EP1027584A2 - Essai d'etancheite acoustique - Google Patents

Essai d'etancheite acoustique

Info

Publication number
EP1027584A2
EP1027584A2 EP98950215A EP98950215A EP1027584A2 EP 1027584 A2 EP1027584 A2 EP 1027584A2 EP 98950215 A EP98950215 A EP 98950215A EP 98950215 A EP98950215 A EP 98950215A EP 1027584 A2 EP1027584 A2 EP 1027584A2
Authority
EP
European Patent Office
Prior art keywords
leakage
acoustic
storage tank
pressure
liquid
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Withdrawn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
EP98950215A
Other languages
German (de)
English (en)
Inventor
Carl Denby
James Edward Denby
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP1027584A2 publication Critical patent/EP1027584A2/fr
Withdrawn legal-status Critical Current

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
    • G01M3/24—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using infrasonic, sonic or ultrasonic vibrations

Definitions

  • This invention relates to the acoustic testing of aircraft components
  • the method is particularly, but not exclusively, applicable in relation to
  • Aircraft fuel wing tanks are designed and built as an integral part of
  • wingwet the surface of the wing creating what is termed in the industry as "wingwet”.
  • a vacuum is
  • breach can last a number of days.
  • a second and less preferred method is to apply a vacuum to the fuel
  • a helium detector is used to attempt to identify first of
  • the method proposed includes receiving acoustic signals
  • acoustic sensing is unsuitable for identifying the course of a leakage path
  • apparatus for locating fluid leakage, said apparatus comprising a device to be
  • said device comprising two acoustic transducers arranged to
  • This aspect of the invention provides apparatus suitable for following
  • sensing apparatus comprising a rigid rod member held by a
  • an acoustic transducer attached within a cavity inside said rod member
  • transducer being arranged in said cavity to sense acoustic vibrations
  • This aspect of the invention provides a sensitive and accurate method
  • an acoustic sensing device for detecting a defective or failing component in the aircraft by contacting an acoustic sensing device, adapted to focus on sounds emanating from the
  • Figure 1 is a cross-section of an aircraft wing which leaks fuel
  • Figure 2 is a schematic illustration of components of a test kit used in
  • FIG. 3 is a schematic illustration of further components of the test kit
  • Figure 4 is a cross-section of an embodiment of acoustic sensor which
  • Figure 5 is a cross-section of a further embodiment of acoustic sensor
  • a common structure of aircraft wing 2 includes
  • the wing is divided into several fuel tank compartments 8, by a series of
  • baffles 10 which include connecting passages 12 to allow the transfer of fuel
  • baffles The purpose of the baffles is to
  • Figure 1 shows an example of a typical leakage path which has
  • the leakage path 18 lies between the resin lining 6 and the
  • Figure 2 shows components of a test kit according to this embodiment
  • a control case 70 houses a vacuum pump 24, connected to
  • the inlet port 40 is connected to a manually-operable three
  • the selector valve 42 connects the inlet port 40 to the pressure regulator 40.
  • manually-operable two position selector valve 44 connects an outlet port 46
  • the pressure gauge 32 is connected to the outlet port 46.
  • One of the pressure transducers 34 is connected to a first pressure
  • the other pressure transducer 36 is connected to a
  • selector valve 56 depending on its position.
  • the pressure transducers 34, 36 are electronic pressure transducers
  • Model No DPI 700 A coil of neoprene tubing 58, 60,
  • this tubing coil is to provide a damping action in relation
  • the coils move, i.e. expand and contract, to
  • transducers 34, 36 for example liquid mercury, which would damp such
  • test that it is preferably carried out with a tank containing its normal liquid
  • the tank(s) being tested are preferably filled to
  • pressure return port 48 are sealingly connected, via a T-junction and flexible
  • vent box located centrally in the fuselage, via a vent
  • vent port is used to alter the vent port
  • the specially-adapted connector is similar to a standard
  • control case 20 is set. using the
  • selector switch 42 the pressure regulator 30 and two-way selector switch 44,
  • the fuel storage tank is next sealed for a monitoring period, to
  • the gas pressure within the storage tank is
  • the pressure monitored on the second pressure transducer 36 is the sum of the
  • control case 20 to a negative pressure in the region of -20 to -200 Mb
  • the leak path may be
  • the initial leakage rate under vacuum consists of a combination of the leakages into each of the internal breaches 16.
  • test pressures and above the liquid surface and below the liquid surface may be used by a test operator, using the indications referred to above, to identify
  • the next stage of the testing procedure concerns identifying the course
  • control case 20 is set to produce a constant negative pressure
  • the fuel storage tank is not
  • test kit used in this stage of the test
  • a sensing rod 84 and/or a sensing rod 84, a two channel signal receiver and processor 64, a pair
  • the dual-microphone acoustic sensor 62 As shown in Figure 4, the dual-microphone acoustic sensor 62
  • the microphones are spaced apart on two sides of a
  • a circular rubber flange 78 surrounds the space in front of each
  • each microphone 72, 74 is filled with a
  • silicone gel 80 which also tends to block atmospheric sounds reaching each
  • Both microphones 72, 74 are connected to a two channel
  • radio transmitter 82 The radio transmitter 82.
  • the receiver 64 contains a two channel amplifier and a variable
  • breach 16 has a characteristic frequency which is relatively high (between 10-
  • the acoustic sensor 62 is first placed adjacent to the known external
  • the acoustic sensor 62 is moved to track the course of the internal leakage path 18. The course of the
  • the signals shown on the oscilloscope display has a greater amplitude than the
  • the acoustic sensor 62 to maintain balance between the two signals.
  • test operator can readily identify
  • the receiver 64 may also be
  • the microphones 72. 74 are spaced by approximately 20
  • a sensing rod 84 having a microphone which is also be connected to the
  • microphone acoustic sensor 62 In this case, only one channel is required as
  • This sensing rod 84 includes a cylindrical body 86 having a solid end
  • portion 88 with a rounded base 90 and constructed from a material being non ⁇
  • the rounded base 90 is designed to pick up acoustic
  • the body has a length of approximately 30 cm and an outer
  • the microphone is threaded into the body 86, such that vibrations
  • the transmitted along the cavity 94 are transmitted directly to and picked up by the microphone. Furthermore, the microphone 92 is directed towards the
  • the sensing rod 84 provides a means of increased sensitivity for
  • receiver 64 tuned to select a frequency range spanning the characteristic
  • sensing rod 84 over the outer surface of the wing skin 4, preferably starting
  • the dual-microphone sensor 62 is used to coarsely plot
  • sensitivity is used to diagonally criss-cross in a zig-zag fashion across the
  • leakage path 18 will have been repaired along its whole length, and that then
  • the sensing rod described may be used to test the condition of
  • Condition testing may be
  • the components identified which are testable in such manner include the aviation fuel systems (fuel tanks, fuel transfer lines, fuel pumps

Landscapes

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

Abstract

L'invention concerne un procédé permettant de détecter une fuite suivant la ligne de fuite qui s'étend depuis un point de fuite extérieur connu et traverse le revêtement intérieur d'un réservoir de stockage de fluide. Ce procédé consiste à exercer une pression différentielle entre la surface intérieure du revêtement et la surface extérieure du réservoir de stockage, à déplacer des organes transducteurs sur cette surface extérieure, et enfin à détecter, à l'aide de ces organes transducteurs, des signaux acoustiques caractéristiques de la ligne de fuite lors du déplacement desdits organes transducteurs, de manière à identifier la trajectoire de ladite ligne de fuite.
EP98950215A 1997-10-29 1998-10-29 Essai d'etancheite acoustique Withdrawn EP1027584A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB9722871 1997-10-29
GB9722871A GB2331152A (en) 1997-10-29 1997-10-29 Leakage testing
PCT/GB1998/003231 WO1999022214A2 (fr) 1997-10-29 1998-10-29 Essai d'etancheite acoustique

Publications (1)

Publication Number Publication Date
EP1027584A2 true EP1027584A2 (fr) 2000-08-16

Family

ID=10821278

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98950215A Withdrawn EP1027584A2 (fr) 1997-10-29 1998-10-29 Essai d'etancheite acoustique

Country Status (4)

Country Link
EP (1) EP1027584A2 (fr)
AU (1) AU9637198A (fr)
GB (1) GB2331152A (fr)
WO (1) WO1999022214A2 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2841335B1 (fr) * 2002-06-19 2004-09-03 Helitest Ags Procede de controle de l'etancheite d'un reservoir d'un aeronef et dispositif associe pour equiper ces reservoirs
GB201204653D0 (en) * 2012-03-16 2012-05-02 Airbus Operations Ltd Method for detecting leaks in aircraft wings
GB2542769B (en) * 2015-09-25 2017-10-04 Airbus Operations Ltd Method for detecting leaks in aircraft wings
FR3074320A1 (fr) 2017-11-30 2019-05-31 Airbus Operations Systeme et procede de detection automatisee de bruit de fuite dans un aeronef
CN108317403A (zh) * 2018-01-29 2018-07-24 清华大学合肥公共安全研究院 一种管道状态检测器
CN110879122A (zh) * 2019-12-13 2020-03-13 西安飞机工业（集团）有限责任公司 一种飞机机翼油箱密封性检测装置及检测方法
CN113551846A (zh) * 2021-08-27 2021-10-26 中国商用飞机有限责任公司 用于检测水箱泄漏的装置及包含该装置的飞机

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE502847A (fr) * 1951-04-25
US4309576A (en) * 1979-07-16 1982-01-05 Heath Consultants Incorporated Listening device for localizing underground water leakages
US4455863A (en) * 1982-03-29 1984-06-26 Consolidated Natural Gas Service Company Sonic detection of gas leaks in underground pipes
DE3336245A1 (de) * 1983-10-05 1985-04-25 Kraftwerk Union AG, 4330 Mülheim Verfahren zum ermitteln einer leckstelle an druckfuehrenden behaeltern und einrichtung dazu
JPS60111132A (ja) * 1983-11-18 1985-06-17 Tokiko Yuki Kk タンクの漏洩検査方法
US4911012A (en) * 1988-03-18 1990-03-27 Ziska Thomas J Sewer line detection system
US5269335A (en) * 1990-07-27 1993-12-14 Heitman Lynn B Automatic pulsing valve
GB2269900A (en) * 1992-08-19 1994-02-23 Christopher David Hill Acoustic leak detection method for liquid storage tanks
JPH0777477A (ja) * 1992-09-02 1995-03-20 Rion Co Ltd リーク検出装置及び方法
JPH07286930A (ja) * 1994-04-18 1995-10-31 Japan Airlines Co Ltd 航空機における燃料漏れ位置の検出方法及びこれに用いる装置
EP0793118A3 (fr) * 1996-02-27 1998-10-28 Thames Water Utilities Limited Dispositif pour déterminer la position et connection de tuyauterie

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9922214A3 *

Also Published As

Publication number Publication date
WO1999022214A3 (fr) 1999-09-02
GB9722871D0 (en) 1997-12-24
WO1999022214A2 (fr) 1999-05-06
GB2331152A (en) 1999-05-12
AU9637198A (en) 1999-05-17

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