Actuator with vibration attenuation using visco elastic materials

Patent metadata

Field	Value
Publication number	US-10787272-B2
Application number	US-201715856761-A
Country	US
Kind code	B2
Filing date	Dec 28, 2017
Priority date	Oct 20, 2017
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

An actuator is provided for an aircraft engine and includes a tubular base layer and a visco-elastic layer adhesively disposed on the tubular base layer.

First claim

What is claimed is:

1. An actuator for an aircraft engine, comprising:
a tubular base layer;
a visco-elastic layer adhesively disposed on the tubular base layer; and
a constrained layer adhered to the visco-elastic layer,
wherein:
the tubular base layer extends between an actuator engine case end and an actuator cowl door end at opposite terminal ends thereof,
the tubular base layer and the constrained layer comprise metallic materials, and
each of the visco-elastic layer and the constrained layer has opposite axial ends respectively displaced inwardly by equal respective distances from the actuator engine case end and the actuator cowl door end.

2. The actuator according to claim 1 , wherein the visco-elastic layer is adhesively disposed on an interior facing surface of the tubular base layer.

3. The actuator according to claim 1 , wherein the tubular base layer and the constrained layer comprise similar metallic materials.

4. The actuator according to claim 1 , wherein the visco-elastic material is selected in accordance with at least a vibration frequency of vibration to which the actuator is exposed.

5. The actuator according to claim 1 , further comprising adhesive which is radially interposed between an interior facing surface of the tubular base layer and an exterior facing surface of the visco-elastic layer.

6. An aircraft engine assembly, comprising:
an engine case;
a cowl door; and
an actuator comprising, at opposite terminal ends thereof, an engine case end coupled to the engine case, and a cowl door end coupled to the cowl door, the actuator comprising:
a tubular base layer;
a visco-elastic layer disposed on the tubular base layer and selected in accordance with at least a vibration frequency of vibration to which the actuator is exposed; and
a constrained layer adhered to an interior facing surface of the visco-elastic layer,
wherein the tubular base layer and the constrained layer comprise metallic materials and each of the visco-elastic layer and the constrained layer has opposite axial ends respectively displaced inwardly by equal respective distances from the engine case end and the cowl door end.

7. The aircraft engine assembly according to claim 6 , wherein the tubular base layer extends between the engine case end and the cowl door end of the opposite terminal ends of the actuator.

8. The aircraft engine assembly according to claim 6 , wherein the visco-elastic layer is adhesively disposed on an interior facing surface of the tubular base layer.

9. The aircraft engine assembly according to claim 6 , wherein the tubular base layer and the constrained layer comprise similar metallic materials.

10. The aircraft engine assembly according to claim 6 , further comprising adhesive interposed between the tubular base layer and the visco-elastic layer.

11. An aircraft engine assembly, comprising:
an engine case;
a cowl door; and
an actuator comprising, at opposite terminal ends thereof, an engine case end, which is configured to be coupled to the engine case, and a cowl door end, which is configured to be coupled to the cowl door, the actuator comprising:
a tubular base layer extending between the engine case end and the cowl door end of the opposite terminal ends of the actuator;
a constrained layer; and
a visco-elastic layer adhesively interposed between an interior facing surface of the tubular base layer and an exterior facing surface of the constrained layer and selected in accordance with at least a vibration frequency of vibration to which the actuator is exposed,
wherein the tubular base layer and the constrained layer comprise metallic materials and each of the visco-elastic layer and the constrained layer has opposite axial ends respectively displaced inwardly by equal respective distances from the engine case end and the cowl door end.

12. The aircraft engine assembly according to claim 11 , wherein the tubular base layer and the constrained layer comprise similar metallic materials.

13. The aircraft engine assembly according to claim 11 , further comprising:
first adhesive radially interposed between the interior facing surface of the tubular base layer and an exterior facing surface of the visco-elastic layer; and
second adhesive radially interposed between an interior facing surface of the visco-elastic layer and the exterior facing surface of the constrained layer.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Vinjanampati Pavan Kumar
• Janakiraman Rajasekaran

Classifications

• F16F7/087

  Elastomeric surface effect dampers · CPC title

• F15B15/22

  for accelerating or decelerating the stroke · CPC title

• F16F7/09

  in dampers of the cylinder-and-piston type · CPC title

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · CPC title

• F16F9/003

  Dampers characterised by having pressure absorbing means other than gas, e.g. sponge rubber · CPC title