Method of making integrally bladed rotor

Patent metadata

Field	Value
Publication number	US-10792771-B2
Application number	US-201715702531-A
Country	US
Kind code	B2
Filing date	Sep 12, 2017
Priority date	Sep 12, 2017
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

Disclosed is a method of making an integrally bladed rotor. According to the method, a rotor disk comprising a radially outer rim surface is provided. A portion of the disk outer rim surface is removed, leaving a protrusion on the rotor disk outer rim surface. The disk with material removed is subjected to thermal processing. A blade comprising an airfoil and a base is positioned such that a base surface is in contact with the protrusion, and heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the protrusion.

First claim

What is claimed is:

1. A method of making an integrally bladed rotor, comprising providing a rotor disk comprising a radially outer rim surface free from blades;
removing a portion of the disk outer rim surface, leaving a protrusion on the rotor disk outer rim surface;
subjecting the disk including said protrusion to thermal processing;
positioning a blade comprising an airfoil and a base such that a base surface is in contact with the thermally processed protrusion; and
applying heat, pressure, and motion between the blade and the disk to friction weld the base surface to the protrusion.

2. The method of claim 1 , further comprising machining the thermally processed disk outer rim surface to a final shape before positioning the blade.

3. The method of claim 1 , wherein the protrusion extends in a direction between a leading edge of the disk outer rim surface to a trailing edge of the disk outer rim surface, and removing a portion of the disk outer rim surface includes removing a portion of the disk outer rim surface material along each side of the extending protrusion.

4. The method of claim 3 , wherein the protrusion is positioned corresponding to a chord of the airfoil where the airfoil meets the disk.

5. The method of claim 1 , wherein the disk comprises a metal alloy, and the thermal processing comprises heating the disk at or above a solution temperature of the metal alloy and quenching the disk to a temperature below the solution temperature of the metal alloy.

6. The method of claim 5 , further comprising holding the disk at or above the solution temperature of the metal alloy before quenching.

7. The method of claim 5 , wherein the quenching reduces temperature at a rate of at least 100° F. per minute.

8. The method of claim 5 , wherein the quenching reduces temperature at a rate of at least 200° F. per minute.

9. The method of claim 5 , wherein the quenching reduces temperature at a rate of at least 300° F. per minute.

10. The method of claim 1 , wherein the thermally processed disk comprises a microstructure comprising primary alpha grains of less than 10 μm.

11. The method of claim 1 , wherein the airfoil is a solid contiguous structure.

12. The method of claim 1 , wherein each of the blade and the disk comprises a titanium alloy.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Machinchick Michael F
• Rettberg Luke H
• Haynes Andrew L
• Stanley Janet M
• Venkatesh Vasisht
• Furrer David Ulrich
• Murdock James R
• Gynther Daniel
• Linden Michael J

Classifications

• B23P15/006 Primary

  turbine wheels · CPC title

• F01D5/3061

  by welding, brazing · CPC title

• F01D5/286

  Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion (F01D5/288 takes precedence) · CPC title

• B23K20/1205

  using translation movement · CPC title

• B21K1/36

  with blades · CPC title