Rotor balance system

• US 4,848,182 A
• Filed: 09/08/1987
• Issued: 07/18/1989
• Est. Priority Date: 09/08/1987
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Novotny, Rudolph J.
• Primary Examiner(s): Lindsey, Rodney M.
• Application Number:
  US07/094,213
• Time in Patent Office: 679 Days
• Field of Search: 74/573 R, 74/572, 74/574, 188/218 XL, 188/218 A, 416/144, 416/500, 415/119, 73/460, 73/469, 73/487, 464/180, 16/1 R, 16/1 C, 418/151, 310/51
• US Class Current: 464/180
• CPC Class Codes: F01D 5/027 Arrangements for balancing for balancing rotating bodies in general F16F15/32; for compensating unbalance G01M1/36
• CPC Class Codes: F16F 15/322 the rotating body being a shaft F16F15/34, F16F15/36 take precedence
• CPC Class Codes: F16F 15/34 Fastening arrangements therefor
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the asssembly balance of the rotor. A snap ring (42) retains the weights within the openings.

Claims

1. A rotor balance system for a bladed gas turbine engine rotor comprising:

an assembled plurality of disks, each carrying a plurality of blades;

a balance ring internally shrink fit to each disk;

said balance ring having excess internal material beyond that required to avoid buckling during the shrink fit;

said balance ring selectively ground for establishing a detail balanced condition of each disk;

a plurality of openings through the outer edge of each balance ring;

a plurality of balance weights within said openings for establishing a balanced condition of the assembled plurality of disks;

a snap ring fit internally in each disk adjacent to said balance ring for retaining said balance weights within said openings;

said disks each having at least one radially extending internal local protrusion in the area of said shrink fit balance ring; and

said protrusion being located within one of said openings, whereby an anti-rotation lock between said balance ring and said disk is provided.

2. A rotor balance system for a bladed gas turbine engine rotor comprising:

an assembled plurality of disks, each carrying a plurality of blades;

a balance ring internally shrink fit to each disk;

said balance ring having excess internal material beyond that required to avoid buckling during the shrink fit;

said balance ring selectively ground for establishing a detail balanced condition of each disk;

a plurality of openings through the outer edge of each balance ring;

a plurality of balance weights within said openings for establishing a balanced condition of the assembled plurality of disks;

a snap ring fit internally in each disk adjacent to said balance ring for retaining said balance weights within said openings;

said disks each having an inner circumferential lip at a first edge of said balance ring, whereby said weights placed within said openings are restrained; and

said disks each having a slight inner circumferential lip at a second edge of said balance ring, whereby said balance ring is restrained with respect to said disk by said lips in addition to the shrink fit.

3. A rotor balance system as in claim 2:

said disks each having at least one radially extending internal local protrusions in the area of said shrink fit balance ring;

said protrusions being located within one of said openings, whereby an anti-rotation lock between said balance ring and said disk is provided; and

said internal protrusion being located only on said slight inner circumferential lip.