Fabrication of dual alloy integrally bladed rotors

• US 4,864,706 A
• Filed: 08/12/1987
• Issued: 09/12/1989
• Est. Priority Date: 08/12/1987
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Jenkel, Steven D.
• Primary Examiner(s): Hall, Carl E.
• Assistant Examiner(s): Cuda, Irene
• Application Number:
  US07/084,369
• Time in Patent Office: 762 Days
• Field of Search: 29/158.8 R, 29/156.8 B, 29/156.8 CF, 29/469.5, 29/428, 29/445, 29/521, 228/193, 416/95, 416/96 R, 148/11.5 N, 148/11.5 P, 148/11.5 Q, 148/11.5 R, 148/11.5 F, 148/11.5 A, 148/11.5 C, 148/11.5 M, 148/12 R, 148/902, 148/DIG. 30
• US Class Current: 29/889.21
• CPC Class Codes: B23K 11/002 specially adapted for particular articles or work
• CPC Class Codes: B23K 13/00 Welding by high-frequency current heating
• CPC Class Codes: B23K 20/00 Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
• CPC Class Codes: B23P 15/006 turbine wheels
• CPC Class Codes: F01D 5/3023 of radial insertion type, e.g. in individual recesses
• CPC Class Codes: F01D 5/3061 by welding, brazing
• CPC Class Codes: Y10T 29/49321 Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
• CPC Class Codes: Y10T 29/49826 Assembling or joining

Abstract

Fabrication methods are described for producing an integrally bladed rotor wherein single crystal blade portions are securely metallurgically bonded to a polycrystalline disk. The polycrystalline disk is fabricated with protruding portions in the location where the blades are to be bonded. The blades are fabricated with a root portion having a cavity adapted to mate with the disk protrusions. The blade and disk are assembled and forced. Localized heating causes localized softening metal flow in the disk protrusion. Bonding occurs as a result of this combination of softening and force.

Claims

1. Method of producing an integrally bladed rotor from a forged disc material and a single crystal blade material with the disc material having a softening temperature which is less than the blade softening temperature including the steps of:

a. forming a cavity in the root portion of at least one single crystal superalloy blade;

b. forming a plurality of protrusions on the periphery of a polycrystalline superalloy disk, said protrusions being shaped to conform to the blade cavities;

c. assembling at least one blade onto at least one disk protrusion;

d. forcing the blade and disk together;

e. locally heating the blade cavity/disk protrusion to an elevated temperature is intermediate between the blade and disc material softening temperatures causing the protrusion to deform against the stronger blade cavity;

f. holding the disk-blade assembly together under conditions of heat and pressure until bonding occurs, and

g. subsequent to bonding removing a portion of the single crystal which defines the cavity,

wherein bonding occurs on a plane tangential to the disc periphery.

2. A method as in claim 1 wherein bonding is performed between 1700°

F.-2200°

F. and an applied pressure of 3-15 ksi.

3. A method as in claim 1 wherein local heating is provided by flowing current between the articles.

4. A method as in claim 1 wherein local heating is provided by induction heating means.

5. A method as in claim 1 wherein bonding is performed under vacuum conditions.

6. Method of joining a single crystal superalloy article having a cavity to a polycrystalline superalloy article having a protrusion which conforms to said cavity, wherein said single crystal article has a softening temperature in excess of the softening temperature of said polycrystalline article including the steps of:

a. assembling the parts so that the protrusion mates with the cavity;

b. applying a force to urge the single crystal and polycrystalline articles together;

c. locally heating the cavity/protrusion to an elevated temperature which is between the softening temperatures of the single crystal and polycrystalline materials thereby causing deformation of the polycrystalline protrusion, with said force and said temperature being chosen so as to cause bonding;

d. subsequent to bonding removing a portion of the single crystal article which defines the cavity.

7. A method as in claim 6 wherein bonding is performed between 1700°

F.-2200°

F. and an applied pressure of 3-15 ksi.

8. A method as in claim 6 wherein bonding is performed under vacuum conditions.

9. Method of joining a single crystal superalloy article containing a cavity to a polycrystalline superalloy article having a matching protrusion, said single crystal having a first softening temperature and said polycrystalline article having a second softening temperature, said first softening temperature exceeding said second softening temperature, including the steps of:

a. assembling said articles so that the protrusion fits into the cavity;

b. heating the cavity and the protrusion to a temperature between said first and said second temperatures while simultaneously forcing said parts together so that said polycrystalline material conforms to and bonds to said single crystal material.

c. subsequent to bonding removing a portion of the single crystal article which defines the cavity.

10. A method as in claim 9 wherein local heating is provided by flowing current between the articles.

11. A method as in claim 9 wherein bonding is performed under vacuum conditions.