Gas turbine engine rotor disk balancing

Patent metadata

Field	Value
Publication number	US-2016222784-A1
Application number	US-201514613404-A
Country	US
Kind code	A1
Filing date	Feb 4, 2015
Priority date	Feb 4, 2015
Publication date	Aug 4, 2016
Grant date	—

Abstract

A gas turbine engine rotor disk includes a web that extends inward in a radial direction from a rim to a bore that circumscribes an axis. An annular ridge extends axially from the side of the web. A balancing cut is in the annular ridge that includes a fillet that extends in the radial direction.

First claim

What is claimed is:

1 . A gas turbine engine rotor disk comprising:
a web that extends inward in a radial direction from a rim to a bore that circumscribes an axis; an annular ridge extends axially from side of the web; and a balancing cut in the annular ridge that includes a fillet extending in the radial direction.

2 . The rotor disk according to claim 1 , wherein a circumferential array of blades is supported on the web opposite the bore.

3 . The rotor disk according to claim 2 , wherein the blades, web and bore are integrally formed with one another to provide a unitary, one-piece structure.

4 . The rotor disk according to claim 3 , comprising a spacer extending in an axial direction from the web near the blades, the spacer integrally formed with the web.

5 . The rotor disk according to claim 1 , wherein the side is a forward side.

6 . The rotor disk according to claim 5 , wherein the web includes an aft side opposite the forward side, the aft side includes an annular groove configured to cooperate with a hub that clamps the rotor disk in a multi-disc compressor stack.

7 . The rotor disk according to claim 1 , wherein the annular ridge circumscribes the axis substantially 360°.

8 . The rotor disk according to claim 1 , where the balancing cut has spaced apart lateral fillets provided in a circumferential direction.

9 . The rotor disk according to claim 8 , wherein the side has a generally planar surface, the fillet in the radial direction has spaced apart first and second axial heights relative to the generally planar surface at radial extremities of the balancing cut, the second axial height is arranged at a greater axial distance from the axis than the first axial height, the second axial height greater than the first axial height.

10 . The rotor disk according to claim 8 , wherein the fillet has a radius of at least ten times the first axial height.

11 . The rotor disk according to claim 10 , wherein radius is between fifteen and thirty times the first axial height.

12 . A method of balancing a gas turbine engine rotor disk, the method comprising the steps of:
determining an imbalance of a rotor disk that has a web circumscribing an axis and extending in a radial direction; identifying an area of an annular ridge on a side of the web for material removal to balance the rotor disk; supporting the rotor disk in a fixture; and machining a cut in the annular ridge that includes a fillet in the radial direction, the cut balancing the rotor disk about the axis.

13 . The method according to claim 12 , wherein a circumferential array of blades is supported on the web opposite a bore, wherein the blades, web and bore are integrally formed with one another to provide a unitary, one-piece structure.

14 . The method according to claim 13 , comprising a spacer extending in an axial direction from the web near the blades, the spacer integrally formed with the web.

15 . The method according to claim 14 , wherein the machining step includes articulating a cutting tool along an arcuate path toward the spacer to provide the fillet in the radial direction.

16 . The method according to claim 15 , wherein the cutting tool is a ball-nosed end mill.

17 . The method according to claim 16 , where the balancing cut has spaced apart lateral fillets provided in a circumferential direction.

18 . The method according to claim 17 , wherein the annular ridge circumscribes the axis substantially 360°.

19 . The method according to claim 17 , wherein the side has a generally planar surface, the fillet in the radial direction has spaced apart first and second axial heights relative to the generally planar surface at radial extremities of the balancing cut, the second axial height is arranged at a greater axial distance from the axis than the first axial height, the second axial height greater than the first axial height.

20 . The method according to claim 19 , wherein radius is between fifteen and thirty times the first axial height.

Assignees

• United Technologies Corp

Inventors

• Espinoza Michael

Classifications

• B23C2215/52

  Axial turbine wheels · CPC title

• F01D5/027 Primary

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

• B23C3/00

  Milling particular work; Special milling operations; Machines therefor (milling gear-teeth B23F, {heat assisted machining B23P25/00}) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/24

  for turbines · CPC title