Gas turbine engines with internally stretched tie shafts

Patent metadata

Field	Value
Publication number	US-9896938-B2
Application number	US-201514614904-A
Country	US
Kind code	B2
Filing date	Feb 5, 2015
Priority date	Feb 5, 2015
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A tie shaft for a rotating group of an engine core includes a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end. The tie shaft further includes a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end and a second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end.

First claim

What is claimed is:

1. A tie shaft for a rotating group of an engine core, comprising:
a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end;
a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end; and
a second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end,
wherein the cylindrical body includes at least one set of slots extending from the internal surface proximate to at least one of the first group of internal grooves and the second group of internal grooves.

2. The tie shaft of claim 1 , wherein the first group of internal grooves is a first group of buttress rings, and wherein the second group of internal grooves is a second group of buttress rings.

3. The tie shaft of claim 2 , wherein the first group of buttress rings and the second group of buttress rings are concentric, circumferential rings.

4. The tie shaft of claim 2 , wherein each of the first group of buttress rings includes a first surface that engages a first axial load in a first direction, and wherein each of the second group of buttress rings includes a second surface that engages a second axial load in a second direction.

5. The tie shaft of claim 1 , wherein the first group of internal grooves is configured to engage a first stretch load in a first direction and the second group of internal grooves is configured to engage a second stretch load in a second direction.

6. The tie shaft of claim 1 , wherein the external surface of the cylindrical body is free from axial surfaces configured to engage an axial stretch load.

7. A rotating assembly for a gas turbine engine, comprising:
at least two rotating group components defining a bore; and
a tie shaft extending through the bore and axially retaining the at least two rotating group components during operation of the gas turbine engine, the tie shaft having a cylindrical body with a forward end and an aft end and defining an interior surface,
wherein the tie shaft comprises a first at least one internal groove on the interior surface of the cylindrical body at the forward end and a second at least one internal groove on the interior surface of the cylindrical body at the aft end, wherein the cylindrical body includes at least one set of slots extending from the internal surface proximate to at least one of the first at least one internal groove and the second at least one internal groove.

8. The rotating assembly of claim 7 , wherein the tie shaft is configured to receive a stretch load from a stretch tooling assembly via the first at least one internal groove and the second at least one internal groove.

9. The rotating assembly of claim 8 , wherein the tie shaft is only configured to receive the stretch load from the stretch tooling assembly via the first at least one internal groove and the second at least one internal groove.

10. The rotating group of claim 7 , wherein the at least two rotating group components include at least two compressor rotor assemblies.

11. The rotating group of claim 7 , wherein the at least two rotating group components include at least one compressor rotor assembly and at least one turbine rotor assembly.

12. The rotating group of claim 7 , wherein the gas turbine engine includes a compression section and a turbine section such that the at least one compressor rotor assembly includes a first compressor rotor assembly at a forward-most position in the compression section and the at least one turbine rotor assembly includes a first turbine rotor assembly at an aft-most position in the turbine section, and wherein the forward end of the tie shaft terminates aft of a forward-most point of the first compressor rotor assembly and the aft end of the tie shaft terminates forward of an aft-most portion of the second turbine rotor assembly.

13. The rotating group of claim 7 , wherein the first at least one internal groove comprises a first group of buttress rings, and wherein the second at least one internal groove comprises a second group of buttress rings.

14. The rotating group of claim 13 , wherein the first group of buttress rings and the second group of buttress rings are concentric, circumferential rings.

15. The rotating group of claim 7 , wherein the first at least one internal groove is configured to engage a first stretch load in a first direction and the second at least one internal groove is configured to engage a second stretch load in a second direction.

16. A method for servicing an engine assembly with a rotating group axially retained by a tie shaft, the tie shaft comprising a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end; a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end; and a second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end,
the method comprising the steps of:
inserting a stretch tool assembly through the tie shaft;
exerting an outward axial force on the internal surface of the tie shaft at the forward end and at the aft end to stretch the tie shaft to axially decouple the tie shaft from the rotating group;
wherein the exerting step includes exerting the outward axial force at the forward end via the first group of internal grooves and at the aft end via the second group of internal grooves, and
wherein the inserting step comprises:
inserting a tool main body of the tool assembly through a bore of the tie shaft, the tool assembly further including a first set of jaw members on the tool main body with a first set of circumferential grooves, wherein the tool main body portion is inserted into the bore of the tie shaft with the first set of jaw members in a collapsed position;
expanding the first set of jaw members on the forward tool portion into an expanded position such that the first set of circumferential grooves on the first set of jaw members engage the first group of internal grooves;
inserting an aft tool portion through the bore of the tie shaft, the aft tool portion including a second set of jaw members having a second set of circumferential grooves, wherein the aft tool portion is inserted into the bore of the tie shaft with the second set of jaw members in a collapsed position; and
expanding the second set of jaw members on the aft tool portion into an expanded position such that the second set of circumferential grooves on the second set of jaw members engage a second group of internal grooves; and
removing at least one component of the rotating group from the tie shaft.

Assignees

• Honeywell Int Inc

Inventors

• Tucker Bradley Reed
• Frost Cristopher
• Johnstun Clay
• Obrien Mike

Classifications

• F05D2250/281

  threaded · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D5/025

  Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00) · CPC title

• F05D2230/70

  Disassembly methods · CPC title

• F05D2240/24

  for turbines · CPC title