Turbomachine rotors with thermal regulation

• US 10,161,251 B2
• Filed: 09/11/2015
• Issued: 12/25/2018
• Est. Priority Date: 09/12/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Bintz, Matthew E., Forcier, Matthew P., Hiester, Paul J.
• Primary Examiner(s): Edgar, Richard A
• Assistant Examiner(s): Hunter, Jr., John S
• Application Number:
  US14/851,588
• Publication Number:
  US 20160076378A1
• Time in Patent Office: 1,201 Days
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/06 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 Class Codes: F01D 5/08 Heating, heat-insulating or cooling means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/081 Cooling fluid being directed on the side of the rotor disc or at the roots of the blades F01D5/087 takes precedence
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/584 cooling or heating the machine F04D29/5846, F04D29/5853 take precedence
• CPC Class Codes: F05D 2220/30 in turbines
• CPC Class Codes: F05D 2240/20 Rotors
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling

Abstract

A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.

Claims

1. A turbomachine, comprising

a forward stage including a forward stage rotor disk including a forward stage rotor disk rim, wherein the forward stage rotor disk is disposed radially adjacent to a shaft at a forward stage rotor disk bore;

and

a plurality of intermediate stages in axial sequence, which are aft of the forward stage, each intermediate stage including an intermediate stage rotor disk, wherein the intermediate stage rotor disk includes;

an intermediate stage disk body;

an intermediate stage disk rim connected to a rotor blade disposed on a radially outward portion of the intermediate stage disk body;

an intermediate stage disk bore defined in a radially inward portion of the intermediate stage disk body and disposed radially adjacent to the shaft; and

an aft stage, which is aft of an aftmost intermediate stage, including an aft stage rotor disk having an aft stage rotor disk bore,

wherein each intermediate stage rotor disk has an intermediate stage rotor disk thermal regulation aperture disposed in a radially outward portion of the intermediate stage disk body proximate to a radial rim that is opposite to a stator sealing structure of the turbomachine; and

wherein at least one bleed hole is included in at least one of an aft portion of the forward stage rotor disk rim or a forward portion of the foremost intermediate stage rotor disk rim to allow cool air from the forward stage to pass therethrough, and through the thermal regulation apertures of the plurality of intermediate stage rotor disks, into a cavity between the aftmost intermediate stage and the aft stage and down to the aft stage rotor disk bore to regulate a temperature differential of the intermediate and/or aft stage rotor disk.

2. The turbomachine of claim 1, wherein at least one of the intermediate stage disk bodies have a flange for supporting an anti-vortex tube thereon.

3. The turbomachine of claim 1, wherein the aftmost intermediate stage includes an anti-vortex tube disposed on an aft portion of the aftmost intermediate stage disk body between the aftmost intermediate stage and an aft stage.

4. The turbomachine of claim 1, wherein each intermediate stage includes an anti-vortex tube disposed on an aft portion of the intermediate stage disk body.

5. The turbomachine of claim 4, wherein each anti-vortex tube balances flow between each stage.

6. The turbomachine of claim 1, wherein only the aft stage includes an anti-vortex tube.

7. The turbomachine of claim 1, wherein the intermediate stage rotor disk bore or each intermediate stage rotor disk bore is sealed or metered to only allow certain amounts of flow therethrough.

8. The turbomachine of claim 1, wherein the intermediate stage rotor disk thermal regulation aperture reduces material stress during rotational motion.

9. The turbomachine of claim 1, wherein the intermediate stage rotor disk thermal regulation aperture regulates flow through each intermediate stage rotor disk.

10. The turbomachine of claim 1, wherein each intermediate stage rotor disk body has a plurality of circumferentially spaced intermediate stage rotor disk thermal regulation apertures defined therein.

11. The turbomachine of claim 10, wherein at least two of the plurality of thermal regulation apertures include a different aperture shape.

12. The turbomachine of claim 10, wherein at least two of the plurality of thermal regulation apertures include a different radial position on the disk body.