Compressor rotor stack assembly for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10927686-B2
Application number	US-202016811666-A
Country	US
Kind code	B2
Filing date	Mar 6, 2020
Priority date	Jul 14, 2017
Publication date	Feb 23, 2021
Grant date	Feb 23, 2021

Abstract

A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.

First claim

What is claimed is:

1. A compressor assembly comprising:
a compressor section defining a compressor structure; and
a rotor disk assembly of the compressor section comprising:
a plurality of rotor disks, each extending radially from an inner end to an outer end;
a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and the adjacent spacer disposed proximate the outer end of a respective rotor disk, the spacers forming an outer backbone of the compressor structure;
an inner backbone of the compressor structure, the inner backbone comprising a plurality of backbone segments being axially aligned with one another and engaged with one another to define the inner backbone, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from the adjacent rotor disk, each backbone segment of the plurality of backbone segments being disposed proximate the inner end of the respective rotor disk; and
a tie shaft extending axially within the compressor structure proximate the inner end of the plurality of rotor disks and opposite the outer end, the tie shaft being threaded to the compressor structure to axially compress the plurality of rotor disks together.

2. The compressor assembly of claim 1 , wherein the inner backbone is disposed radially between the outer backbone and the tie shaft.

3. The compressor assembly of claim 1 , wherein a one of the plurality of rotor disks has respective axial sides and a distance between the outer backbone and the inner backbone is different for the respective axial sides.

4. The compressor assembly of claim 3 , wherein the inner backbone defines a substantially cylindrical member.

5. The compressor assembly of claim 4 , wherein the distance is larger for a one of the respective sides closer to a last stage of the compressor section.

6. The compressor assembly of claim 3 , wherein the distance is larger for a one of the respective sides closer to a last stage of the compressor section.

7. The compressor assembly of claim 6 , wherein the inner backbone defines a substantially cylindrical member.

8. The compressor assembly of claim 1 , wherein the plurality of rotor disks are part of a high pressure compressor assembly.

9. A compressor assembly comprising:
a compressor section defining a compressor structure; and
a rotor disk assembly of the compressor section comprising:
a plurality of rotor disks, each extending radially from an inner end to an outer end;
a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and the adjacent spacer disposed proximate the outer end of a respective rotor disk, the spacers forming an outer backbone of the compressor structure;
an inner backbone of the compressor structure, the inner backbone comprising a plurality of backbone segments being axially aligned with one another and engaged with one another to define the inner backbone, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from the adjacent rotor disk, each backbone segment of the plurality of backbone segments being disposed proximate the inner end of the respective rotor disk, a one of the plurality of rotor disks has respective axial sides and a distance between the outer backbone and the inner backbone is different for the respective axial sides; and
a tie shaft extending axially within the compressor structure proximate the inner end of the plurality of rotor disks and opposite the outer end, the tie shaft being threaded to the compressor structure to axially compress the plurality of rotor disks together.

10. The compressor assembly of claim 9 , wherein the inner backbone is disposed radially between the outer backbone and the tie shaft.

11. The compressor assembly of claim 9 , wherein the inner backbone defines a substantially cylindrical member.

12. The compressor assembly of claim 11 , wherein the distance is larger for a one of the respective sides closer to a last stage of the compressor section.

13. The compressor assembly of claim 9 , wherein the distance is larger for a one of the respective sides closer to a last stage of the compressor section.

14. The compressor assembly of claim 13 , wherein the inner backbone defines a substantially cylindrical member.

15. A method of assembling a compressor rotor assembly comprising:
arranging a plurality of rotor disks in an axially spaced manner relative to each other, each extending radially from an inner end to an outer end;
engaging a spacer extending from each rotor disk with an adjacent spacer extending from an adjacent rotor disk, the spacers disposed proximate a radially outer end of the rotor disks;
forming an outer backbone of the compressor rotor assembly with the spacers.
engaging a backbone segment extending from each rotor disk with an adjacent backbone segment extending from the adjacent rotor disk to form an inner backbone, the backbone segment disposed proximate a radially inner end of the rotor disks, the backbone segment being axially aligned with one another and engaged with one another; and
axially compressing the spacers and the inner backbone with a tie shaft extending axially along the compressor rotor assembly, radially substantially near the inner end of the plurality of rotor disks opposite the outer end with a positive torque thereby threading the tie shaft to a compressor structure.

16. The method of claim 15 , wherein the inner backbone is disposed radially between the outer backbone and the tie shaft.

17. The method of claim 15 , wherein a one of the plurality of rotor disks has respective axial sides and a distance between the outer backbone and the inner backbone is different for the respective axial sides.

18. The method of claim 17 , wherein the inner backbone defines a substantially cylindrical member.

19. The method of claim 17 , wherein the distance is larger for a one of the respective sides closer to a last stage of the compressor rotor assembly.

20. The method of claim 15 , wherein the plurality of rotor disks are part of a high pressure compressor assembly.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Ditomasso John C

Classifications

• 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

• F01D5/066 Primary

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

• F01D5/06

  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 title

• F01D5/022

  with concentric rows of axial blades · CPC title