Vibration damping of a static part using a retaining ring

• US 8,197,189 B2
• Filed: 11/27/2007
• Issued: 06/12/2012
• Est. Priority Date: 11/27/2007
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Bonniere, Philippe, Eleftheriou, Andreas, Theratil, Ignatius, Abate, Aldo
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): ELLIS, RYAN H
• Application Number:
  US11/945,490
• Publication Number:
  US 20090136348A1
• Time in Patent Office: 1,659 Days
• Field of Search: 415/119, 415/206, 415/213.1, 416/190
• US Class Current: 415/119
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F04D 29/162 of a centrifugal flow wheel
• CPC Class Codes: F04D 29/4206 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/668 damping or preventing mechanical vibrations
• CPC Class Codes: F05D 2250/15 spiral
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise

Abstract

A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping.

Claims

1. A gas turbine engine compressor comprising a rotor mounted for rotation about a central axis of the engine, the rotor having a series of circumferentially distributed blades, each of said blades having a tip, a shroud surrounding said rotor and having a radially inwardly facing surface defining a flowpath and with the tip of said blades a tip clearance, the shroud projecting forwardly in a cantilevered fashion from an impeller, and a multi-turn spiral ring mounted to a radially outwardly facing surface of the shroud at a cantilevered forward end thereof, said multi-turn spiral ring being in frictional engagement with said radially outwardly facing surface of said shroud, the friction and relative motion between the multi-turn spiral ring and the shroud provides damping of the vibration deflection induced in the shroud.

2. The gas turbine engine compressor defined in claim 1, wherein the multi-turn spiral wound retaining ring mounted in a channel defined in the radially outwardly facing surface of the shroud.

3. The gas turbine engine compressor defined in claim 1, wherein the multi-turn spiral ring is received in an annular channel having a radially outwardly facing surface and two axially spaced-apart sidewalls, the friction between 1) the multi-turn spiral ring and the radially outwardly facing surface of the annular channel and 2) the multi-turn spiral ring and the axially spaced-apart sidewalls of the annular channel both contributing to the damping of the vibrations in the shroud.

4. The gas turbine engine compressor defined in claim 1, wherein the shroud further has a supported aft end and an intermediate knee defining a bend from axial to radial between said cantilevered forward end and said supported aft end.

5. The gas turbine engine compressor defined in claim 1, wherein said multi-turn spiral ring has a cross-section defined by a radial height and an axial width, and wherein said radial height is greater than said width.

6. The gas turbine engine compressor defined in claim 1, wherein said multi-turn spiral ring has a radial stiffness sufficient to create a relative sliding motion between the multi-turn spiral ring and the shroud in response to vibratory induced deflections of the shroud.

7. The gas turbine engine compressor defined in claim 1, wherein the multi-turn spiral ring has a substantially rectangular cross-section with a plain shroud engaging surface preloaded on the radially outwardly facing surface of the shroud.

8. A vibration damping arrangement comprising a static gas turbine engine part subject to vibrations, a multi-turn spiral wound retaining ring mounted in frictional engagement with the static gas turbine engine part, the multi-turn spiral wound retaining ring being mounted in an annular channel defined in an outer surface of the static gas turbine engine part, each turn of the multi-turn spiral wound retaining ring being in frictional contact with an adjacent turn, the multi-turn spiral wound retaining ring having a radial stiffness sufficient to cause the retaining ring to slip on the static gas turbine engine part in response to vibratory motion of the static engine part, the slip between the adjacent turns of the retaining ring as well as between the retaining ring and the static gas turbine engine part both causing frictional damping of the vibration induced in the static gas turbine engine part.

9. The vibration damping arrangement defined in claim 8, wherein the multi-turn spiral wound retaining ring has a cross-section defined by a height and a width, the height extending in a radial direction, whereas the width extends in an axial direction, and wherein the height is greater than the width.

10. The vibration damping arrangement defined in claim 8, wherein the static gas turbine engine part is a diffuser mounted impeller shroud.

11. A method of damping vibration induced in a static annular shroud, wherein the annular shroud is subject to deflections induced by vibration, the method comprising:

opposing the deflections by externally mounting a retaining ring in frictional engagement with an outer surface of the annular shroud, the retaining ring having a cross-section defined by a height and a width, the height extending in a radial direction, whereas the width extends in an axial direction, the height being greater than the width, the retaining ring having a radial stiffness sufficient to substantially not conform to the shroud deflections, thereby resulting in relative sliding motion between the shroud and the retaining ring, the relative sliding motion providing frictional damping of the vibration.

12. The method defined in claim 11, wherein the annular shroud has a cantilevered end, and wherein the method comprises:

mounting the retaining ring to said cantilevered end.

13. The method defined in claim 11, wherein the retaining ring has multiple adjacent turns, the retaining ring being a multi-turn spiral wound retaining ring, and wherein the method comprises using the friction between adjacent turns to provide additional friction damping.

14. The method defined in claim 11, wherein the retaining ring has a substantially rectangular cross-section with a plain inner circumferential surface, the method comprising preloading the plain inner circumferential surface against a corresponding plain circumferential surface of a channel defined in the outer surface of the annular shroud.

15. A method of damping vibration induced in a static gas turbine engine part, comprising:

providing a multi-turn spiral wound retaining ring, the multi-turn spiral wound retaining ring having at least two turns; and

causing said spiral wound retaining ring to slip on an external surface of the static gas turbine engine part and said at least two turns to slip relative to each other as a reaction to vibration induced in the static gas turbine engine part, the friction between the multi-turn retaining ring and the static gas turbine engine part as well as the friction between the at least two turns of the multi-turn spiral wound retaining ring providing vibration damping.

16. A method as defined in claim 15, wherein the multi-turn retaining ring has a substantially rectangular cross-section defining a plain circumferential surface, the method comprising engaging said plain circumferential surface on a corresponding plain circumferential surface of the static gas turbine engine part.