Dual alloy gas turbine engine rotors and methods for the manufacture thereof

Patent metadata

Field	Value
Publication number	US-10294804-B2
Application number	US-201514823787-A
Country	US
Kind code	B2
Filing date	Aug 11, 2015
Priority date	Aug 11, 2015
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

Dual alloy Gas Turbine Engine (GTE) rotors and method for producing GTE rotors are provided. In one embodiment, the method include includes arranging bladed pieces in an annular grouping or ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces. A first or bonding alloy is deposited along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints, which join the bladed pieces in a bonded blade ring. The bonding alloy is preferably selected to have a ductility higher than and a melt point lower than the alloy from which the bladed pieces are produced. After deposition of the first alloy and formation of the alloy-filled joints, a hub disk is inserted into the central opening of the bonded blade ring. The hub disk and blade ring are then bonded utilizing, for example, a Hot Isostatic Pressing process.

First claim

What is claimed is:

1. A method for manufacturing a bladed Gas Turbine Engine (GTE) rotor, the method comprising:
arranging bladed pieces in a ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces;
depositing a first alloy along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints bonding the bladed pieces in a bonded blade ring having a central opening;
inserting a hub disk into the central opening of the bonded blade ring;
positioning metal diaphragms over opposing faces of the hub disk after inserting the hub disk into the central opening of the bonded blade ring:
forming circumferential joints around outer peripheries of the metal diaphragms. the circumferential joints bonding the metal diaphragms to the bonded blade ring and overlapping with the alloy-filled joints; and
bonding the bonded blade ring to the hub disk;
wherein, during the step of depositing, a localized heat input is applied to the first alloy utilizing a computer-controlled deposition tool to form each of the plurality of alloy-filled joints in a single pass or to gradually build-up each of the plurality of alloy-filled joints along the shank-to-shank junctions in accordance with pre-established three dimensional object data; and
wherein the same localized fusion deposition process is utilized to deposit first alloy and to form the circumferential joints around the outer peripheries of the metal diaphragms.

2. The method of claim 1 wherein the plurality of alloy-filled joints are spaced around a circumference of the bonded blade ring.

3. The method of claim 2 wherein the alloy-filled joints are spaced around an inner circumference of the bonded blade ring.

4. The method of claim 3 further comprising maintaining the bladed pieces in the ring formation utilizing tooling while depositing the first alloy along the shank-to-shank junctions, the tooling having a central opening through which the inner circumferential surface is exposed.

5. The method of claim 1 wherein the bladed pieces are produced from a second alloy, and wherein the method further comprises selecting the first alloy to have a ductility higher than the second alloy.

6. The method of claim 5 wherein the second alloy comprises a single crystal alloy.

7. The method of claim 1 wherein, during deposition of the first alloy along the shank-to-shank junctions, local heat input is controlled to heat the first alloy at a site-of-deposition to a predetermined temperature greater than a melt point of the first alloy.

8. The method of claim 7 wherein the heat source is selected from the group consisting of a laser and an arc.

9. The method of claim 8 wherein the first alloy is actively supplied to the site-of-deposition as a powder alloy feed during deposition of the first alloy along the shank-to-shank junctions.

10. The method of claim 8 wherein the first alloy is actively supplied to the site-of-deposition as a wire alloy feed during deposition of the first alloy along the shank-to-shank junctions.

11. The method of claim 7 wherein deposition of the first alloy along the shank-to-shank junctions comprises:
positioning discrete pieces of the first alloy adjacent the shank-to-shank junctions; and
fusing the discrete pieces of the first alloy to the bladed pieces along the shank-to- shank junctions.

12. A bladed Gas Turbine Engine (GTE) rotor, comprising:
a blade ring comprised of a plurality of bladed pieces fabricated from a blade alloy;
a hub disk to which the plurality of bladed pieces are bonded;
alloy-filled joints spaced about an inner circumference of the blade ring and composed of a bonding alloy having a ductility greater and a melt point less than the blade alloy; and
radial slots formed in the blade ring, the radial slots extending through and bisecting the alloyed-filled joints.

13. The dual alloy GTE rotor of claim 12 wherein the plurality of bladed pieces are cast from one of the group consisting of a single crystal and a directionally-solidified superalloy.

14. The method of claim 1 depositing comprises:
rotating the ring formation by a predetermined amount to position one of the shank-to-shank junctions adjacent the computer-controlled deposition tool;
after rotating the ring formation, depositing an alloy-filled joint along the shank-to-shank junction positioned adjacent the computer-controlled deposition tool; and
repeating the steps of rotating and depositing, as needed, to form the alloy-filled joints along all of the shank-to-shank junctions and yield the bonded blade ring.

15. A method for manufacturing a bladed Gas Turbine Engine (GTE) rotor, the method comprising:
arranging bladed pieces in a ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces;
depositing a first alloy along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints bonding the bladed pieces in a bonded blade ring having a central opening;
inserting a hub disk into the central opening of the bonded blade ring;
bonding the bonded blade ring to the hub disk; and
after bonding the bonded blade ring to the hub disk, forming at least one radial slot in the blade ring extending through at least one of the alloyed-filled joints.

Assignees

• Smoke Jason
• Blumer Eric
• Jan David K
• Adams Robbie Joseph
• Kington Harry Lester
• Honeywell Int Inc

Inventors

• Smoke Jason
• Blumer Eric
• Jan David K
• Adams Robbie Joseph
• Kington Harry Lester

Classifications

• F05D2300/518

  Ductility · CPC title

• F05D2230/233

  Electron beam welding · CPC title

• F05D2300/17

  Alloys · CPC title

• F01D5/06

  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 title

• F01D5/3061 Primary

  by welding, brazing · CPC title