ANISOTROPIC VIBRATION ISOLATION MOUNTING ASSEMBLY

• US 20130186105A1
• Filed: 01/25/2012
• Published: 07/25/2013
• Est. Priority Date: 01/25/2012
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Meacham, Walter Lee, Bridges, Eric, Margolis, Alan
• Granted Patent: US 9,297,438 B2
• Time in Patent Office: Days
• US Class Current: 60/797
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F16C 2360/23 Gas turbine engines in general F02C
• CPC Class Codes: F16C 27/04 Ball or roller bearings, e.g. with resilient rolling bodies
• CPC Class Codes: F16F 15/023 using fluid means
• CPC Class Codes: F16F 15/131 the rotating system comprising two or more gyratory masses
• CPC Class Codes: Y10T 29/49826 Assembling or joining

Abstract

An anisotropic vibration isolation mounting assembly includes at least two three-parameter vibration isolators each having a first end configured for attachment to a rotating member assembly or a rotating member assembly housing and each having a second, opposing end configured for attachment to the rotating member assembly housing where the first end is configured for attachment to the rotating member assembly or to a system interface member where the first member is configured for attachment to the rotating member assembly housing. The at least two three-parameter vibration isolators are tuned anisotropically to minimize the transmission of vibrations during operation of the rotating machine.

Claims

1. An anisotropic vibration isolation mounting assembly for mounting on and providing vibration isolation to a rotating machine, the rotating machine comprising a rotating member assembly, a rotating member assembly housing, and a system interface member, the vibration isolation mounting assembly comprising:

at least two three-parameter vibration isolators each having a first end and a second end, each first end configured for attachment to the rotating member assembly or the rotating member assembly housing, each second end configured for attachment to the rotating member assembly housing when the first end is configured for attachment to the rotating member assembly or to the system interface member when the first member is configured for attachment to the rotating member assembly housing, the at least two three-parameter vibration isolators tuned anisotropically to minimize transmission of vibrations during operation of the rotating machine.

2. The anisotropic vibration isolation mounting assembly of claim 1, comprising at least three three-parameter vibration isolators.

3. The anisotropic vibration is isolation mounting assembly of claim 1, wherein one of the at least two three-parameter vibration isolators has the first end thereof configured for attachment to the rotating member assembly and the second end thereof configured for attachment to the rotating member assembly housing, and wherein another of the at least three-parameter two vibration isolators has the first end thereof configured for attachment to the rotating member assembly housing and the second end thereof configure for attachment to the system interface member.

4. The anisotropic vibration is isolation mounting assembly of claim 1, wherein each of the at least two three-parameter vibration isolators comprises a mounting portion and a strut portion.

5. The anisotropic vibration isolation mounting assembly of claim 1, wherein the at least two three-parameter vibration isolators are mounted at non-equal distances from one another on the rotating machine.

6. The anisotropic vibration isolation mounting assembly of claim 5, wherein one of the at least two three-parameter vibration isolators is configured having vibration damping parameters that differ from at least one other of the at least two three-parameter vibration isolators.

7. The anisotropic vibration isolation mounting assembly of claim 1, wherein one of the at least two three-parameter vibration isolators is configured having vibration damping parameters that differ from at least one other of the at least two three-parameter vibration isolators.

8. The anisotropic vibration isolation mounting assembly of claim 1, wherein the at least two three-parameter vibration isolators are tuned anisotropically to minimize the transmission of low-frequency vibrations during operation of rotating machine.

9. The anisotropic vibration isolation mounting assembly of claim 1, wherein the at least two three-parameter vibration isolators are tuned anisotropically to minimize the transmission of critical speed-induced vibrations during operation of rotating machine.

10. The anisotropic vibration isolation mounting assembly of claim 1, wherein the at least two three-parameter vibration isolators are tuned anisotropically to minimize the transmission of maneuver deflection-induced vibrations during operation of rotating machine.

11. The anisotropic vibration isolation mounting assembly of claim 1, wherein the rotating machine is selected from the group consisting of:

a gas turbine engine, a spacecraft navigational component, a pump, a turbocharger, and a generator.

12. A gas turbine engine assembly configured to be mounted to an airframe, the gas turbine engine assembly comprising:

a gas turbine engine, the gas turbine engine comprising a rotor bearing assembly, a rotor bearing housing, and an engine casing; and

at least three three-parameter vibration isolators each having a first end and a second end, each first end configured for attachment to the rotor bearing assembly or the rotor bearing housing, each second end configured for attachment to the rotor bearing housing when the first end is configured for attachment to the rotor bearing assembly or to the engine casing when the first member is configured for attachment to the rotor bearing housing, the at least three three-parameter vibration isolators tuned anisotropically to minimize transmission of vibrations from the gas turbine engine to the airframe during operation of the gas turbine engine.

13. The gas turbine engine assembly of claim 12, comprising at least four three-parameter vibration isolators.

14. The gas turbine engine assembly of claim 12, wherein each of the at least three three-parameter vibration isolators comprises a strut portion and a mounting portion.

15. The gas turbine engine assembly of claim 14, wherein the strut portion comprises a first spring element in parallel with a damping element and a second spring element, the damping element and the second spring element being in parallel with one another.

16. The gas turbine engine assembly of claim 15, wherein one of the at least three three-parameter vibration isolators is configured having vibration damping parameters that differ from at least one other of the at least three three-parameter vibration isolators.

17. The gas turbine engine assembly of claim 12, wherein the at least three three-parameter vibration isolators are tuned anisotropically to minimize the transmission of one or more of:

low-frequency vibrations, critical speed-induced vibrations, and maneuver deflection-induced vibrations during operation of the gas turbine engine.

18. A method for producing an anisotropic vibration isolation mounting assembly for mounting on and providing vibration isolation to a rotating machine, the rotating machine comprising a rotating member assembly, a rotating member assembly housing, and a system interface member, the method comprising:

providing a rotating machine having operational characteristics;

attaching a plurality of vibration isolators to the rotating machine at different locations on the rotating machine; and

independently and anisotropically tuning each one of the plurality of vibration isolators to impart vibration isolation to the rotating machine based upon the operational characteristics of the rotating machine.

19. The method of claim 18, wherein independently and anisotropically tuning comprises tuning for critical speed-induced vibrations.

20. The method of claim 18, wherein independently and anisotropically tuning comprises tuning for low-frequency vibrations.