Systems and methods for restricting movement in flexible ducts

Patent metadata

Field	Value
Publication number	US-10480451-B2
Application number	US-201514689265-A
Country	US
Kind code	B2
Filing date	Apr 17, 2015
Priority date	Apr 17, 2015
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

Abstract

Methods and systems for restricting movement in a flow mixer including a plurality of lobes that each includes a trough, using a stiffener mechanism, are provided. The stiffener mechanism includes a first end portion configured to be coupled to a first lobe of the plurality of lobes and a second end portion configured to be coupled to a second lobe of the plurality of lobes. The stiffener mechanism also includes a body portion coupled between the first end portion and the second end portion such that the body portion is configured to restrict movement of the first and second lobes.

First claim

What is claimed is:

1. An aircraft exhaust system comprising:
a flow mixer comprising:
a plurality of first lobes, wherein at least one first lobe comprises a pair of opposing first sidewalls and a first trough extending between said pair of opposing first sidewalls; and
a plurality of second lobes, wherein at least one second lobe comprises a pair of opposing second sidewalls and a second trough extending between said pair of opposing second sidewalls, wherein each second trough is aligned with and spaced a distance from a corresponding first trough; and

a stiffener mechanism integrally formed with said flow mixer from a ceramic matrix composite (CMC) material and extending linearly between an apex of a first lobe, of the plurality of first lobes, and an apex of a second lobe, of the plurality of second lobes, in at least one pair of corresponding first lobe and second lobe such that said stiffener mechanism is configured to restrict movement of said first lobe and said second lobe, said stiffener mechanism comprising:
a first end portion integrally formed with a bottom surface of the apex of said first lobe;
a second end portion integrally formed with a top surface of the apex of said second lobe;
a body portion integrally formed with said first end portion and said second end portion; and
a pair of spacers coupled between said body portion and each of the at least one first lobe and the at least one second lobe.

2. The aircraft exhaust system according to claim 1 , wherein said stiffener mechanism, said plurality of first lobes, and said plurality of second lobes are formed from a same material.

3. The aircraft exhaust system according to claim 1 , further comprising a layer of skin laid over a first portion of a trough of the at least one first lobe, a first side of said body portion, and a first portion of a trough of the at least one second lobe.

4. The aircraft exhaust system according to claim 3 , further comprising a second layer of skin laid over a second portion of the trough of the at least one first lobe, a second side of said body portion, and a second portion of the trough of the at least one second lobe.

5. A method of increasing a resonant frequency of a flow mixer that includes a plurality of lobes that each includes a trough and a pair of sidewalls, said method comprising:
integrally forming a first end portion of a stiffening mechanism with a bottom surface of an apex of a first lobe of the plurality of lobes during a lay-up process;
integrally forming a second end portion of the stiffening mechanism with a top surface of an apex of a second lobe of the plurality of lobes during the lay-up process; and
integrally forming a body portion of the stiffening mechanism with the first end portion and the second end portion during the lay-up process such that the body portion restricts movement of the first and second lobes, wherein the body portion extends linearly between the apexes of the first lobe and the second lobe.

6. The method in accordance with claim 5 , further comprising forming the stiffener mechanism and the plurality of lobes from a same material.

7. The method in accordance with claim 6 , further comprising forming the stiffener mechanism and the plurality of lobes from a ceramic matrix composite (CMC) material.

8. The method in accordance with claim 5 , coupling a pair of spacers coupled between the body portion and each of the first and second lobes.

9. The method in accordance with claim 5 , further comprising laying-up a layer of skin over a first portion of a trough of the first lobe, a first side of the body portion, and a first portion of a trough of the second lobe.

10. The method in accordance with claim 9 , further comprising laying-up a second layer of skin over a second portion of the trough of the first lobe, a second side of the body portion, and a second portion of the trough of the second lobe.

11. An aircraft exhaust system comprising:
a flow mixer comprising:
a plurality of first lobes, wherein at least one first lobe comprises a pair of opposing first sidewalls and a first trough extending between said pair of opposing first sidewalls; and
a plurality of second lobes, wherein at least one second lobe comprises a pair of opposing second sidewalls and a second trough extending between said pair of opposing second sidewalls, wherein each second trough is aligned with and spaced a distance from a corresponding first trough; and

a stiffener mechanism integrally molded with said flow mixer from a metallic or metal alloy material and extending linearly between an apex of a first lobe, of the plurality of first lobes, and an apex of a second lobe, of the plurality of second lobes, in at least one pair of corresponding first lobe and second lobe such that said stiffener mechanism is configured to restrict movement of said first lobe and said second lobe, said stiffener mechanism comprising:
a first end portion integrally molded with a bottom surface of the apex of said first lobe;
a second end portion integrally molded with a top surface of the apex of said second lobe;
a body portion integrally molded with said first end portion and said second end portion; and
a pair of spacers coupled between said body portion and each of the at least one first lobe and the at least one second lobe.

12. The aircraft exhaust system according to claim 11 , wherein said stiffener mechanism, said plurality of first lobes, and said plurality of second lobes are formed from a same material.

13. The aircraft exhaust system according to claim 11 , further comprising a layer of skin laid over a first portion of a trough of the at least one first lobe, a first side of said body portion, and a first portion of a trough of the at least one second lobe.

14. The aircraft exhaust system according to claim 13 , further comprising a second layer of skin laid over a second portion of the trough of the at least one first lobe, a second side of said body portion, and a second portion of the trough of the at least one second lobe.

Assignees

• Boeing Co

Inventors

• Pinney Thomas Richardson
• Best Michael
• Embler Jonathan D
• Keith William P
• Sidiropoulos Aristidis
• Tong Edward T

Classifications

• F02K1/46 Primary

  Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing (F02K1/28, F02K1/36, F02K1/38 take precedence) · CPC title

• F05D2220/329

  in helicopters · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title