Integrated vibration damper for additively manufactured structure and method

Patent metadata

Field	Value
Publication number	US-2017368608-A1
Application number	US-201515541650-A
Country	US
Kind code	A1
Filing date	Dec 30, 2015
Priority date	Jan 5, 2015
Publication date	Dec 28, 2017
Grant date	—

Abstract

A vibration damper for an additively manufactured structure includes a structure at least partially formed with an additive manufacturing technique. Also included is a damping element embedded within the structure at an internal location of the structure. A method of damping vibration of an additively manufactured component is provided. The method includes additively manufacturing a structure. The method also includes embedding at least one damping element within the structure at an internal location of the structure.

First claim

1 . A vibration damper for an additively manufactured structure comprising:
a structure at least partially formed with an additive manufacturing technique; and a damping element embedded within the structure at an internal location of the structure.

2 . The vibration damper of claim 1 , wherein the damping element comprises loose particles.

3 . The vibration damper of claim 1 , wherein the damping element comprises powder.

4 . The vibration damper of claim 1 , wherein the damping element comprises a resonator.

5 . The vibration damper of claim 4 , wherein the resonator comprises a mass-spring arrangement.

6 . The vibration damper of claim 1 , wherein the damping element comprises at least one thin film layer of fluid.

7 . The vibration damper of claim 1 , wherein the structure comprises a composite material having a host material and damped material integrally formed within the host material.

8 . The vibration damper of claim 1 , wherein the damping element is integrally formed with a base material of the structure.

9 . The vibration damper of claim 1 , wherein the structure is a helicopter component.

10 . The vibration damper of claim 9 , wherein the helicopter component is one of a gear, a transmission casing, a gearbox, and a fuselage structure.

11 . The vibration damper of claim 1 , wherein the additive manufacturing technique is at least one of direct metal laser sintering (DMLS), and electron beam melting (EBM).

12 . The vibration damper of claim 1 , wherein the damping element is loosely disposed within the structure.

13 . The vibration damper of claim 1 , further comprising a plurality of damping elements completely embedded within the structure.

14 . A method of damping vibration of an additively manufactured component comprising:
additively manufacturing a structure; and embedding at least one damping element within the structure at an internal location of the structure.

15 . The method of claim 14 , wherein the damping element comprises at least one of loose particles, a resonator, at least one film layer of fluid, and a damped material integrally formed within a host material of a composite material.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Homma Kenji
• Braunwart Paul R
• Viens Daniel V
• Nardi Aaron T
• Klecka Michael A
• Mendoza Jeffrey Michael

Classifications

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B22F5/10

  of articles with cavities or holes, not otherwise provided for in the preceding subgroups · CPC title

• F16F7/10

  using inertia effect (F16F13/108, F16F13/22, F16F15/10, F16F15/22 take precedence; stabilising vehicle bodies by means of movable masses B62D37/04; protection of buildings against vibrations or shocks by mass dampers E04H9/0215; arrangements or devices for damping mechanical oscillations of power lines H02G7/14) · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B22F7/02 Primary

  of composite layers {(B22F7/002 takes precedence)} · CPC title