Gas turbine engine rotor balancing

Patent metadata

Field	Value
Publication number	US-11215055-B2
Application number	US-202016789959-A
Country	US
Kind code	B2
Filing date	Feb 13, 2020
Priority date	Feb 9, 2012
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.

First claim

What is claimed is:

1. A gas turbine engine rotor comprising a disc adapted to be mounted for rotation about an axis, a circumferentially extending rim at a periphery of the disc, a circumferential array of blades extending radially outwardly from a radially outer surface of the rim, a circumferential array of selectively formable balance tabs projecting radially inwardly from a radially inner surface of the rim about the axis of rotation of the disc, wherein circumferentially adjacent balance tabs are spaced by stress shielding scallops defined in the radially inner surface of the rim, wherein the balance tabs, prior to balancing, have a pre-established initial weight, wherein material from selected ones of the balance tabs is removed to reduce said pre-established initial weight to a reduced weight in order to balance the gas turbine engine rotor, wherein the balance tabs are free from holes for receiving rotor balancing weight, and wherein the selected ones of the balance tabs have a radial height that is less than the radial height of other ones of the balance tabs.

2. The rotor defined in claim 1 , wherein the selectively formable balance tabs have a tapering profile.

3. The rotor defined in claim 1 , wherein the tabs are machineable.

4. The rotor defined in claim 1 , wherein a number of the tabs equals a number of the blades.

5. The rotor defined in claim 1 , wherein each tab is radially aligned with a corresponding blade.

6. The rotor defined in claim 1 , wherein the tabs have a pre-established initial height, and wherein the material from the tabs is selectably removed to reduce the pre-established initial height to a reduced height in order to balance the gas turbine engine rotor.

7. The rotor defined in claim 1 , wherein a fillet is defined in the radially inner surface of the rim between each one of the circumferentially adjacent balance tabs and neighboring ones of the stress shielding scallops, and wherein the circumferential array of balance tabs is provided in a cantilevered axially end portion of the rim.

Assignees

• Pratt & Whitney Canada

Inventors

• Stone Paul

Classifications

• Y10T29/49336

  Blade making · CPC title

• F05D2260/15

  Load balancing · CPC title

• F05D2230/10

  by removing material · CPC title

• B23P15/02

  turbine or like blades from one piece · CPC title

• F05D2220/32

  in gas turbines · CPC title