WO1991007208A2 - Ameliorations apportees a des systemes de vaporisation d'eau - Google Patents

Ameliorations apportees a des systemes de vaporisation d'eau Download PDF

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Publication number
WO1991007208A2
WO1991007208A2 PCT/GB1990/001767 GB9001767W WO9107208A2 WO 1991007208 A2 WO1991007208 A2 WO 1991007208A2 GB 9001767 W GB9001767 W GB 9001767W WO 9107208 A2 WO9107208 A2 WO 9107208A2
Authority
WO
WIPO (PCT)
Prior art keywords
water
spray
storage vessel
spray system
water spray
Prior art date
Application number
PCT/GB1990/001767
Other languages
English (en)
Other versions
WO1991007208A3 (fr
Inventor
Robert Lindsay Farquhar
David Nicholas Ball
Raymond Tindall Whitfield
Original Assignee
Kidde-Graviner Limited
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 Kidde-Graviner Limited filed Critical Kidde-Graviner Limited
Publication of WO1991007208A2 publication Critical patent/WO1991007208A2/fr
Publication of WO1991007208A3 publication Critical patent/WO1991007208A3/fr
Priority to GB9210132A priority Critical patent/GB2256366A/en

Links

Classifications

    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C3/00—Fire prevention, containment or extinguishing specially adapted for particular objects or places
    • A62C3/07—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles
    • A62C3/08—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C31/00—Delivery of fire-extinguishing material
    • A62C31/02—Nozzles specially adapted for fire-extinguishing
    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C35/00—Permanently-installed equipment
    • A62C35/58—Pipe-line systems
    • A62C35/62—Pipe-line systems dry, i.e. empty of extinguishing material when not in use
    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C37/00—Control of fire-fighting equipment
    • A62C37/50—Testing or indicating devices for determining the state of readiness of the equipment

Definitions

  • This invention relates to water spray systems, and particularly, though not exclusively, to water spray systems for aircraft.
  • known water spray systems discharge a fine spray into the cabin via an array of spray outlet nozzles.
  • the water may be carried on the aircraft (on-board system) or delivered from a fire appliance or other external source.
  • the water droplets forming the spray have several beneficial effects. They provide an infra-red radiation barrier protecting passengers and crew, improve visibility within the cabin and absorb toxic gases which congregate in the upper zone of the cabin, enabling passengers to breathe more easily.
  • the spray also has a cooling effect on the gas cloud near the roof of the cabin, slowing its progagation and reducing the risk of flash-over ignition. Also, the spray wets combustible material (furnishings etc.) delaying their ignition, and has a cooling effect on the interior surface of the aircraft wall. Notwithstanding these beneficial effects, existing water spray systems have serious drawbacks.
  • the fuselage could separate into discrete sections, and this could compromise the operational integrity of the entire water spray system.
  • a water spray system comprising a water storage vessel, at least one spray outlet nozzle connected to the water storage vessel and a pyrotechnic gas source for pressurizing the water storage vessel enabling water in the vessel to be discharged via the at least one spray outlet nozzle.
  • the pyrotechnic gas source may comprise a pyrotechnic material (e.g. an alkali metal azide, such as sodium azide) and an oxidizing agent (e.g. an alkali metal chlorate or perchlorate) .
  • a pyrotechnic material e.g. an alkali metal azide, such as sodium azide
  • an oxidizing agent e.g. an alkali metal chlorate or perchlorate
  • a water spray system comprising a water storage vessel, at least one spray outlet nozzle connected to the water storage vessel, means responsive to a control signal for pressurizing the water storage vessel enabling water stored in the vessel to be discharged via the at least one spray outlet nozzle and processing means for generating the control signal in response to input signals derived from different respective sources.
  • a water spray system comprising a water storage vessel, at least one spray outlet nozzle connected to the water storage vessel, means for pressurizing the water storage vessel enabling water stored in the vessel to be discharged via the at least one spray outlet nozzle and an exhaust valve operable to vent the water stored in the vessel.
  • a water spray system comprising a water storage vessel, at least one spray outlet nozzle connected to the water storage vessel and means for pressurizing the water storage vessel enabling water in the vessel to be discharged via the at least one spray outlet nozzle to a respective zone and wherein the at least one spray outlet nozzle so directs the spray as to enhance the residence time of water droplets in the spray in an upper region of a zone.
  • the at least one spray outlet nozzle may be directed upwardly and/or laterally. By this means, less water is required to achieve the desired effect.
  • a water spray system comprising a plurality of water spray sub-systems each comprising a water storage vessel, at least one spray outlet nozzle connected to the water storage vessel and means for pressurizing the water storage vessel enabling water in the vessel to be discharged via the at least one spray outlet nozzle, wherein each sub-system operates independently of the others to supply spray to a respective zone.
  • the water spray system has particular, though not exclusive, application to aircraft, each said zone being a respective section of the aircraft cabin.
  • a water spray system comprising a water storage vessel, at least one spray outlet nozzle connected to the water storage vessel and means for pressurizing the water storage vessel enabling water stored in the vessel to be discharged via the at least one spray outlet nozzle to a zone, wherein the at least one spray outlet nozzle is operable in each of three distinct modes; a sealed mode, enabling pressure testing to be carried out up to a first predetermined pressure, a low flow mode operable in response to a water supply pressure exceeding the first predetermined pressure, but less than a second predetermined pressure, and a high flow mode operable in response to a water supply pressure exceeding the second predetermined pressure.
  • the invention also relates to a spray outlet nozzle defined in accordance with the sixth aspect of the invention.
  • a method for connecting a water spray system having a water storage vessel to an external water supply system including the steps of penetrating a wall of the water storage vessel whereby to simultaneously connect the interior of the vessel to the external supply system via the penetration hole formed in the supply vessel.
  • the wall of the water supply vessel may be penetrated by a remotely launched penetration device which may be coupled to the external supply system by means of a flexible hose.
  • FIG. 1 is a schematic representation of a water spray sub-system in accordance with one aspect of the invention
  • Figure 2 shows a longitudinal cross-sectional view through an active vent in the open and closed conditions thereof
  • FIG 3 illustrates the manner by which an external water supply system may be coupled to the sub-system illustrated in Figure 1;
  • Figure 4 shows a longitudinal cross-sectional view through a three-mode spray outlet nozzle
  • Figure 5 shows a transverse cross-sectional view through the fuselage of an aircraft and illustrates how the spray outlet nozzles are arranged within the aircraft cabin.
  • the aircraft fuselage may sustain severe damage and may separate into several discrete sections.
  • the system may consist of a number of independent sub-systems, each being associated with a respective section of the fuselage, each section typically containing 20 to 30 seats.
  • FIG. 1 of the drawings gives a schematic representation of one such sub-system.
  • This comprises a water supply tank l which is connected, via a supply main 2, to several branch pipes 4 arranged at intervals along the fuselage.
  • the supply tank is pressurised with air from an air pressure bottle 5, causing water to be discharged to the interior of the cabin via a respective set of spray outlet nozzles, e.g. 6, 6 M , 6" ' , connected to each branch pipe 4.
  • a respective set of spray outlet nozzles e.g. 6, 6 M , 6" '
  • pyrotechnic gas source has the advantage that gas is generated only when it is needed and so gas leakages are eliminated.
  • the pyrotechnic source may be arranged to burn in a controlled manner, tailored to maintain a constant pressure in the ullage reservoir of the supply tank thereby providing a uniform flow of water to the outlet nozzles throughout the discharge.
  • the pyrotechnic material might typically comprise a pyrotechnic material such as an alkali metal azide (e.g. sodium azide) and an oxidizing agent (e.g. an alkali metal chlorate or perchlorate) .
  • the source of pressurised gas is connected to the tank by means of a suitable control valve 7 (e.g. a solenoid valve) which is effective to release gas into the tank in response to a control signal I received from a central control unit 8 for the sub-system.
  • a pyrotechnic gas source would have a pyrotechnic igniter which would be activated in response to the control signal I .
  • the central control unit 8 receives input signals from several different sources.
  • One of the input signals Is is produced by one or more smoke detectors 9 whenever the level of smoke detected within the respective section of cabin exceeds a predetermined threshold. To that end, a smoke detector would normally be located centrally within the cabin, at ceiling level.
  • Another input signal I is produced by a so-called
  • g-force M sensor 10 (which may be common to all the sub-systems) in response to the excessively high loads which occur during a crash.
  • I are aircraft system signals which denote respectively that the aircraft is in a "wheels-down" mode and is at ground altitude.
  • the control unit 8 also receives command signals If and Ig which are set manually by the flight deck crew and the flight cabin crew respectively.
  • any sub-system may be activated either by the cabin crew (i.e. I high), by depression of, for instance, "panic buttons" located at strategic positions around the respective section of cabin or by an output from a respective smoke detector 9 indicating a high level of smoke in the associated cabin section (i.e. Is high).
  • each sub-system would be enabled automatically (independently of the action of the flight crew) and, as before, could then be activated in response to an output from a smoke detector 9, or by the action of cabin crew.
  • control signal I may be inhibited unless the "wheels-down" input signal I W and the altitude signal I3 have been received.
  • the flight crew has the ability to over-ride the control unit 8 and thereby activate the water spray sub-systems directly.
  • the respective supply tank 1 can be vented externally in order to minimise damage to the cabin.
  • each tank may be fitted with an active vent 11, such as a dump valve, for example.
  • FIG. 2 shows one embodiment of a dump valve.
  • the valve comprises a valve housing 20 fitted with a sealing piston 21 which is maintained in the closed position (shown on the left side of the drawing) by a ball lock 22 which is held in the locked condition by an actuator piston 23.
  • an explosive cartridge 24 is triggered by a suitable control signal, produced by the control unit 8 or directly by the crew, forcing the actuator piston 23 downwards thereby rapidly releasing the ball lock from the locked condition.
  • the pressure of water on the upstream side of the valve then forces the sealing piston 21 upwardly in the direction of arrow A (to the position shown on the right side of the drawing) so that the water in the supply tank is discharged via outlet openings 25.
  • a pressurised, on-board system would typically discharge water to the cabin at a pressure of about 1 to 7 bar (preferably 2 to 5 bar), and each sub-system would have a sufficient capacity to operate at this pressure for at least three minutes, by which time a fire appliance would have arrived at the scene.
  • the water supply system of the tender must be coupled to the on-board system of the aircraft without delay.
  • the lance has a barb 34 which is biased by the action of a spring 35 against the inner wall of the tank thereby to establish a fluid-tight seal around the penetration opening formed by the lance tip.
  • the inner wall of the supply tank 1 may be made from a self-sealing material which swells up when wet to form a seal around the penetration hole.
  • the water supply system provided by the tender operates at a much higher pressure than does the on-board water spray system.
  • the spray outlet nozzles of the on-board system may be adapted to operate in two different flow modes; a "low flow” mode, which is adopted when water is being supplied by the (low pressure - typically from 2 to 7 bar) on-board system and a "high flow” mode, which is adopted when water is being supplied by the (high pressure - typically from 7 to 15 bar) tender supply system.
  • each nozzle should permit routine pneumatic testing in order to confirm the integrity of the pipe-work system, and such testing should be carried out without releasing water from the system.
  • each nozzle is sealed to a low pressure, perhaps a few tenths of a bar, which is high enough to enable pressure testing to be carried out, yet is sufficiently less than the "low flow" mode supply pressure.
  • each nozzle is capable of operating in each of three distinct modes; that is, a sealed mode, enabling pressure testing to be carried out up to a first predetermined threshold pressure, a low flow mode operable in response to a water supply pressure which exceeds the first predetermined threshold pressure, but is less than a second predetermined threshold pressure, and a high flow mode operable in response to a water pressure which exceeds the second predetermined threshold pressure.
  • a nozzle may incorporate a switchable valve which interconnects the nozzle inlet and the nozzle outlet, enabling the nozzle to switch between the sealed, low flow and high flow modes in response to a respective pressure change at the nozzle inlet.
  • the valve may respond directly to a change of pressure at the nozzle outlet or, alternatively, may switch between the three modes in response to an output from a pressure transducer arranged to monitor the pressure at the nozzle inlet.
  • each outlet nozzle is fitted with a trim panel and this is arranged to be ejected from the nozzle by the increase of pressure which takes place when the nozzle switches from the sealed mode to the low flow mode.
  • the ejection of the trim panel may be the means for switching from the sealed mode to the low flow mode.
  • Figure 4 shows one embodiment of a switchable spray outlet nozzle.
  • the nozzle comprises a cylindrical nozzle body 40 having an inlet 41 and a spray outlet orifice 42 provided in an end wall 43 of the nozzle body.
  • a trim panel 44 is fitted over the end of the nozzle body, as shown, and is sealed thereto by an "0 M -ring 45.
  • a first predetermined pressure typically a few tenths of a bar, which is adequate to allow pressure testing to be carried out, the trim panel is retained in place by the "0"-ring and a flow of water is prevented - the sealed mode.
  • the trim panel 44 will be ejected allowing water to flow around a cylindrical valve member 46 and to exit the outlet orifice 42 as a spray.
  • the valve member 46 has a helical, ribbed formation 47 which induces swirling as the water flows toward the outlet orifice creating a spray in the form of a hollow cone.
  • the valve member is supported within the nozzle body by a circumferentially apertured support member 48. To that end, the valve member has an axial shaft 49 located in a cylindrical socket 50 of the support member. A volume 51 of oil trapped at the closed end of the socket contains a gas bubble 52. If the pressure of water is less than a second predetermined pressure, but greater than the first predetermined pressure, the axial position of the valve member 46 in the.nozzle body 40 is such that a restrictor 53, in the form of a pip at the end of the valve member, partially blocks the outlet orifice (as shown in the drawing) and so restricts the flow of water - the low flow mode.
  • the inlet pressure exceeds the second predetermined pressure, the pressure of water acting on the valve member compresses the gas bubble 52 thereby displacing the valve member towards the inlet and retracting the restrictor from the outlet orifice, allowing a greater flow of water - the high flow mode.
  • the water flow rate and the size of the water droplets in the spray will be determined by the dimensions of the nozzle outlet orifice.
  • the passenger cabin of an aircraft would be fitted with a large number of spray outlet nozzles and these may have a range of different orifice sizes.
  • the size of orifice selected in a particular case would depend on the location of the nozzle within the cabin. For example, a nozzle positioned in relatively close proximity to combustible material, e.g. below the overhead luggage compartments, would have a relatively large outlet orifice giving a corresponding high flow rate and producing spray containing relatively large water droplets.
  • Combustion products generated during a fire inside the cabin of an aircraft include toxic gases, such as carbon monoxide, hydrogen fluoride, hydrogen chloride and hydrogen cyanide.
  • a further aspect of the present invention provides a water spray system for use in an aircraft in which a plurality of spray outlet nozzles are arranged to direct the spray whereby to enhance the residence time of water droplets in the upper region of the aircraft cabin.
  • the nozzles may be so arranged as to direct the spray laterally and/or upwardly.
  • nozzles are mounted to either side of the cabin centre line and, in the case of the cabin having more than one aisle, nozzles may be mounted to either side of each aisle.
  • the nozzles may be mounted directly on the structure of the luggage compartments themselves. However, the compartments could collapse during a crash landing and so it is preferred that the nozzles (e.g. N3,N4) be mounted on the airframe, preferably in the corner spaces defined by the roof panel R of the cabin and the inwardly facing sides of the overhead lockers on opposite sides of the aisle.
  • Additional nozzles may also be provided, at a lower level, in order to douse the furnishings and passengers in the immediate vicinity.
  • the spray produced by the aforementioned configuration of nozzles resides in the upper region U for a- time sufficient to permit enhanced absorption of the combustion gases, thereby significantly reducing the risk to passengers below, and at the same time reducing the quantity of water required.
  • the water may contain a suitable additive.
  • the additive may also be used as an anti-freeze.
  • the supply tank could be fitted with a low energy immersion heater.

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  • Health & Medical Sciences (AREA)
  • Public Health (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)

Abstract

L'invention se rapporte à un système de vaporisation d'eau pour avions, qui comprend plusieurs buses d'émission de jets (6', 6'', 6''') réparties dans toute la cabine passagers de l'avion et couplées à un réservoir d'eau (1). Une source de gaz pyrotechnique (5) est utilisé pour pressuriser l'eau stockée dans le réservoir (1). Le système peut se composer de plusieurs sous-systèmes, qui sont chacun associés à une section respective de la cabine de l'avion et qui sont actionnable indépendemment les uns des autres. La source de gaz pyrotechnique (5) peut être actionnée par un signal de commande (IO) produit par une unité de commande (8) en réponse à différents signaux d'entrée et le réservoir d'eau ou chaque réservoir d'eau est équipé d'une soupape d'évacuation (11) servant à vider l'eau du réservoir au cas où le système est actionné par inadvertance. Les buses d'émission de jets peuvent fonctionner selon différents modes et peuvent être dirigés de façon à accroître le temps de séjour des gouttelettes d'eau dans une partie supérieure (U) de la cabine. Le système ne peut être couplé à une source d'alimentation externe au moyen d'un projectile pénétrant lancé depuis un lieu éloigné.
PCT/GB1990/001767 1989-11-17 1990-11-16 Ameliorations apportees a des systemes de vaporisation d'eau WO1991007208A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9210132A GB2256366A (en) 1989-11-17 1992-05-11 Improvements relating to water spray systems

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB898926086A GB8926086D0 (en) 1989-11-17 1989-11-17 Improvements relating to water spray systems
GB8926086.3 1989-11-17

Publications (2)

Publication Number Publication Date
WO1991007208A2 true WO1991007208A2 (fr) 1991-05-30
WO1991007208A3 WO1991007208A3 (fr) 1991-11-28

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Family Applications (1)

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PCT/GB1990/001767 WO1991007208A2 (fr) 1989-11-17 1990-11-16 Ameliorations apportees a des systemes de vaporisation d'eau

Country Status (4)

Country Link
EP (1) EP0500666A1 (fr)
CA (1) CA2068720A1 (fr)
GB (1) GB8926086D0 (fr)
WO (1) WO1991007208A2 (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992022353A1 (fr) * 1991-06-19 1992-12-23 Sundholm Goeran Procede et materiel de lutte contre les incendies
WO1993012839A1 (fr) * 1991-12-20 1993-07-08 Kidde-Graviner Limited Appareillage pour eteindre ou combattre les incendies dans les soutes a cargaison d'avions
WO1994008659A1 (fr) * 1992-10-20 1994-04-28 Sundholm Goeran Procede et installation de lutte contre le feu
GB2275871A (en) * 1993-03-10 1994-09-14 Graviner Ltd Kidde Aircraft fire preventions and extinguishing system
EP0667795A1 (fr) * 1993-07-12 1995-08-23 Invention Technologies Pty, Ltd. Appareil d'extinction d'incendie
FR2742121A1 (fr) * 1995-12-12 1997-06-13 Intertechnique Sa Dispositif humidificateur pour cabine d'aeronef
AU689118B2 (en) * 1993-07-12 1998-03-26 Invention Technologies Pty. Ltd. Fire extinguishing apparatus & method
EP1283065A2 (fr) * 2001-07-30 2003-02-12 The Boeing Company Système et procédé de suppression d'incendie pour l'intérieur d'un avion - protection contre le feu pour conteneur de déchets
DE102005029226A1 (de) * 2005-06-23 2006-12-28 Airbus Deutschland Gmbh Zuführen eines Mehrkomponentenstrahls zu einem Gesichtsfeld eines Benutzers
AU2004222663B2 (en) * 2003-03-19 2008-01-03 Siemens Mobility Austria Gmbh Sprinkler installation for railway vehicles
US8113195B2 (en) 2005-06-23 2012-02-14 Airbus Operations Gmbh Bringing a multi-component jet into the visual field of a user
WO2022015507A1 (fr) * 2020-07-17 2022-01-20 The Boeing Company Méthodologie de lutte contre l'incendie dans une cabine adaptative

Citations (13)

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Publication number Priority date Publication date Assignee Title
FR826882A (fr) * 1936-08-13 1938-04-12 Procédé et dispositif automatique pour l'extinction des combustions violentes, notamment des feux de poudre
FR893170A (fr) * 1942-12-08 1944-06-01 Perfectionnements aux installations fixes pour l'extinction des incendies
US2566235A (en) * 1942-12-18 1951-08-28 Graviner Manufacturing Co Fire preventing means for power plants, particularly on aircraft
DE922747C (de) * 1944-05-09 1955-01-24 Messerschmitt Boelkow Blohm Feuerloeschanlage fuer Flugzeuge
US2857005A (en) * 1957-07-19 1958-10-21 Boeing Co Fire fighting apparatus
US3017894A (en) * 1960-04-04 1962-01-23 Futurecraft Corp Valve
US3830307A (en) * 1970-05-11 1974-08-20 Parker Hannifin Corp Fire prevention and/or suppression system
DE2701935A1 (de) * 1977-01-19 1978-07-20 Dynamit Nobel Ag Druckgasbetaetigtes schaltelement
US4289277A (en) * 1980-04-07 1981-09-15 Premier Industrial Corporation Constant pressure nozzle with modulation effect
US4319640A (en) * 1979-12-06 1982-03-16 The United States Of America As Represented By The Secretary Of The Army Gas generator-actuated fire suppressant mechanism
US4434855A (en) * 1982-03-30 1984-03-06 The United States Of America As Represented By The Secretary Of The Navy Sprinkler valve
EP0170749A1 (fr) * 1981-11-25 1986-02-12 William Armand Enk Système de protection contre l'incendie pour des avions
GB2181050A (en) * 1985-10-05 1987-04-15 Thomas Cassie Faulds Aircraft fire control

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR826882A (fr) * 1936-08-13 1938-04-12 Procédé et dispositif automatique pour l'extinction des combustions violentes, notamment des feux de poudre
FR893170A (fr) * 1942-12-08 1944-06-01 Perfectionnements aux installations fixes pour l'extinction des incendies
US2566235A (en) * 1942-12-18 1951-08-28 Graviner Manufacturing Co Fire preventing means for power plants, particularly on aircraft
DE922747C (de) * 1944-05-09 1955-01-24 Messerschmitt Boelkow Blohm Feuerloeschanlage fuer Flugzeuge
US2857005A (en) * 1957-07-19 1958-10-21 Boeing Co Fire fighting apparatus
US3017894A (en) * 1960-04-04 1962-01-23 Futurecraft Corp Valve
US3830307A (en) * 1970-05-11 1974-08-20 Parker Hannifin Corp Fire prevention and/or suppression system
DE2701935A1 (de) * 1977-01-19 1978-07-20 Dynamit Nobel Ag Druckgasbetaetigtes schaltelement
US4319640A (en) * 1979-12-06 1982-03-16 The United States Of America As Represented By The Secretary Of The Army Gas generator-actuated fire suppressant mechanism
US4289277A (en) * 1980-04-07 1981-09-15 Premier Industrial Corporation Constant pressure nozzle with modulation effect
EP0170749A1 (fr) * 1981-11-25 1986-02-12 William Armand Enk Système de protection contre l'incendie pour des avions
US4434855A (en) * 1982-03-30 1984-03-06 The United States Of America As Represented By The Secretary Of The Navy Sprinkler valve
GB2181050A (en) * 1985-10-05 1987-04-15 Thomas Cassie Faulds Aircraft fire control

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992022353A1 (fr) * 1991-06-19 1992-12-23 Sundholm Goeran Procede et materiel de lutte contre les incendies
US5713417A (en) * 1991-06-19 1998-02-03 Sundholm; Goeran Method and equipment for fire fighting
WO1993012839A1 (fr) * 1991-12-20 1993-07-08 Kidde-Graviner Limited Appareillage pour eteindre ou combattre les incendies dans les soutes a cargaison d'avions
US5676210A (en) * 1992-10-20 1997-10-14 Sundholm; Goeran Method and installation for fighting fire
WO1994008659A1 (fr) * 1992-10-20 1994-04-28 Sundholm Goeran Procede et installation de lutte contre le feu
GB2275871A (en) * 1993-03-10 1994-09-14 Graviner Ltd Kidde Aircraft fire preventions and extinguishing system
AU689118B2 (en) * 1993-07-12 1998-03-26 Invention Technologies Pty. Ltd. Fire extinguishing apparatus & method
US6637518B1 (en) * 1993-07-12 2003-10-28 Invention Technologies Pty. Ltd. Fire extinguishing apparatus
EP0667795A1 (fr) * 1993-07-12 1995-08-23 Invention Technologies Pty, Ltd. Appareil d'extinction d'incendie
EP0667795A4 (fr) * 1993-07-12 1996-04-10 Invention Tech Pty Ltd Appareil d'extinction d'incendie.
FR2742121A1 (fr) * 1995-12-12 1997-06-13 Intertechnique Sa Dispositif humidificateur pour cabine d'aeronef
US5944284A (en) * 1995-12-12 1999-08-31 Intertechnique Humidifier system for an aircraft cabin
EP0779207A1 (fr) 1995-12-12 1997-06-18 Intertechnique Dispositif humidificateur pour cabine d'aéronef
EP1283065A2 (fr) * 2001-07-30 2003-02-12 The Boeing Company Système et procédé de suppression d'incendie pour l'intérieur d'un avion - protection contre le feu pour conteneur de déchets
EP1283065A3 (fr) * 2001-07-30 2004-01-21 The Boeing Company Système et procédé de suppression d'incendie pour l'intérieur d'un avion - protection contre le feu pour conteneur de déchets
US6899184B2 (en) 2001-07-30 2005-05-31 The Boeing Company Fire suppression system and method for an interior area of an aircraft lavatory waste container fire protection
AU2004222663B2 (en) * 2003-03-19 2008-01-03 Siemens Mobility Austria Gmbh Sprinkler installation for railway vehicles
AT504360B1 (de) * 2003-03-19 2008-05-15 Siemens Transportation Systems Sprinkleranlage für schienenfahrzeuge
DE102005029226A1 (de) * 2005-06-23 2006-12-28 Airbus Deutschland Gmbh Zuführen eines Mehrkomponentenstrahls zu einem Gesichtsfeld eines Benutzers
DE102005029226B4 (de) * 2005-06-23 2010-09-23 Airbus Deutschland Gmbh Zuführen eines Freistrahls zu einem Gesichtsfeld eines Benutzers
US8113195B2 (en) 2005-06-23 2012-02-14 Airbus Operations Gmbh Bringing a multi-component jet into the visual field of a user
WO2022015507A1 (fr) * 2020-07-17 2022-01-20 The Boeing Company Méthodologie de lutte contre l'incendie dans une cabine adaptative

Also Published As

Publication number Publication date
EP0500666A1 (fr) 1992-09-02
WO1991007208A3 (fr) 1991-11-28
GB8926086D0 (en) 1990-01-10
CA2068720A1 (fr) 1991-05-18

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