weld beads of the chocks have a depth or radial dimension relative to the longitudinal axis of the disk that is less than or equal to half the total thickness of material that is consumed during the friction welding, said total thickness being the combined thickness of material that is consumed from the airfoil and from the projecting stub.

2. The method of claim 1 , wherein before friction welding, a weld bead is formed between each chock and the leading or trailing edge of the projecting stub.

3. The method of claim 2 , wherein the weld bead between each chock and the leading or trailing edge of the projecting stub extends continuously along the radially outer peripheral edge of the recess in the chock.

4. The method of claim 1 , wherein the chocks are made of identical material having a main chemical component that is identical to a main chemical component of the projecting stub and of the airfoil.

5. The method of claim 1 , wherein before friction welding, members for protecting the disk are interposed between the outer periphery of the disk and the chocks.

6. The use of the method of claim 1 for fabricating a blisk or for repairing a blisk.

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Mottin Jean-Baptiste
• Vassault Marc Jacky

Classifications

• B23K20/1205 Primary

  using translation movement · CPC title

• B23K2101/001

  Turbines · CPC title

• F05D2240/24

  for turbines · CPC title

• F01D5/3061 Primary

  by welding, brazing · CPC title

• F05D2230/239

  Inertia or friction welding · CPC title