Enhanced fluid attenuators and methods, especially useful for aircraft hydraulic systems

Patent metadata

Field	Value
Publication number	US-9476533-B2
Application number	US-201514595838-A
Country	US
Kind code	B2
Filing date	Jan 13, 2015
Priority date	Jan 13, 2015
Publication date	Oct 25, 2016
Grant date	Oct 25, 2016

Abstract

Fluid attenuator systems and methods for attenuating fluid ripple waves within a main fluid line (e.g., a main hydraulic fluid line of an aircraft hydraulic system). At least one attenuator branch conduit may be provided in fluid communication with and at substantially a right angle to the main fluid line with a porous material positioned therewithin (e.g., at an open inlet or a closed distal end of the at least one attenuator branch conduit). The porous material may be a metallic or ceramic open-cell foam material. Multiple attenuator branch conduits may be provided with each having a different length as compared to the others. In such embodiments, the porous material may (or may not) be positioned within the different length attenuator branch conduits (e.g., at an open inlet or a closed distal end of respective ones of attenuator branch conduits).

First claim

What is claimed is:

1. An aircraft hydraulic system comprising:
a main hydraulic fluid line,
a hydraulic pump fluid connected to the main hydraulic fluid line which hydraulically generates dynamic pressure fluctuations of hydraulic fluid in the main hydraulic fluid line when operated, and
a hydraulic fluid attenuator system downstream of the hydraulic pump for attenuating the dynamic pressure fluctuations of the hydraulic fluid within the main hydraulic fluid line, wherein the fluid attenuator system comprises:
(i) at least one attenuator branch conduit in fluid communication with and at substantially a right angle to the main hydraulic fluid line; and
(ii) a porous material positioned within the at least one attenuator branch conduit.

2. The aircraft hydraulic system as in claim 1 , wherein the porous material of the hydraulic fluid attenuator system is positioned within the at least one attenuator branch at an open proximal end thereof at a juncture with the main hydraulic fluid line.

3. The aircraft hydraulic system as in claim 1 , wherein the porous material of the hydraulic fluid attenuator system is positioned within the at least one attenuator branch at a closed distal end thereof relative to the main hydraulic fluid line.

4. The aircraft hydraulic system as in claim 1 , wherein the porous material of the hydraulic fluid attenuator system is a metallic or ceramic open-cell foam material.

5. The aircraft hydraulic system as in claim 1 , wherein the hydraulic fluid attenuator system further comprises multiple attenuator branch conduits each at a substantially right angle to the main hydraulic fluid line, wherein each of the multiple attenuator branch conduits includes a porous material positioned therewithin.

6. The aircraft hydraulic system as in claim 5 , wherein the porous material of the hydraulic fluid attenuator system is positioned within the multiple attenuator branch conduits at an open proximal end thereof at a juncture with the main hydraulic fluid line.

7. The aircraft hydraulic system as in claim 5 , wherein the porous material of the hydraulic fluid attenuator system is positioned within the multiple attenuator branch conduits at a closed distal end thereof relative to the main hydraulic fluid line.

8. The aircraft hydraulic system as in claim 1 , wherein the hydraulic fluid attenuator system further comprises multiple attenuator branch conduits each at substantially right angle to the main hydraulic fluid line, wherein each of the multiple attenuator branch conduits has a different length dimension.

9. The aircraft hydraulic system as in claim 8 , wherein each of the multiple attenuator branch conduits has a porous material.

10. The aircraft hydraulic system as in claim 9 , wherein the porous material of the hydraulic fluid attenuator system is positioned within the multiple attenuator branch conduits at an open proximal end thereof at a juncture with the main hydraulic fluid line.

11. The aircraft hydraulic system as in claim 9 , wherein the porous material of the hydraulic fluid attenuator system is positioned within the multiple attenuator branch conduits at a closed distal end thereof relative to the main hydraulic fluid line.

12. An aircraft hydraulic system comprising:
a main hydraulic fluid line,
a hydraulic pump fluid connected to the main hydraulic fluid line which hydraulically generates dynamic pressure fluctuations of hydraulic fluid in the main hydraulic fluid line when operated, and
a hydraulic fluid attenuator system downstream of the hydraulic pump for attenuating the dynamic pressure fluctuations of the hydraulic fluid within the main hydraulic fluid line, wherein the fluid attenuator system comprises:
(i) multiple attenuator branch conduits each in fluid communication with and at substantially a right angle to the main hydraulic fluid line, wherein
(ii) each one of the multiple attenuator branch conduits has a length dimension which is different from others of the multiple attenuator branch conduits.

13. The aircraft hydraulic system as in claim 12 , wherein each of the multiple attenuator branch conduits of the fluid attenuator system has a porous material positioned therewithin.

14. The aircraft hydraulic system as in claim 13 , wherein the porous material is positioned within the multiple attenuator branch conduits at an open proximal end thereof at a juncture with the main hydraulic fluid line.

15. The aircraft hydraulic system as in claim 13 , wherein the porous material is positioned within the multiple attenuator branch conduits at a closed distal end thereof relative to the main hydraulic fluid line.

16. A method of attenuating dynamic pressure fluctuations in hydraulic fluid caused by operating a hydraulic pump in fluid communication with a main hydraulic fluid line of an aircraft hydraulic system, comprising:
(i) providing at least one attenuator branch conduit downstream of the hydraulic pump in fluid communication with and at substantially a right angle to the main hydraulic fluid line of the aircraft hydraulic system; and
(ii) positioning a porous material within the at least one attenuator branch conduit.

17. The method as in claim 16 , wherein the porous material is positioned within the at least one attenuator branch at an open proximal end thereof at a juncture with the main hydraulic fluid line.

18. The method as in claim 16 , wherein the porous material is positioned within the at least one attenuator branch at a closed distal end thereof relative to the main hydraulic fluid line.

19. The method as in claim 16 , wherein the porous material is a metallic or ceramic open-cell foam material.

20. The method as in claim 16 , further comprising providing multiple attenuator branch conduits each at a substantially right angle to the main hydraulic fluid line, wherein each of the multiple attenuator branch conduits includes a porous material therewithin.

21. The method as in claim 20 , wherein the porous material is positioned within the multiple attenuator branch conduits at an open proximal end thereof at a juncture with the main hydraulic fluid line.

22. The method as in claim 20 , wherein the porous material is positioned within the multiple attenuator branch conduits at a closed distal end thereof relative to the main hydraulic fluid line.

23. The method as in claim 16 , further comprising multiple attenuator branch conduits each at substantially right angle to the main hydraulic fluid line, wherein each one of the multiple attenuator branch conduits has a different length dimension as compared to others of the multiple attenuator branch conduits.

24. The method as in claim 23 , wherein each of the multiple attenuator branch conduits has a porous material therewithin.

25. The method as in claim 24 , wherein the porous material is positioned within the multiple attenuator branch conduits at an open proximal end thereof at a juncture with the main hydraulic fluid line.

26. The method as in claim 24 , wherein the porous material is positioned within the multiple attenuator branch conduits at a closed distal end thereof relative to the main hydraulic fluid line.

27. A method for attenuating dynamic pressure fluctuations in hydraulic fluid caused by operating a hydraulic pump in fluid communication with a main hydraulic fluid line of an aircraft hydraulic system, comprising providing multiple attenuator branch conduits each i

Assignees

• Embraer Sa

Inventors

• Futatsugi Sideto
• Klug Francisco Keller
• Gasparotti André

Classifications

• F16L55/033 Primary

  Noise absorbers (F16L55/027 takes precedence) · CPC title

• F16L55/041

  specially adapted for preventing vibrations (flexible pipe connections F16L27/10) · CPC title