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WO2005066601A1 - Procede et dispositif pour surveiller l'integrite d'une structure comportant une surface en contact avec un liquide - Google Patents

Procede et dispositif pour surveiller l'integrite d'une structure comportant une surface en contact avec un liquide Download PDF

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Publication number
WO2005066601A1
WO2005066601A1 PCT/AU2005/000023 AU2005000023W WO2005066601A1 WO 2005066601 A1 WO2005066601 A1 WO 2005066601A1 AU 2005000023 W AU2005000023 W AU 2005000023W WO 2005066601 A1 WO2005066601 A1 WO 2005066601A1
Authority
WO
WIPO (PCT)
Prior art keywords
cavity
fluid communication
fluid
liquid
pressure
Prior art date
Application number
PCT/AU2005/000023
Other languages
English (en)
Inventor
Kenneth John Davey
Original Assignee
Structural Monitoring Systems 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
Priority claimed from AU2004900114A external-priority patent/AU2004900114A0/en
Application filed by Structural Monitoring Systems Ltd filed Critical Structural Monitoring Systems Ltd
Publication of WO2005066601A1 publication Critical patent/WO2005066601A1/fr

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
    • G01M3/04—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
    • G01M3/20—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
    • G01M3/04—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
    • G01M3/20—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material
    • G01M3/22—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material for pipes, cables or tubes; for pipe joints or seals; for valves; for welds; for containers, e.g. radiators
    • G01M3/226—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material for pipes, cables or tubes; for pipe joints or seals; for valves; for welds; for containers, e.g. radiators for containers, e.g. radiators

Definitions

  • the present invention is for a method and apparatus for monitoring the integrity of a structure having a surface in contact with a liquid.
  • the present invention has its genesis from consideration of the problems faced by aircraft engineers in monitoring the integrity of load carrying structure that may be located within, or that partly defines, a liquid storage area such a fuel containment "wet" areas in wings of aircraft.
  • This monitoring method is complicated by the use of tank sealants and can be subordinate to statutory inspection requirements of aviation regulators .
  • the inspection process is very expensive due to the time required to dry out the inspection area and the difficulty in accessing some areas.
  • a method for monitoring the integrity of a structure having a surface in contact with a liquid at a first pressure comprising:
  • Preferably forming the first cavity comprises sealing a fluid impervious material along the surface wherein the cavity is defined between the fluid impervious material and an underlying portion of the surface .
  • providing the fluid comprises providing a gas and the monitoring comprises drawing the gas through the cavity and passing the gas through a detection device for detecting traces of the liquid entrained in the gas.
  • drawing the gas through the first cavity comprises placing one end of the cavity in fluid communication with a supply of the gas, placing an opposite end of the first cavity in fluid communication with the detection device and placing the detection device in fluid communication with a relative vacuum.
  • an apparatus for monitoring the integrity of a structure having a surface in contact with a liquid at a first pressure comprising:
  • a fluid impervious cavity defining structure sealed along the surface forming a cavity between the surface and the cavity defining structure, the cavity having a first end and a second end;
  • a first conduit having one end sealed to the first end arid in fluid communication with the cavity
  • a pressure equaliser in fluid communication with an other end of the first conduct, the pressure equaliser having an opening at substantially the same level as the cavity;
  • the apparatus further comprises a monitoring device in fluid communication with the second end of the cavity for monitoring the traces of the liquid in the fluid.
  • the monitoring device comprises a liquid trap.
  • the monitoring device further comprises a relative vacuum in fluid communication with the liquid trap.
  • the monitoring device comprises a manometer coupled across the cavity.
  • the apparatus further comprises a high fluid flow impedance in fluid communication with the second end of the cavity, and wherein the manometer comprises a manometer leg having one end in fluid communication with the first conduit and a second end in fluid communication with the high fluid flow impedance.
  • the manometer further comprises a storage vessel containing a liquid in fluid communication with the one end of the manometer leg, and wherein the storage vessel is in fluid communication with the first conduit.
  • the monitoring device further comprises a vacuum source in fluid communication with the high fluid flow impedance and the first conduit.
  • the pressure equaliser comprises a bladder in the opening provided and a housing defining a volume in which the bladder is disposed, the volume being in fluid communication with the cavity.
  • the pressure equaliser comprises a vessel in which the opening is formed, the vessel in fluid communication with the cavity.
  • the pressure equaliser further comprises a pipe in fluid communication between the vessel and the cavity.
  • the pipe extends substantially vertically.
  • the pressure equaliser further comprises a gas permeable filter in fluid communication between the vessel and the cavity.
  • Figure 1 is an oblique view of a portion of an aircraft fuel tank sectioned at a location of a crack to which an embodiment of the present method may be applied;
  • Figure 2 is a schematic representation of an apparatus relating to Figure 1 with apparatus for maintaining a pressure of the fluid to be substantially the same as the first pressure, apparatus for testing and periodic monitoring, and additional apparatus for testing;
  • Figure 2a is a plan view of a terminal device incorporated in the apparatus shown in Figure 2 with an upper shell half removed;
  • Figure 2b is a schematic representation of a prior art monitoring system that can be utilised in embodiments of the present invention
  • Figure 3 is a schematic representation of a further apparatus for use in an alternative method of maintaining pressure of the fluid to be substantially the same as the first pressure.
  • Figure 4 is a schematic representation of the function of the further apparatus of Figure 3.
  • Figure 5 is a schematic representation of periodic monitoring of the apparatus of Figure 3.
  • Figure 6 is a variation of the embodiment of Figure 1.
  • Figure 7 is a schematic representation of apparatus relating to Figure 6 and apparatus for maintaining pressure of the fluid to be substantially the same as the first pressure.
  • Figure 8 is a schematic representation of periodic monitoring of the apparatus of Figure 6.
  • Figure 9 is a schematic representation of additional apparatus for testing and periodic monitoring of the apparatus of Figure 6.
  • Figure 10 is a schematic representation of further additional apparatus for testing and periodic monitoring of the apparatus of Figure 1. Detailed Description of Preferred Embodiments
  • Figure 1 illustrates an oblique view of a structure 10 in the form of a portion of an aircraft wing with an integral fuel tank 12 sectioned through a plane of a fatigue crack 14 (see the magnified view) in a lower spar cap 16.
  • a surface 18 of the spar cap 16 which is exposed to the fuel in the interior of tank 12 will be in contact with (ie immersed in) the liquid fuel.
  • the spar cap 16 is fastened to other components of the tank 12 and structure 10 by rivets 20. It is common for fatigue cracks 14 to form in a metallic structure or member such as the spar cap 16 about the rivets 20 and moreover about holes 22 through which the rivets 20 pass.
  • An embodiment of the present method for monitoring the integrity of structures can detect a flaw such as a crack 14 in the structure 10 and more particularly the spar cap 16, which has its surface 18 in contact with a liquid, comprises forming a cavity 24 on and along the surface 18 of the spar 16. This is achieved by sealing a fluid impervious material
  • the cavity 24 is filled with a fluid.
  • the fluid is a gas such as air.
  • Respective ends of the cavity 24 are coupled to ducts 30 and 31, (see Figure 2) .
  • the cavity 24 can be formed by directly laying a bead of fluid impervious sealant material on the surface, where the bead is shaped to self define a recess that together with the surface 18 forms the cavity. For example this may be achieved by an extrusion process . Alternately the material can be laid over a former (such as a fine wire) that is subsequently withdrawn. In a further alternative the manifold- can be made separately and sealed onto the surface.
  • the equaliser 100 accommodates for expansion of the entrapped fluid due to variations in altitude and assists in preventing the ingress of fluid into the cavity 24 directly from permeation into manifold 26. It is considered advantageous to make provision for a nine fold expansion in the volume of the entrapped fluid at ground level for aircraft cruising up to 40,000ft.
  • the pressure equaliser 100 comprises a bladder or sachet 101 located within a protective shell 97 comprising an upper half 102U and lower half 102L.
  • the sachet 101 is in fluid communication with a vent 99 formed in the shell 97 and can be fluidly connected to duct 30 by connector Cl .
  • the sachet 101 is shown in an expanded state which would occur at altitude. At sea level the sachet 101 would normally be in a collapsed state.
  • the sachet 101 is made of a material that is solvent resistant, flexible and has low permeability at the temperature extremes experienced in the tank 12.
  • One such material is Mylar.
  • a vent 103 is provided in the shell 97 between shell halves 102U and 102L and allows some hydrostatic pressure influence together with reference to variance of surrounding atmospheric pressure.
  • the duct 30 which is attached to an opposite end of the manifold 26 and hence cavity 24 facilitates the periodic ground testing and monitoring by allowing induction of a fluid to confirm continuity of the cavity 24 and allow monitoring for the presence of liquid (fuel) . Thorough pre- service testing of the seal of the manifold 26 (defining
  • Figure 2b illustrates an apparatus 150 for the initial dry testing of the sealing integrity of cavity 24 by connecting to either duct connector Cl or C2, and sealing the other duct with a terminal cap 33.
  • the apparatus 150 is described fully in US 5,770,794 the contents of which are incorporated herein by way of reference and in brief comprises a high fluid impedance Z in series connection in a duct D, one end of which is in communication with a vacuum source V, the other end of duct D being connected to connector Cl .
  • a transducer T and associate gauge G is coupled in parallel across the impedance Z to monitor changes in vacuum condition in duct D.
  • the equaliser 100 and terminal 33 are raised free of liquid and dried.
  • the equaliser 100 is removed from connector Cl and terminal 33 removed from connector C2.
  • a relative vacuum 1 with a liquid detector such as for example a transparent liquid trap 90 is connected to the duct 30 (or 31) at connector Cl (or C2) to draw the gas from the cavity 24. Any liquid that has seeped into the cavity 24 through the opening of a developing fatigue crack 14 under loading in flight will be entrained in the air and can be detected in the liquid detector 90.
  • the liquid is in this instance aviation fuel.
  • the connected combination of the cavity 24, pressure equaliser 100 and liquid detector 90 comprise broadly an embodiment of an apparatus 200 for monitoring the integrity of a structure having a surface in contact with a liquid.
  • FIG 3 shows a method and apparatus 200' for monitoring the structure 10 which differs from the apparatus 200 by replacement of the equaliser 100 with an alternate pressure equaliser 100 ' and corresponding method of maintaining the pressure of the fluid (i.e. air) within the cavity 24 of manifold 26 substantially the same as the pressure of the liquid (i.e. fuel) within the tank 12.
  • This equaliser 100' comprises a three-way valve 40, a gas permeable filter 42, and a standpipe 44 fluidly connected to a vessel 48, with the vessel having a hole in its base 50 to admit or expel liquid (fuel) .
  • the base 50 is arranged to be at approximately the same level as the manifold 26, and the three-way valve 40 and gas permeable filter 42 are arranged for access close to an inspection hatch (not shown) in the top of the tank Figure 1.
  • Figure 4 features a progressive series of views of the vessel 48 labelled A, B, C, D, E, F, G, H, I, J, 'A', and ⁇ BA
  • the vessel 48 accommodates for expansion of gas within the ducts 30 and 31 and cavity 24 arising from variations in altitude and changes in the hydrostatic pressure of the surrounding fuel.
  • the liquid level relative to containment within vessel 48 is shown as 45.
  • it is preferable to make provision for the expansion of the entrapped gas by at least nine times the volume of the entrapped gas at ground level for aircraft cruising up to 40,000ft and the volume of vessel 48 should be designed accordingly.
  • the vessel 48 will accommodate varying contained levels of liquid 45 during flying operations as follows: A) Aircraft on ground after refuelling. Vessel 48 is immersed in a full tank of fuel. Some fuel enters the vessel to level 45 due to hydrostatic pressure.
  • Figure 5 illustrates a method of monitoring the integrity of the fuel tank using the apparatus 200' shown in Figure 3.
  • terminals 33 of Figure 3 are removed, valve 40 positioned to allow fluid communication with cavity 24; and the relative vacuum 1 with transparent liquid trap (or other suitable liquid detector 90) connected to connector Cl.
  • Small white arrows at terminal C2 represent air induced into the apparatus 200' and connecting ducts 30 and 31 during such monitoring. Air is inducted through valve 40 by the action of the vacuum 1. This air passes through the cavity 24 and entrains any liquid that has seeped into the cavity 24 during cyclic loading of the fuel tank 12 as would occur in flight.
  • any cracks that propagate along the surface 18 to the cavity 24 forms a channel via which fuel can flow into the cavity 24.
  • the air inducted into the channel 24 by the vacuum 1 together with any entrained fuel is carried to the liquid trap 90.
  • the presence of liquid within the trap 90 is indicative of the formation of a crack in the spar cap 16 that extend into the cavity 24.
  • Figures 6-9 illustrate a further embodiment of the method and corresponding apparatus 200'' for monitoring the integrity of a structure 10, which is based on the first embodiment shown in Figures 1 and 2.
  • the single cavity 24 In this embodiment the single cavity 24
  • valve 40 is positioned to provide fluid communication between the duct 31b (and hence cavities 24a and 24b) and the pressure equaliser 100 A This maintains substantially equal fluid pressure between the liquid (ie fuel) in which the manifold 26 is immersed and the fluid (i.e. air) within the cavities 24a and 24b.
  • valve 40 is positioned to allow fluid communication with cavities 24a and 24b, and the relative vacuum 1 with transparent liquid trap (or other suitable liquid detector means) 90 is connected to connector Cl as shown in Figure 8.
  • Small white arrows at connector C2 represent air induced through the system 30a, 31a, 30b 31b and cavities 24a and 24b and valve 40. Any fuel that has seeped into the cavities 24a and/or 24b will be carried by the induced air to, and be visible at, the detector 90.
  • a benefit of apparatus 200'' is that by the provision of an isolation device 60 (depicted in Figure 9) between ducts 30a and 31a, the cavities 24a and 24b can be isolated from each other and thereby enable a backup test of the integrity of the cavities and ducts .
  • This is achieved by moving the valve 40 to a position where the conduit 31b and cavity 24b are in communication with the surrounding atmosphere and hence at ambient pressure (isolating the pressure equaliser 100' from conduit 31b) and attaching the apparatus 150 to connector Cl .
  • the cavity 24b is at ambient pressure and the cavity 24a is subjected to a relative vacuum via vacuum V and the impedance Z.
  • the apparatus 150 can be replaced with a mechanical, (ie non-electrical) equivalent apparatus 150' illustrated in Figure 10 and modified to include means of detecting the ingress of fuel into a cavity 24 or 24a as an alternative to the apparatus comprising relative vacuum 1 with transparent liquid trap 90, to produce a further embodiment 200'"' of the apparatus for monitoring the integrity of a structure having a surface in contact with a liquid.
  • the apparatus 200''' comprises manifold 26 and duct 30 similar to manifold 26 and duct 30 of Figures 1 and 2. However, duct 31 is replaced with duct 31' that performs the function of the high fluid flow impedance Z of the apparatus 150'. Although not shown in Figure 10 the apparatus 200''' further comprises a pressure equaliser 100, 100' coupled to duct 31' during operational service.
  • the high fluid flow impedance would have dimensions of a bore of 0.2 mm and a length in excess of 3 metres determined by the desired sensitivity.
  • the ducts 30 and 31' may be terminated in similar manner to ducts 30, and 31 of Figure 2 and reside within the tank 12 of Figure 1 (that is, if no feed through of ducting from integral fuel tank 12 is permitted during the initial installation) .
  • additional apparatus 150' is connected to the free ends at connections Cl and C2 of the ducts 30 and 31' .
  • the electrical transducer T of the apparatus 150 is replaced with a manometer 155 comprising valve 81, transparent vessel 83, transparent tubing column 85, valve 87, vessel 89, liquid 91 and valve 93.
  • the vacuum V of apparatus 150 is replaced with a container 97 and ducts 95 which together form a vacuum storage that may be charged mechanically by a simple air vacuum pump (not shown) to provide a vacuum in the order of -20kPa in preparation for periodic testing and monitoring.
  • the small diameter transparent column 85 provides a single manometer leg.
  • Reservoir 89 is a squat transparent vessel containing the indicating liquid 91.
  • the surface area of the reservoir 89 is large in comparison to that of column 85 so that its contained liquid level will not vary significantly in response to liquid 91 being drawn up the column 85.
  • the use of jet fuel is satisfactory as an indicating liquid 91.
  • the liquid should substantially fill the vessel 89 (as indicated by liquid surface 92) to minimise the amount of gas above the liquid. This reduces response time in achieving a stable differential pressure across column 85.
  • the purpose of the transparent vessel 83 on top of column 85 is to trap unintentional liquid egress from the top of column 85 due to exposure to excessive differential pressure.
  • the valve 93 is provided to prevent exposure to excessive pressure differential across column 85 when first carrying out a test.
  • Valves 81 and 87 provide containment of liquid 91 during transport and storage and additionally, the apparatus should remain upright.
  • any other form or type of differential pressure measurement device may be used such as pneumatically powered or driven devices .
  • the apparatus is tested for self integrity using for example the apparatus 150 or 150 ' .
  • the fuel tanks are filled and aircraft operated in a normal manner.
  • Testing for the integrity of the spar cap 16 can be incorporated as a part of scheduled maintenance. The testing need not be performed on each landing. Rather it is envisaged that testing would occur on the basis of flying time. It should also be understood that the present method is performed with the aircraft on the ground.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Examining Or Testing Airtightness (AREA)

Abstract

L'invention concerne un procédé et un dispositif pour surveiller l'intégrité de la surface (18) d'une structure (10) immergée dans un liquide et qui comprend une cavité (24) imperméable aux fluides, formée dans la surface (18) de la structure (10). La cavité (24) est en communication fluidique, par l'intermédiaire d'un conduit (30), avec un égaliseur de pression (100), ce dernier présentant une ouverture qui se situe pratiquement au même niveau que la cavité. Un fluide est placé dans la cavité (24) en communication fluidique avec l'égaliseur de pression. Si une fissure se forme sur la surface (18) s'étendant dans la cavité (24), le liquide dans lequel la surface (18) est immergée s'écoule dans la cavité (24) et peut être détecté par divers dispositifs de détection tels qu'un piège à liquide (90).
PCT/AU2005/000023 2004-01-12 2005-01-12 Procede et dispositif pour surveiller l'integrite d'une structure comportant une surface en contact avec un liquide WO2005066601A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AU2004900114A AU2004900114A0 (en) 2004-01-12 Method and apparatus for monitoring the integrity of a structure having a surface in contact with a liquid
AU2004900114 2004-01-12

Publications (1)

Publication Number Publication Date
WO2005066601A1 true WO2005066601A1 (fr) 2005-07-21

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PCT/AU2005/000023 WO2005066601A1 (fr) 2004-01-12 2005-01-12 Procede et dispositif pour surveiller l'integrite d'une structure comportant une surface en contact avec un liquide

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5770794A (en) * 1993-05-06 1998-06-23 Tulip Bay Pty Ltd Monitoring apparatus for monitoring impending faults in the integrity of a component or structure
WO2002001175A1 (fr) * 2000-06-28 2002-01-03 Bae Systems Plc Detection de fuite de fluide dans des contenants de fluides
WO2002021096A1 (fr) * 2000-09-08 2002-03-14 Structural Monitoring Systems Ltd Procede et appareil permettant de controler l'integrite de constituants et de structures
WO2002057733A1 (fr) * 2001-01-18 2002-07-25 Structural Monitoring Systems Ltd Procede et appareil d'auto-controle pour controler l'etat d'une structure
US6539776B2 (en) * 2000-06-19 2003-04-01 Structural Monitoring Systems, Ltd. Apparatus for condition monitoring of the integrity of fasteners and fastened joints

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5770794A (en) * 1993-05-06 1998-06-23 Tulip Bay Pty Ltd Monitoring apparatus for monitoring impending faults in the integrity of a component or structure
US6539776B2 (en) * 2000-06-19 2003-04-01 Structural Monitoring Systems, Ltd. Apparatus for condition monitoring of the integrity of fasteners and fastened joints
WO2002001175A1 (fr) * 2000-06-28 2002-01-03 Bae Systems Plc Detection de fuite de fluide dans des contenants de fluides
WO2002021096A1 (fr) * 2000-09-08 2002-03-14 Structural Monitoring Systems Ltd Procede et appareil permettant de controler l'integrite de constituants et de structures
WO2002057733A1 (fr) * 2001-01-18 2002-07-25 Structural Monitoring Systems Ltd Procede et appareil d'auto-controle pour controler l'etat d'une structure

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