Airflow modification patch and method

Patent metadata

Field	Value
Publication number	US-10286996-B2
Application number	US-201314427765-A
Country	US
Kind code	B2
Filing date	Sep 9, 2013
Priority date	Sep 25, 2012
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

An airflow modification patch 14 for reducing aeroacoustic noise generated by an aircraft assembly. The patch has a substrate 14 a and a plurality of airflow disruption elements 14 b.

First claim

The invention claimed is:

1. An aircraft assembly including a patch for reducing noise generated by an airflow negotiating a noise-inducing component of the aircraft assembly, the patch comprising:
a substrate arranged to be attached to the noise-inducing component, or an upstream component, on the aircraft assembly; and
a plurality of airflow disruption elements associated with the substrate and being arranged to induce turbulence in the airflow to reduce the noise generated by the airflow negotiating the noise-inducing component;
wherein one or more of the airflow disruption elements comprises a protrusion which projects from the substrate by at least 0.5 mm and is arranged in use to increase drag.

2. An aircraft assembly according to claim 1 , wherein a plurality of the airflow disruption elements each comprise a protrusion extending from the substrate in a direction generally away from the noise-inducing component.

3. An aircraft assembly according to claim 2 , wherein a first one of the protrusions has a first shape and a second one of the protrusions has a second shape different from the first shape.

4. An aircraft assembly according to claim 2 , wherein one or more of the protrusions project from the substrate by between about 0.5 mm and about 20 mm.

5. An aircraft assembly according to claim 2 , wherein the protrusions collectively have a flow-facing surface area of at least 1 mm 2 .

6. An aircraft assembly according to claim 1 , wherein the substrate has a major face having a surface area of between about 20 mm 2 and about 5 m 2 .

7. An aircraft assembly according to claim 1 , wherein the airflow disruption elements are removably coupled to the substrate.

8. An aircraft assembly according to claim 7 , wherein the substrate includes a plurality of mounting elements arranged to position the airflow disruption elements.

9. An aircraft assembly according to claim 1 , wherein the substrate is arranged to define a regular or irregular array of protrusions.

10. An aircraft assembly according to claim 1 , wherein the disruption elements are arranged to increase drag by at least a factor of 1.1.

11. An aircraft assembly according to claim 1 , wherein an edge of the patch defines a generally serrated edge.

12. An aircraft assembly according to claim 1 comprising an aircraft landing gear, a high lift device or an aircraft panel.

13. An aircraft assembly comprising:
a noise-inducing component; and
a patch for reducing noise generated by an airflow negotiating the noise-inducing component, the patch comprising:
a substrate arranged to be attached to the noise-inducing component, or an upstream component, on the aircraft assembly; and
a plurality of airflow disruption elements associated with the substrate and being arranged to induce turbulence in the airflow to reduce the noise generated by the airflow negotiating the noise-inducing component;
wherein the patch is formed from a woven or sponge-like material.

14. An aircraft landing gear comprising:
a noise-inducing component; and
a patch for reducing noise generated by an airflow negotiating the noise-inducing component, the patch comprising:
a substrate arranged to be attached to the noise-inducing component, or an upstream component, on the aircraft assembly, and
a plurality of airflow disruption elements associated with the substrate and being arranged to induce turbulence in the airflow to reduce the noise generated by the airflow negotiating the noise-inducing component,
wherein one or more of the airflow disruption elements comprises a protrusion which projects from the substrate by at least 0.5 mm and is arranged in use to increase drag.

Assignees

• Safran Landing Systems Uk Ltd

Inventors

• Lacy Stuart
• Cumner Geoff
• Michaelides Peter

Classifications

• Y02T50/162

  Cross-Sectional Technologies · mapped topic

• Y02T50/166

  Cross-Sectional Technologies · mapped topic

• B64C23/06

  by generating vortices · CPC title

• G01H3/00

  Measuring {characteristics of} vibrations by using a detector in a fluid (G01H7/00, G01H9/00, G01H11/00 take precedence) · CPC title

• B64C2025/003

  Means for reducing landing gear noise, or turbulent flow around it, e.g. landing gear doors used as deflectors · CPC title