Methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities

Patent metadata

Field	Value
Publication number	US-10040122-B2
Application number	US-201414492302-A
Country	US
Kind code	B2
Filing date	Sep 22, 2014
Priority date	Sep 22, 2014
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

First claim

What is claimed is:

1. A method for manufacturing a Gas Turbine Engine (GTE) rotor, the method comprising:
consolidating a powdered metal body within a Hot Isostatic Pressing (HIP) container utilizing a HIP process to produce a rotor preform in which elongated sacrificial tubes are embedded;
directing a solvent into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolve the elongated sacrificial tubes and create shaped cavities within the rotor preform; and
prior to or after the chemical dissolution of the elongated sacrificial tubes, further processing the rotor preform to produce the GTE rotor;
wherein the method further comprises:
selecting and positioning the elongated sacrificial tubes to twist about a rotational axis of the rotor preform and to converge in a radially inward direction when moving in a fore-aft direction;
filling the solvent inlet channels with a non-compressible material;
sealing the elongated sacrificial tubes to trap the non-compressible material within the solvent inlet channels; and
after sealing the elongated sacrificial tubes and prior to consolidating the powdered metal body, positioning the elongated sacrificial tubes within the HIP container.

2. The method of claim 1 wherein the non-compressible material comprises a powder packing.

3. The method of claim 1 wherein the non-compressible material comprises metal cores occupying the solvent inlet channels, which are solid at room temperature and which have a melt point less than that of the elongated sacrificial tubes, and wherein the method further comprises:
after consolidating the powdered metal body and producing the rotor preform, severing sealed ends of the elongated sacrificial tubes to expose the solvent inlet channels and the metal cores; and
removing the metal cores from the solvent inlet channel by heating the metal cores to a temperature exceeding the melt point, while allowing the metal cores to drain from the solvent inlet channels in a liquefied state.

4. The method of claim 1 further comprising:
after consolidating the powdered metal body and producing the rotor preform, severing sealed ends of the elongated sacrificial tubes to expose the solvent inlet channels and the non-compressible material contained therein; and
removing the non-compressible material from the solvent inlet channels.

5. The method of claim 4 wherein removing comprises directing forced fluid flow into the solvent inlet channels to flush out the non-compressible material.

6. The method of claim 4 wherein the sealed ends of the elongated sacrificial tubes are severed in conjunction with removal of a material from a hub region of the GTE rotor.

7. The method of claim 1 wherein the shaped cavities created by chemical dissolution of the elongated sacrificial tubes are located, at least in substantial part, in a hub region of the GTE rotor.

8. The method of claim 7 wherein the shaped cavities created in the rotor preform by chemical dissolution of the elongated sacrificial tubes comprise at least one of the group consisting of stress distribution tunnels and air flow passages.

9. The method of claim 1 wherein the GTE rotor has a large outer diameter face and a small outer diameter face opposite the large diameter face, as taken along the rotational axis of the GTE rotor; and
wherein the steps of consolidating, directing, and further processing are performed such that the shaped cavities created by the chemical dissolution of the elongated sacrificial cores extend from the large outer diameter face to the small outer diameter face of the GTE rotor.

10. The method of claim 1 wherein the GTE rotor comprises a rotor hub from which a plurality of blades extends; and
wherein the method further comprises sizing and positioning the elongated sacrificial cores such that the chemical dissolution of the elongated sacrificial cores yields stress distribution tunnels, which follow curved paths within regions of the rotor hub located beneath neighboring pairs of the plurality of blades.

Assignees

• Honeywell Int Inc

Inventors

• Chase Deanna Pinar
• Miner Amandine
• Kington Harry Lester
• Martinez Anthony

Classifications

• B23P15/006

  turbine wheels · CPC title

• F01D5/043

  of the axial inlet- radial outlet, or vice versa, type · CPC title

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• B22F3/24

  After-treatment of workpieces or articles {(B22F3/1146 takes precedence)} · CPC title

• B22F2003/247

  Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface · CPC title