System and method for balancing a rotor in an assembled engine

Patent metadata

Field	Value
Publication number	US-10954793-B2
Application number	US-201816014214-A
Country	US
Kind code	B2
Filing date	Jun 21, 2018
Priority date	Jun 21, 2018
Publication date	Mar 23, 2021
Grant date	Mar 23, 2021

Abstract

A balance system for an assembled engine includes a rotor mounted on a shaft for rotation within an engine casing having an inner case and an outer case; and a weight system mounted on the shaft of the rotor and having at least one weight positionable relative to the rotor around a circumference of the shaft; wherein the inner case has an inner access port, the outer case has an outer access port, and the inner access port, the outer access port and the weight system are positioned on the same radial plane of the rotor, whereby the weight system can be accessed through the outer port and the inner port to adjust circumferential position of the at least one weight relative to the rotor.

First claim

What is claimed is:

1. A balance system for an assembled engine, comprising:
a rotor mounted on a shaft for rotation within an engine casing having an inner case and an outer case; and
a weight system mounted on the shaft of the rotor and having at least one weight positionable relative to the rotor around a circumference of the shaft;
wherein the inner case has an inner access port, the outer case has an outer access port, and the inner access port, the outer access port and the weight system are positioned on the same radial plane of the shaft, whereby the weight system can be accessed through the outer port and the inner port to adjust circumferential position of the at least one weight relative to the shaft, and wherein the outer access port is a fuel injector port.

2. The system of claim 1 , wherein the weight system comprises a rail mounted around at least a portion of the circumference of the shaft, and wherein the at least one weight is mounted to the rail and has a lock structure for locking the weight in position relative to the rail, wherein the lock structure can be locked and unlocked through the inner access port and the outer access port.

3. The system of claim 2 , wherein, when the lock structure is unlocked, the at least one weight can be moved along the rail, and when the lock structure is locked, the at least one weight is fixed in place on the rail.

4. The system of claim 1 , wherein the at least one weight can be accessed from outside the engine casing in a straight line through the outer access port and the inner access port.

5. The system of claim 1 , wherein the rotor has a plurality of blades mounted around the shaft, and wherein the weight system is spaced axially from the blades.

6. The system of claim 1 , wherein the engine is a gas turbine engine, and wherein the rotor is a high speed rotor of the gas turbine engine.

7. The system of claim 6 , wherein the rotor is a high pressure compressor of the engine.

8. The system of claim 1 , wherein the engine has a plurality of rotors positioned along an axis of the engine, and wherein the rotor is an intermediate rotor along the axis.

9. The system of claim 1 , wherein at least one of the outer access port and the inner access port is a borescope port.

10. A method for balancing a rotor for an assembled engine, comprising the steps of:
accessing a weight system of a rotor mounted on a shaft for rotation within an engine casing having an inner case and an outer case, the weight system being mounted on the shaft and having at least one weight positionable relative to the rotor around a circumference of the shaft, the inner case having an inner access port, the outer case having an outer access port, and the inner access port, the outer access port and the weight system being positioned on the same radial plane of the rotor; and
changing circumferential position of the at least one weight relative to the shaft, wherein the outer access port is a fuel injector port, and further comprising the step of removing a fuel injector from the fuel injector port to allow access through the fuel injector port.

11. The method of claim 10 , wherein the weight system comprises a rail mounted around at least a portion of the circumference of the shaft, and wherein the at least one weight is mounted to the rail and has a lock structure for locking the weight in position relative to the rail, wherein the lock structure can be locked and unlocked through the inner access port and the outer access port, the method further comprising the steps of:
accessing the lock structure from outside the engine casing, through the outer access port and the inner access port;
unlocking the lock structure;
moving the at least one weight along the rail to a different circumferential position relative to the shaft; and
locking the lock structure.

12. The method of claim 11 , wherein the unlocking step comprises unlocking the lock structure with an implement inserted from outside the engine casing through the outer access port and the inner access port, and wherein the moving step comprises holding the at least one weight in place with the implement while the rotor is rotated so as to move the at least one weight to the different circumferential position.

13. The method of claim 10 , wherein the rotor has a plurality of blades mounted around the shaft, and wherein the weight system is spaced axially from the blades.

14. The method of claim 10 , wherein the engine is a gas turbine engine, and wherein the rotor is a high speed rotor of the gas turbine engine.

15. The method of claim 14 , wherein the rotor is a high pressure compressor of the engine.

16. The method of claim 10 , wherein the engine has a plurality of rotors positioned along an axis of the engine, and wherein the rotor is an intermediate rotor along the axis.

17. The method of claim 10 , wherein the accessing and changing steps are carried out while the rotor is in a use position within the engine casing.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Korn Nathan D

Classifications

• F04D29/662

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

• F16F15/34

  Fastening arrangements therefor · CPC title

• F05D2260/15

  Load balancing · CPC title

• F05D2240/24

  for turbines · CPC title

• F01D5/027 Primary

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