Gas turbine engine rotor stack assembly

Patent metadata

Field	Value
Publication number	US-10077663-B2
Application number	US-201113248350-A
Country	US
Kind code	B2
Filing date	Sep 29, 2011
Priority date	Sep 29, 2011
Publication date	Sep 18, 2018
Grant date	Sep 18, 2018

Abstract

A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.

First claim

What is claimed is:

1. A rotor stack assembly for a gas turbine engine, comprising:
a first rotor assembly having a first rim, a first bore and a first web that extends between said first rim and said first bore;
a second rotor assembly aft of said first rotor assembly and having a second rim, a second bore and a second web that extends between said second rim and said second bore, at least one of said first rotor assembly and said second rotor assembly including a rotor blade that extends radially outboard of said first rim or said second rim;
a tie shaft positioned radially inward of said first bore and said second bore, wherein said tie shaft maintains a compressive load on said first rotor assembly and said second rotor assembly, said tie shaft threaded through a forward hub and snapped into an aft hub; and
said compressive load is communicated through a first load path of said first rotor assembly and a second load path of said second rotor assembly, wherein at least one of said first load path and said second load path is radially inboard of said first rim and said second rim.

2. The assembly as recited in claim 1 , comprising a spacer that extends between said first rotor assembly and said second rotor assembly.

3. The assembly as recited in claim 2 , wherein said compressive load is communicated through said spacer.

4. The assembly as recited in claim 1 , wherein at least one of said first rotor assembly and said second rotor assembly is a bladed rotor assembly.

5. The assembly as recited in claim 4 , wherein said bladed rotor assembly includes a blade received in a slot of one of said first rim and said second rim.

6. The assembly as recited in claim 5 , wherein at least one of said first load path and said second load path are radially inboard of said slot.

7. A gas turbine engine, comprising:
a compressor section, a combustor section and a turbine section each disposed about an engine centerline axis;
a rotor stack assembly disposed within at least one of said compressor section and said turbine section, said rotor stack assembly including at least a first rotor assembly and a second rotor assembly downstream from said first rotor assembly;
a tie shaft positioned radially inward of said first rotor assembly and said second rotor assembly and that maintains a compressive load on said first rotor assembly and said second rotor assembly, wherein said compressive load is communicated through said first rotor assembly along a first load path and through said second rotor assembly along a second load path; and
wherein said first rotor assembly includes a first radial gap establishing a first distance between a first rim and said first load path of said first rotor assembly and said second rotor assembly includes a second radial gap establishing a second distance between a second rim and said second load path of said second rotor assembly, wherein said second distance is greater than said first distance.

8. The gas turbine engine as recited in claim 7 , wherein at least one of said first rotor assembly and said second rotor assembly is a bladed rotor assembly.

9. The gas turbine engine as recited in claim 8 , wherein said bladed rotor assembly includes a blade received in a slot of one of said first rim and said second rim.

10. The gas turbine engine as recited in claim 9 , wherein at least one of said first load path and said second load path are radially inboard of said slot.

11. The gas turbine engine as recited in claim 7 , comprising a spacer that extends between said first rotor assembly and said second rotor assembly.

12. The gas turbine engine as recited in claim 11 , wherein said compressive load is communicated through said spacer.

13. The gas turbine engine as recited in claim 7 , wherein said first load path and said second load path are isolated from said first rim and said second rim of said first rotor assembly and said second rotor assembly.

14. The gas turbine engine as recited in claim 7 , comprising a primary gas path that extends between an outer casing and said first rim of said first rotor assembly and said second rim of said second rotor assembly, wherein a second temperature of said primary gas path at said second rim is greater than a first temperature of said primary gas path at said first rim.

15. A method for providing a rotor stack assembly for a gas turbine engine, comprising the steps of:
lowering a load path of a rotor assembly of the rotor stack assembly including establishing a radial gap having a first distance between a rim and the load path of the rotor assembly, wherein the radial gap is greater than a second radial gap of an upstream rotor assembly; and
isolating the rim of the rotor assembly from a primary gas path of the gas turbine engine, the rotor assembly including a rotor blade that extends radially outboard of the rim.

16. The method as recited in claim 15 , wherein the load path is radially inboard from the rim.

17. The method as recited in claim 15 , wherein the step of isolating the rim includes:
inserting the rotor blade into a slot of the rim.

18. The assembly as recited in claim 1 , comprising a first airfoil configured as an integrally bladed airfoil of said first rotor assembly and a second airfoil received within a slot of said second rim of said second rotor assembly.

Assignees

• Malmborg Eric W
• Houston David P
• Midgley James R
• Grelotti Robert A
• Bridges Joseph W
• United Technologies Corp

Inventors

• Malmborg Eric W
• Houston David P
• Midgley James R
• Grelotti Robert A
• Bridges Joseph W

Classifications

• Y10T29/4932

  Turbomachine making · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F01D5/066 Primary

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