Dual tierod assembly for a gas turbine engine and method of assembly thereof

Patent metadata

Field	Value
Publication number	US-10823013-B2
Application number	US-201615282547-A
Country	US
Kind code	B2
Filing date	Sep 30, 2016
Priority date	Sep 30, 2016
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A core engine includes a first tierod and a compressor rotor assembly including a plurality of compressor rotor disks arranged in a face to face orientation and spaced along the first tierod. The core engine includes a second tierod and a turbine rotor assembly including a plurality of turbine rotor disks arranged in a face to face orientation and spaced along the second tierod. The compressor rotor assembly is aft of the turbine rotor assembly.

First claim

What is claimed is:

1. A core engine comprising:
a first tierod;
a compressor rotor assembly comprising a plurality of compressor rotor disks arranged in a face to face orientation and extending between inner ends and outer ends along a radial direction of the core engine, the inner ends separated outwardly by a first variable distance apart from the first tierod along the radial direction of the core engine;
a second tierod; and
a turbine rotor assembly comprising a plurality of turbine rotor disks arranged in a face to face orientation and extending between inner ends and outer ends along the radial direction of the core engine, the inner ends separated outwardly by a second distance apart from the second tierod along the radial direction of the core engine, and wherein said compressor rotor assembly is spaced from said turbine rotor assembly along the axial direction;
wherein said first tierod is loaded with a first tension load clamping the plurality of compressor rotor disks together, and wherein said second tierod is loaded with a second tension load clamping the plurality of turbine rotor disks together.

2. The core engine in accordance with claim 1 further comprising an impeller disk coupled to at least one of said first tierod and said second tierod.

3. The core engine in accordance with claim 2 , wherein at least one of said first tierod and said second tierod is coupled to said impeller disk through a threaded connection.

4. The core engine in accordance with claim 2 , wherein said first tierod is coupled to said compressor rotor assembly through a locknut positioned aft of a first stage compressor rotor disk of said plurality of compressor rotor disks.

5. The core engine in accordance with claim 2 , wherein said first tierod is coupled to said impeller disk through a locknut and said first tierod is coupled to said compressor rotor assembly through a threaded connection at a first stage compressor rotor disk of said plurality of compressor rotor disks.

6. The core engine in accordance with claim 2 , wherein said second tierod is coupled to said turbine rotor assembly through a locknut positioned forward of a last stage turbine rotor disk of said plurality of turbine rotor disks.

7. The core engine in accordance with claim 2 , wherein said first tierod is coupled to the impeller disk on a first side of said impeller disk, and wherein said second tierod is coupled to said impeller disk through an extension arm on a second side of said impeller disk.

8. The core engine in accordance with claim 2 , wherein said second tierod is coupled to a last stage turbine rotor disk through a disk extension.

9. The core engine in accordance with claim 1 , wherein said first tierod comprises a first material and said second tierod comprises a second material, the first material is different from the second material.

10. The core engine in accordance with claim 1 , wherein said first tierod comprises a first diameter and said second tierod comprises a second diameter, the first diameter is different from the second diameter.

11. The core engine in accordance with claim 1 , wherein the first tension load is different from the second tension load.

12. A method of assembling a core engine comprising:
coupling a first tierod to a compressor rotor assembly, the compressor rotor assembly includes a plurality of compressor rotor disks arranged in a face to face orientation and extending between inner ends and outer ends along a radial direction of the core engine, the inner ends separated outwardly by a first variable distance apart from the first tierod along the radial direction of the core engine, said first tierod loaded with a first tension load clamping the plurality of compressor rotor disks together;
coupling a second tierod to a turbine rotor assembly, the turbine rotor assembly includes a plurality of turbine rotor disks arranged in a face to face orientation and extending between inner ends and outer ends along the radial direction of the core engine, the inner ends separated outwardly by a second distance apart from the second tierod along the radial direction of the core engine, said second tierod loaded with a second tension load clamping the plurality of turbine rotor disks together; and
positioning the compressor rotor assembly at a location spaced along an axial direction of the core engine from the turbine rotor assembly.

13. The method in accordance with claim 12 further comprising coupling at least one of the first tierod and the second tierod to an impeller disk.

14. The method in accordance with claim 12 further comprising coupling at least one of the first tierod and the second tierod to an impeller disk through a threaded connection.

15. The method in accordance with claim 12 further comprising coupling the second tierod to an impeller disk through a disk extension.

16. The method in accordance with claim 12 , wherein the first tierod is coupled to the compressor rotor assembly through a locknut positioned aft of a first stage compressor rotor disk of the plurality of compressor rotor disks.

17. The method in accordance with claim 12 , wherein the second tierod is coupled to the turbine rotor assembly through a locknut positioned forward of a last stage turbine rotor disk of the plurality of turbine rotor disks.

18. The method in accordance with claim 12 , wherein the first tierod comprises a first material and the second tierod comprises a second material, the first material is different from the second material.

19. The method in accordance with claim 12 , wherein the first tierod comprises a first diameter and the second tierod comprises a second diameter, the first diameter is different from the second diameter.

20. The method in accordance with claim 12 , wherein the first tension load is different from the second tension load.

Assignees

• Gen Electric

Inventors

• Waslo Daniel

Classifications

• F01D5/066 Primary

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F05D2250/311

  the axes being in line · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title