Turbine engine balancing structure and method

Patent metadata

Field	Value
Publication number	US-10544679-B2
Application number	US-201515111364-A
Country	US
Kind code	B2
Filing date	Jan 9, 2015
Priority date	Jan 21, 2014
Publication date	Jan 28, 2020
Grant date	Jan 28, 2020

Abstract

An example method of balancing a shaft includes inserting a balancing insert into one of a plurality of cavities. The plurality of cavities are radially inside an outermost surface of the shaft.

First claim

We claim:

1. A method of balancing a turbine engine shaft, comprising:
inserting a balancing insert into one of a plurality of cavities, the plurality of cavities radially inside an outermost surface of a shaft, the balancing insert configured to rotatably balance the shaft; and
accessing the plurality of cavities through an aftmost end of the shaft, the shaft a turbine engine shaft.

2. The method of claim 1 , further comprising trim balancing a low rotor of a gas turbine engine during the balancing of the shaft.

3. The method of claim 2 , wherein the gas turbine engine is a land-based gas turbine engine.

4. The method of claim 1 , wherein the plurality of cavities are radially outside a central bore of the shaft.

5. The method of claim 1 , further comprising selecting the balancing insert from among a plurality of balancing inserts having varied weights.

6. The method of claim 1 , further comprising holding the balancing insert axially within one cavity of the plurality of cavities using a shaft bore cover.

7. The method of claim 6 , further comprising holding the shaft bore cover axially utilizing a trim ring received within a circumferential groove of the shaft.

8. The method of claim 1 , wherein the plurality of cavities are provided within the shaft.

9. The method of claim 1 , further comprising inserting a cartridge into a bore provided by the shaft, the cartridge providing the plurality of cavities.

10. A gas turbine rotor, comprising:
a balancing insert; and
a shaft of a turbine engine, wherein a plurality of cavities to selectively receive the balancing insert are positioned radially inside an outermost surface of the shaft, wherein the plurality of cavities are radially outside a central bore of the shaft, the balancing insert configured to rotatably balance the shaft; and wherein the plurality of cavities are accessible through an aftmost end of the shaft.

11. The rotor of claim 10 , wherein the shaft is a low rotor shaft of a gas turbine engine.

12. The rotor of claim 11 , wherein the gas turbine engine is a land-based gas turbine engine.

13. The rotor of claim 10 , wherein the balancing insert is one of a plurality of balancing inserts having varied weights.

14. The rotor of claim 10 , further comprising a shaft bore cover holding the balancing insert axially within one cavity of the plurality of cavities.

15. The rotor of claim 10 , wherein the plurality of cavities are distributed annularly about an axis of the shaft.

16. The rotor of claim 14 , further comprising a trim ring received within a circumferential groove of the shaft to hold the shaft bore cover axially.

17. The rotor of claim 10 , further comprising a cartridge providing the plurality of cavities, the cartridge insertable into the central bore provided by the shaft.

18. The rotor of claim 10 , wherein the plurality of cavities each have an aft end that is axially spaced a distance from an aftmost end face of the shaft.

19. The rotor of claim 10 , wherein the balancing insert includes an at least partially threaded aperture.

20. A gas turbine rotor, comprising:
a balancing insert; and
a shaft of a turbine engine, wherein a plurality of cavities to selectively receive the balancing insert are positioned radially inside an outermost surface of the shaft, wherein the plurality of cavities are accessible through an aftmost end of the shaft, the balancing insert configured to rotatably balance the shaft.

Assignees

• United Technologies Corp

Inventors

• Lopez Jesus S
• Borja Mark

Classifications

• F05D2240/61

  Hollow · CPC title

• F16F15/322

  the rotating body being a shaft (F16F15/34, F16F15/36 take precedence) · CPC title

• F04D29/662

  Balancing of rotors (compensating imbalance G01M1/36) · CPC title

• F01D5/027 Primary

  Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36) · CPC title

• G01M1/32

  by adding material to the body to be tested, e.g. by correcting-weights · CPC title