Method of balancing a gas turbine engine rotor

Patent metadata

Field	Value
Publication number	US-10570741-B2
Application number	US-201715484425-A
Country	US
Kind code	B2
Filing date	Apr 11, 2017
Priority date	Nov 3, 2014
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

A gas turbine engine rotor including a disc adapted to be mounted for rotation about an axis, the disc including an annular balancing flange integrally connected thereto, the balancing flange having a first radial dimension around a first arc angle and a second radial dimension greater than the first radial dimension around a second arc angle, the second arc angle corresponding to 360 minus the first arc angle, the second arc angle being less than 180 degrees, the balancing flange around the second arc angle defining a protuberance, the protuberance being defined through machining of the balancing flange, the protuberance compensating for an unbalance of the rotor.

First claim

The invention claimed is:

1. A gas turbine engine rotor comprising a disc adapted to be mounted for rotation about an axis, the disc defining a peripheral annular rim and including an annular balancing flange integrally connected thereto, the balancing flange having a first thickness over a first arc angle and a second thickness over a second arc angle, the first and second thicknesses taken in a radial direction relative to the rotor, the second thickness being greater than the first thickness, the second arc angle corresponding to 360 degrees minus the first arc angle, the second arc angle being less than 180 degrees, the balancing flange around the second arc angle defining a protuberance, the protuberance protruding radially outwardly from a remainder of the annular balancing flange and forming part of a radially outward side of the annular balancing flange, the protuberance being defined through machining of the balancing flange, the protuberance compensating for an unbalance of the rotor.

2. The rotor as defined in claim 1 , wherein the disc includes an annular arm extending inwardly from the peripheral annular rim and the balancing flange is integral with the annular arm of the disc such as to form a monolithic piece therewith.

3. The rotor as defined in claim 2 , wherein the rotor is a fan rotor and the annular arm includes connection members configured for engaging a nosecone of the engine.

4. The rotor as defined in claim 2 , wherein the annular arm has a first annular section extending radially inwardly from the peripheral annular rim and a second annular section extending axially forwardly from the first annular section such that the annular arm has an L-shaped cross-section when viewed in a plane coextensive with a longitudinal axis of the rotor.

5. The rotor as defined in claim 1 , wherein the second arc angle is at least 15 degrees.

6. The rotor as defined in claim 1 , wherein the second arc angle is at most 150 degrees.

7. The rotor as defined in claim 1 , wherein the second arc angle is at most 120 degrees.

8. The rotor as defined in claim 1 , wherein the balancing flange and the disc are integral in a monolithic manner.

9. The rotor as defined in claim 4 , wherein the balancing flange forms part of the second annular section of the annular arm.

10. A gas turbine engine rotor comprising a disc adapted to be mounted for rotation about an axis, the disc defining a peripheral annular rim and an annular arm extending inwardly from the peripheral annular rim, the peripheral annular rim having a first annular section extending radially inwardly from the peripheral annular rim and a second annular section extending axially from the first annular section such that the second annular section extends transversally to the first annular section and the second annular section is radially inwardly offset relative to the peripheral annular rim, the second annular section including an annular balancing flange permanently connected thereto, the annular balancing flange defining a protuberance protruding radially from the second annular section toward the peripheral annular rim, the protuberance extending continuously over an arc angle corresponding to less than 180 degrees.

11. The rotor as defined in claim 10 , wherein the annular balancing flange is formed integral with the second annular section such that the annular arm and the annular balancing flange form a monolithic piece.

12. The rotor as defined in claim 10 , wherein a free end of the second annular section includes a plurality of circumferentially spaced apart connection members for connection with a nosecone.

Assignees

• Pratt & Whitney Canada

Inventors

• Stone Paul
• Ivakitch Richard

Classifications

• F01D5/027 Primary

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

• F04D29/321

  for axial flow compressors · CPC title

• F05D2220/32

  in gas turbines · CPC title

• G01M1/36

  by adjusting position of masses built-in the body to be tested · CPC title

• F05D2230/10

  by removing material · CPC title