Noise reduction apparatus, aircraft, and noise reduction method

Patent metadata

Field	Value
Publication number	US-11577823-B2
Application number	US-201916976020-A
Country	US
Kind code	B2
Filing date	Jan 23, 2019
Priority date	Feb 26, 2018
Publication date	Feb 14, 2023
Grant date	Feb 14, 2023

Abstract

A noise reduction apparatus, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction are provided. The noise reduction apparatus 1 includes a porous plate 2 disposed to face a fluid flow, the porous plate 2 including a bend region 5 bent toward an upstream side of the fluid flow. The bend region 5 is provided at the end portion 6 of the porous plate 2, and has a concave R-shape on an upstream side of the fluid flow.

First claim

The invention claimed is:

1. A noise reduction apparatus reducing a noise generated by a fluid flow flowing from an upstream side of an object to a downstream side of the object, the noise reduction apparatus comprising:
a porous plate disposed at the upstream side, the porous plate facing the object, and the porous plate including a flat region and a bend region bent toward the upstream side,
wherein the bend region is formed by bending an end portion of the porous plate toward the upstream side,
wherein the end portion of the porous plate comprises a plurality of pores located at the upstream side and facing in a direction toward an outside of the object, and
wherein the porous plate decreases a velocity of the fluid flow at the downstream side, thereby reducing the noise generated by the fluid flow.

2. The noise reduction apparatus according to claim 1 , wherein the bend region has a concave shape on the upstream side.

3. The noise reduction apparatus according to claim 1 , wherein the porous plate is disposed to cover a front side of a main landing gear inter-wheel section of an aircraft.

4. The noise reduction apparatus according to claim 1 , wherein the porous plate is disposed to cover a front side of a structural member of a landing gear of an aircraft.

5. The noise reduction apparatus according to claim 1 , wherein the porous plate is disposed along a front edge of a landing gear bay of an aircraft, and the bend region is provided on a distal end side.

6. The noise reduction apparatus according to claim 1 , wherein a width of the flat region is larger than a largest width of the object.

7. An aircraft, comprising:
a porous plate disposed to cover an object of the aircraft or to be disposed along the object of the aircraft, wherein the object is a front side of a main landing gear inter-wheel section, a front side of a structural member of a landing gear, or a front edge of a landing gear bay,
wherein the porous plate reduces a noise generated by a fluid flow flowing from an upstream side of the object to a downstream side of the object,
wherein the porous plate faces the object,
wherein the porous plate includes a flat region and a bend region bent toward the upstream side,
wherein the bend region is formed by bending an end portion of the porous plate toward the upstream side,
wherein the end portion of the porous plate comprises a plurality of pores located at the upstream side and facing in a direction toward an outside of the object, and
wherein the porous plate decreases a velocity of the fluid flow at the downstream side, thereby reducing the noise generated by the fluid flow.

8. The aircraft according to claim 7 , wherein a width of the flat region is larger than a largest width of the object.

9. A noise reduction method for reducing a noise generated by a fluid flow flowing from an upstream side of an object to a downstream side of the object, the method comprising:
disposing a porous plate on the upstream side of the object, the porous plate facing the object; and
bending an end portion of the porous plate toward the upstream side to give a bend region of the porous plate, the porous plate comprising a flat region and the bend region, and a direction of the fluid flow being deflected due to the porous plate,
wherein the end portion of the porous plate comprises a plurality of pores located at the upstream side and facing in a direction toward an outside of the object, and
wherein the porous plate decreases a velocity of the fluid flow at the downstream side, thereby reducing the noise generated by the fluid flow.

10. The noise reduction method according to claim 9 , wherein a width of the flat region is larger than a largest width of the object.

Assignees

• Japan Aerospace Exploration

Inventors

• Hirai Tohru
• Murayama Mitsuhiro
• Yamamoto Kazuomi
• Ito Yasushi
• Tanaka Kentaro
• Takaishi Takehisa
• Yokokawa Yuzuru

Classifications

• B64C2025/003

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

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title

• F15B2211/8616

  the abnormal condition being noise or vibration · CPC title

• B64C2230/14

  achieving noise reductions · CPC title

• B64C25/001 Primary

  Devices not provided for in the groups B64C25/02 - B64C25/68 · CPC title