GB2572021A - Aircraft fuel pipe support - Google Patents

Aircraft fuel pipe support Download PDF

Info

Publication number
GB2572021A
GB2572021A GB1807339.5A GB201807339A GB2572021A GB 2572021 A GB2572021 A GB 2572021A GB 201807339 A GB201807339 A GB 201807339A GB 2572021 A GB2572021 A GB 2572021A
Authority
GB
United Kingdom
Prior art keywords
support
fuel pipe
mounting bracket
pipe support
collar
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB1807339.5A
Other versions
GB201807339D0 (en
Inventor
Kishore Shahani Varun
James Willetts Peter
Suresh Mulay Amol
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Eaton Intelligent Power Ltd
Original Assignee
Eaton Intelligent Power Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Eaton Intelligent Power Ltd filed Critical Eaton Intelligent Power Ltd
Publication of GB201807339D0 publication Critical patent/GB201807339D0/en
Publication of GB2572021A publication Critical patent/GB2572021A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
    • F16L3/08—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing
    • F16L3/10—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing divided, i.e. with two or more members engaging the pipe, cable or protective tubing
    • F16L3/1091—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing divided, i.e. with two or more members engaging the pipe, cable or protective tubing with two members, the two members being fixed to each other with fastening members on each side
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
    • F16L3/08—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing
    • F16L3/12—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
    • F16L3/16—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets with special provision allowing movement of the pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L5/00—Devices for use where pipes, cables or protective tubing pass through walls or partitions
    • F16L5/02—Sealing
    • F16L5/025—Sealing the pipe being movable
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Supports For Pipes And Cables (AREA)

Abstract

An aircraft fuel pipe support 10 comprising at least one mounting bracket 20 for attachment to an aircraft structure 2 and a support collar 30. The support collar is attached to the at least one mounting bracket by a pivot connection 60, and the support collar is rotatable relative to the mounting bracket about the pivot. An aircraft fuel system comprises at least one fuel pipe 4 and at least one fuel pipe support 10. Where an aircraft structure includes the aircraft fuel pipe support 10, the support 10 is fixed to the structure by the mounting bracket 20. The support collar may comprise an outer rigid frame and an inner compliant cushioning member 50 which may be formed of two segments. The support collar may be free to rotate relative to the mounting bracket by an angle of approximately 20 degrees. The aforementioned mounting bracket may comprise two mounting brackets. The pivot connections between the support collar and each of the mounting brackets have a common axis of rotation.

Description

AIRCRAFT FUEL PIPE SUPPORT
FIELD OF INVENTION
The present invention relates to an aircraft fuel pipe support. The invention also relates to an aircraft fuel system including an aircraft fuel pipe support and an aircraft structure including an aircraft fuel pipe support.
BACKGROUND OF INVENTION
Aircraft wing structures generally comprise an internal support structure which may include a series of wing ribs. In a typical commercial aircraft, the aircraft fuel system includes a number of fuel pipes, extending through at least a portion of the wings, for distributing fuel between fuel tanks and to the engines. Accordingly, the fuel pipes must pass through the various wing ribs or other structural members and are required to be supported within the wing, often by brackets or supports.
Known fuel pipe supports often require the fuel pipe to be positioned substantially perpendicular (i.e. having an angle of engagement of 0 degrees) to the wing rib, or other structure, which the pipe is passing through. Therefore, at least one portion of the pipe adjacent to the rib must be angled accordingly so that this can occur. If the angle of engagement with the wing rib is not zero degrees, high stresses may be placed on the support and on the fuel pipe. To alleviate this problem it is known to provide a cushioning material (for example of an elastomer material) within the support. The cushioning material may, for example, be provided between the inner body of the support and the exterior of the fuel pipe and may be an annular ring. Even so, current supports generally only allow small angles of engagement (of around 7 degrees) due to the properties of the cushioning material. Accordingly, larger angles of engagement must still be avoided as they will cause high stresses. In order to address this problem, the fuel pipe may be bent to allow it to pass though the support at a low engagement angle. Bending of the fuel pipes causes wall thinning and unwanted stresses within the pipe walls and it is therefore preferred to avoid or minimise bending.
Further known fuel pipe supports allow slightly larger angles of engagement by providing an adjustable support but with a large number of parts, resulting in complex manufacturing requirements, assembly and installation of the support, and increased component weight. One example of such a support is shown in EP 2 634 467 Al, in which a tube support can be adjusted angularly due to having curved surfaces and an eccentric sleeve which may slide relative to each other so that the alignment of the support can be set during installation.
Accordingly, there is a desire to provide a simple aircraft fuel pipe support that enables a greater variation of engagement angle between the fuel pipe and supporting structure. Embodiments of the present invention seek to provide an aircraft fuel pipe support which overcomes one or more of the above disadvantages of conventional fuel pipe supports.
SUMMARY OF INVENTION
Accordingly, in one aspect of the invention, there is provided an aircraft fuel pipe support comprising:
at least one mounting bracket for attachment to an aircraft structure;
a support collar;
wherein the support collar is attached to the at least one mounting bracket by a pivot connection, the support collar being rotatable relative to the mounting bracket about said pivot.
The support collar may be generally annular and may substantially surround the fuel pipe. The support may be articulated with respect to the mounting bracket about the pivot. Advantageously, the pivot connection between the collar and mounting bracket may allow the support of embodiments of the invention to self align between the pipe and the structure to which the support is attached. The pivot connection may provide a pre-determined degree of freedom of movement between the support collar and the at least one mounting bracket in use.
The pivot connection may comprise a pin. The at least one mounting bracket may comprise a hole to receive the pin. The pin may be either separately or integrally formed with one of the mounting brackets or the support collar.
The support collar may comprise an outer rigid frame and an inner compliant cushioning member. The rigid outer frame and inner compliant cushioning member may comprise separate materials or may be co-moulded from two materials. The cushioning member may be formed of at least two segments.
The support collar outer rigid frame may comprise at least one recess on an internal face. The recess may be formed between first and second flanges defining end walls of the outer frame. The cushioning member may be located in the recess of the support ring.
The support ring may be formed of at least two segments. The support ring segments may comprise a plurality of like segments. Each segment may extend from a male coupling at a first circumferential end to a complementary female coupling at a second circumferential end. Such an arrangement may reduce the number of unique parts required. As such a plurality of identical segments may be assembled into a complete ring. Each support ring segment may comprise a snap fit arrangement. The complementary male and female couplings may, therefore, be snap-fit couplings.
The at least one mounting bracket may comprise two mounting brackets. Said mounting brackets may be positioned on diametrically opposed sides of the support. The pivot connections between the support ring and each of the mounting brackets may have a common axis of rotation. The pipe support may provide a gimbal type arrangement.
The, or each, mounting bracket may comprise at least one bolt hole. The bracket may comprise an elongate member having a bolt hole proximal to each end. The pivot connection may be in a central portion between the ends. The, or each, mounting bracket may include a tab in a central portion in which the pivot connection may be formed.
The support ring may be free to rotate relative to the mounting bracket by an angle of up to approximately 20 degrees.
According to a further aspect of the invention there is provided an aircraft fuel system including at least one fuel pipe and at least one aircraft fuel pipe support, the fuel pipe support may comprise at least one mounting bracket for attachment to an aircraft structure and a support collar. The support collar may be attached to the at least one mounting bracket by a pivot connection, the support collar may be rotatable relative to the mounting bracket about said pivot. The support may be fixed to the structure by the mounting bracket.
According to a further aspect of the invention there is provided an aircraft structure including an aircraft fuel pipe support, the fuel pipe support may comprise at least one mounting bracket for attachment to an aircraft structure and a support collar. The aircraft structure may include an aperture, the mounting bracket may be connected to a periphery of the aperture and the support collar may be positioned generally within the aperture.
Whilst the invention has been described above, it extends to any inventive combination set out above, or in the following description or drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention may be performed in various ways, and an embodiment thereof will now be described by way of example only, reference being made to the accompanying drawings, in which:
Figure 1 shows the pipe support in accordance with an embodiment in use in a typical aircraft wing fuel system;
Figure 2A shows a three dimensional schematic view of a pipe support in accordance with an embodiment;
Figure 2B shows a top view of the pipe and wing rib showing the movement of the pipe relative to the pipe support;
Figure 3A shows the pipe support of an embodiment in isolation from the fuel pipe and aircraft structure;
Figure 3B schematically shows the axis of rotation of the support collar;
Figure 4 shows the individual components of the pipe support according to an embodiment including the mounting bracket (A), the rigid outer frame of the support collar (B), the cushioning member of the support collar (C), the pin (D) and the washer (E)
DETAILED DESCRIPTION OF THE DRAWINGS
Figure 1 shows the fuel pipe support 10 in use in an aircraft fuel system. The aircraft structure includes a plurality of wing ribs 2. The fuel pipes 4 of the aircraft fuel system extend in a generally spanwise direction along the length of the wing. The fuel pipes must pass through, and be supported relative to, the wing ribs 2 which extend generally transversely to the spanwise direction. Fig 2 shows the fuel pipe support 10 of an embodiment in use, supporting the fuel pipe 4 and attached to a wing rib 2. Fig 2A shows a top view of the freedom of movement of the fuel pipe 4 relative to the wing rib in a support according to an embodiment.
Fig 3A shows the fuel pipe support 10 comprising two spaced apart mounting brackets 20a and 20b and a support collar 30. The mounting brackets attach to the wing rib 2 using bolt holes 24 disposed at either end of each mounting bracket 20. The support collar 30 substantially surrounds and engages the fuel pipe 4 and is attached to the mounting brackets 20 by a pivot connection 60. The support collar 30 is freely rotatable relative to the mounting bracket 20 about the pivot 60. The pivot connection 60 comprises a pin 62, shown in Fig 4D, and a pin hole 22 in the mounting bracket 20. A washer 70, shown in Fig 4E, is disposed between the support collar 30 and the mounting bracket 20 and mounted on the pin 62. The pivot connections 60 have a common axis of rotation 64 about which the support collar 30 rotates. Fig 3B shows the axis of rotation 64 through the pin holes 22 in the mounting brackets 20. Each component will be described in further detail below.
The upper 20a and lower 20b mounting brackets are identical. Each mounting bracket 20 comprises a generally elongate member with a bolt hole 24 provided proximal to each end 25. A pin receiving aperture 22 is provided in the central portion of the mounting bracket 20. The bolt holes 24 are used to attach the mounting brackets 20 and, therefore, the fuel pipe support 10 to a surrounding portion of the wing structure (for example the wing rib 2) by conventional means such as a bolt.
It may be noted that the mounting bracket 20 is profiled to minimise weight. As such the portion between the/each bolt hole 24 and the pin aperture 22 has a reduced cross section (for example it has a 'necked' profile). The central portion 21 may include a tab 23 providing a surface in which the aperture 22 can be formed, as shown in Fig 4A. It may be noted that the tab 23 is generally in a plane which is perpendicular to the plane of the ends 25 having the bolt holes 24 (and the axis of the aperture 22 is perpendicular to the plane of the tab 23).
The support collar 30 comprises an outer rigid frame 40 and an inner compliant cushioning member 50. The outer frame 40 comprises 2 identical segments, shown in Fig 4B, which couple together by means of a snap fit arrangement 44. Each segment comprises a male coupling 45 and a female coupling 46 at opposite circumferential ends of each outer frame segment 40. The male coupling 45 comprises a pair of parallel fingers 47a, 47b which project in a generally circumferential direction from the end of the segment. The fingers 47a, 47b each have an arrowhead type formation 49 at their distal end. The female coupling 46 comprises a pair of spaced apart tabs 48a, 48b, for engaging and retaining the fingers 47a, 47b of the male coupling 45. The tabs extend substantially radially from the surface of the collar 30. It will be appreciated that the arrowhead formations 49 of the fingers 47 allow the fingers to resiliently deflect axially inwardly to travel past the tabs 48 and to then elastically spring back into their original position with the stepped surface of the arrowhead positioned beyond/behind the tabs 48 to clip the segments of the collar 30 together.
The outer frame 40 also comprises a recess 42 on the internal face where the recess 42 is formed between first flange 41 and second flange 43 defining end walls of the outer frame 40. The recess 42, which is generally annular, is arranged to receive the cushioning member 50. The recess retains the cushioning member 50 in position relative to the outer frame 40. The cushioning member 50 is formed of two identical segments, shown in Fig 4C, and is located in the recess 42 of the support collar outer frame 40. It will be appreciated that in some embodiments the cushioning member may be integrally formed or permanently attached to the outer frame.
In use the mounting brackets 20 are attached such that they span an aperture in the wing rib 2. The aperture will typically have been specifically provided to allow passage of the fuel pipe through the boundary defined by the wing rib 2. The support collar 30 is therefore positioned approximately within and across the aperture. The support collar can be snap fitted around the fuel pipe 4 such that the pipe is supported and engaged by the bracket 20. The cushioning member 50 is disposed between the outer surface of the fuel pipe 4 and the inner surface of the outer frame 40 and provides a degree of compliance to reduce stress. With the bracket installed the pivots 60 of the mounting brackets are aligned through the common axis 64. As such the support collar 30 can act as a gimbal, providing a support for the pipe which is rotatable about the axis 64. The support collar 30 rotates around the axis 64 relative to the mounting brackets 20 and therefore the wing rib 2 such that the angle of rotation is up to 20 degrees, shown by Fig 2B. The support of embodiments may simplify and/or speed up installation since the support can self align without the need for specific adjustment for each location on the aircraft by the installer.
Although the invention has been described above with reference to an embodiment, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims. For example, whilst the embodiment includes a separate pin component to provide the pivot connection it will be appreciated that a 5 pin may be provided in the form of an axle which is integrally formed on either the mounting bracket or the support collar (with the other having a corresponding formation such as an aperture or recess to receive the pin). Likewise, whilst the frame of the preferred embodiment is formed of two-segments it could be formed of any number of segments subject to the specific application (for example due to the pipe sizing). It will be appreciated that the self-aligning 10 nature about the axis enables the articulated pivot connection between the support collar and mounting bracket of the invention may have the advantage of reducing pressure on the pipe and or support due to the angle of engagement between the pipe and the support. Additionally the freedom of movement about the pivot may allow a degree of dynamic stress alleviation for example due to changes in relative alignment between the structure and fuel pipe as a result of flight loads (for example which cause wing bending).

Claims (18)

1. An aircraft fuel pipe support comprising:
at least one mounting bracket for attachment to an aircraft structure;
a support collar;
wherein the support collar is attached to the at least one mounting bracket by a pivot connection, the support collar being rotatable relative to the mounting bracket about said pivot.
2. A fuel pipe support as claimed in claim 1, wherein the pivot connection comprises a pin and the at least one mounting bracket comprises a hole to receive the pin.
3. A fuel pipe support as claimed in claim 1 or 2 wherein the support collar is generally annular.
4. A fuel pipe support as claimed in any preceding claim, wherein the support collar comprises an outer rigid frame and an inner compliant cushioning member.
5. A fuel pipe support as claimed in claim 4 wherein the cushioning member is formed of at least two segments.
6. A fuel pipe support as claimed in claim 4 or 5 wherein the support collar outer rigid frame comprises at least one recess on an internal face.
7. A fuel pipe support as claimed in any preceding claim wherein the cushioning member is located in the recess of the support collar.
8. A fuel pipe support as claimed in any preceding claim wherein the support collar is formed of at least two segments.
9. A fuel pipe support as claimed in claim 8, wherein the support collar segments comprise a plurality of like segments, each segment extending from a male coupling at a first circumferential end to a complementary female coupling at the second circumferential end.
10. A fuel pipe support as claimed in claim 8 or 9 wherein each support collar segment comprises a snap fit arrangement.
11. A fuel pipe support as claimed in any preceding claim wherein the at least one mounting bracket comprises two mounting brackets.
12. A fuel pipe support as claimed in claim 11, wherein the pivot connections between the support collar and each of the mounting brackets have a common axis of rotation.
13. A fuel pipe support as claimed in any preceding claim wherein the, or each, mounting bracket comprises at least one bolt hole.
14. A fuel pipe support as claimed in any preceding claim wherein the or each mounting bracket comprises an elongate member having a bolt hole proximal to each end and the pivot connection being in a central portion between the ends.
5
15. A fuel pipe support as claimed in any preceding claim wherein the support collar is free to rotate relative to the mounting bracket by an angle of approximately 20 degrees.
16. An aircraft fuel system comprising at least one fuel pipe and at least one fuel pipe support, in accordance with any preceding claim.
17. An aircraft structure including an aircraft fuel pipe support in accordance with any preceding claim, the support being fixed to the structure by the mounting bracket.
18. An aircraft structure as claimed in claim 17, wherein the structure includes an aperture, the
15 mounting bracket being connected to a periphery of the aperture and the support collar being positioned generally within the aperture.
GB1807339.5A 2018-03-17 2018-05-04 Aircraft fuel pipe support Withdrawn GB2572021A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IN201811009870 2018-03-17

Publications (2)

Publication Number Publication Date
GB201807339D0 GB201807339D0 (en) 2018-06-20
GB2572021A true GB2572021A (en) 2019-09-18

Family

ID=62598326

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1807339.5A Withdrawn GB2572021A (en) 2018-03-17 2018-05-04 Aircraft fuel pipe support

Country Status (1)

Country Link
GB (1) GB2572021A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220055766A1 (en) * 2020-08-18 2022-02-24 Airbus Operations Limited Fuel pipe assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE920046C (en) * 1950-11-24 1954-11-11 Frederick Matthew Guy Elastic shaft suspension, preferably for motor vehicles
EP0160212A1 (en) * 1981-02-14 1985-11-06 Dunlop Limited Improvements in or relating to resilient mountings
US20060065801A1 (en) * 2004-09-29 2006-03-30 Anderson Carl J Ii Gimbaled mounting bracket
RU2391594C1 (en) * 2009-02-18 2010-06-10 ЗАО "Нефтемонтаждиагностика" Seismic protective support for pipeline
RU2648179C1 (en) * 2017-06-23 2018-03-22 Публичное акционерное общество "Транснефть" (ПАО "Транснефть") Seismic resistant four-pile mobile pipeline support and damper device for the seismic resistant four-pile mobile pipeline support

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE920046C (en) * 1950-11-24 1954-11-11 Frederick Matthew Guy Elastic shaft suspension, preferably for motor vehicles
EP0160212A1 (en) * 1981-02-14 1985-11-06 Dunlop Limited Improvements in or relating to resilient mountings
US20060065801A1 (en) * 2004-09-29 2006-03-30 Anderson Carl J Ii Gimbaled mounting bracket
RU2391594C1 (en) * 2009-02-18 2010-06-10 ЗАО "Нефтемонтаждиагностика" Seismic protective support for pipeline
RU2648179C1 (en) * 2017-06-23 2018-03-22 Публичное акционерное общество "Транснефть" (ПАО "Транснефть") Seismic resistant four-pile mobile pipeline support and damper device for the seismic resistant four-pile mobile pipeline support

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220055766A1 (en) * 2020-08-18 2022-02-24 Airbus Operations Limited Fuel pipe assembly

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