• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The drainage mast (13) for discharging fluids from an aircraft comprises a fairing (21) comprising a base (33) including an upstream section (33a) for attachment to an outer surface (17) of the aircraft aircraft and a downstream section (33b), and a discharge nozzle (35) comprising a discharge end (39) opening out of said fairing (21), said discharge nozzle (35) projecting from said downstream section (33b) in a first direction relative to said base (33), said base (33) and said discharge nozzle (35) defining a through-tube cavity (43) extending from said upstream section (33a); ) to said discharge end (39). The shroud (21) further comprises an air guiding profiled section (37) projecting from said downstream section (33b), in a direction opposite to said first direction, and configured to orient a mass of air incident on said profiled section (37) towards said discharge end (39).
    公开号:FR3021028A1
    申请号:FR1401095
    申请日:2014-05-15
    公开日:2015-11-20
    发明作者:Eugene Wielgosz
    申请人:Dassault Aviation SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a drainage mast for discharging fluids from an aircraft, said drainage mast comprising a fairing intended to be fixed on an outer surface of the aircraft, said fairing comprising: a base comprising an upstream section intended to be fixed on said outer surface of the aircraft and a downstream section, and a discharge nozzle comprising a discharge end opening outside said fairing, said nozzle discharge projecting from said downstream section in a first direction relative to said base, said base and said discharge nozzle defining a through-tubular cavity, said tubular cavity extending from said upstream section to said discharge end. It applies in particular to the evacuation of wastewater from an aircraft in flight.
    [0002] This wastewater results in particular from the evacuation of sinks from the aircraft and the melting of ice cubes contained in ice trays in which beverages are stored. To achieve the evacuation of these wastewater, it is known to connect the evacuation of sinks and ice cube drawers to a drain circuit extending inside the aircraft to the fuselage of the aircraft. The drain circuit is extended by a drainage mast, fixed on the skin of the fuselage outside the aircraft and allowing the evacuation of wastewater outside the aircraft. The aircraft is for example provided with two drainage masts: a first mast, located at the front of the aircraft, receives the wastewater from sinks and ice drawers, and a second mast, located at the rear of the aircraft, receives only wastewater from sinks. Typically, a drainage mast comprises a fairing fixed on the skin of the fuselage of the aircraft and a drainage duct extending inside the fairing between an upstream end connected to the emptying circuit of the aircraft and a downstream end. by which the water is discharged outside the aircraft. Water from the sink drain is discharged in the form of a flow of more or less water, flowing sporadically depending on the use of sinks. Conversely, water from ice drawers is evacuated in the form of a permanent drip flow that is similar to a seepage.
    [0003] To facilitate the flow of this seepage, a flow of air, for example from a permanent leak from the pressurized cabin, is injected into the drip line to the drain line. In addition, the wastewater tends to freeze during its evacuation through the drainage duct, because of the low temperature of the atmosphere around the aircraft in flight (of the order of -55 ° C to cruise altitude). In an attempt to solve this problem, it is known to provide the drainage duct with heating elements, comprising for example a heating wire wound around the drainage duct. The electric power supplying these heating elements must be limited, in order to avoid any risk of overheating when the aircraft is on the ground, which could lead to a melting of the fairing. Depending on the installation conditions (power supply of the mat under 28V for example), this solution does not give full satisfaction. Indeed, although it allows to limit the freeze of wastewater from the sink drain, this solution does not prevent ice accretion during the evacuation of water from ice drawers , flowing drip. The freezing of wastewater generates an accretion of ice in the drainage duct or at the outlet of it. This accretion can lead to clogging of the drainage duct and poor drainage of wastewater. In addition, the ice cubes accumulated at the outlet of the drainage duct can go up along the fairing of the drainage mast to the fuselage of the aircraft. The ice cubes can also come off in flight, hit the fuselage of the aircraft and damage the aircraft. This gel is all the more marked as the flow rate in the drainage duct is low, and therefore more marked for the water from the ice drawers than those resulting from the evacuation of the sinks. An object of the invention is therefore to provide a drainage mast for the evacuation of wastewater from an aircraft that allows effective evacuation of wastewater, avoiding the freezing of these waters and the accretion of ice on the mast. For this purpose, the invention relates to a drainage mast of the aforementioned type, characterized in that said fairing further comprises a profiled air guide section projecting from said downstream section, in a direction opposite to said first direction said profiled section being configured to orient a mass of air incident on said profiled section toward said discharge end. The drainage mast may comprise one or more of the following features, taken in isolation or in any technically possible combination: said profiled section and said evacuation nozzle form a shell projecting from said downstream section of another of said upstream section; - The drainage mast further comprises at least one drainage duct of a fluid, said drainage duct extending inside said tubular cavity; said drainage duct comprises an upstream end intended to be connected to a fluidic circuit of the aircraft when said drainage mast is fixed on said outer surface of the aircraft and a downstream end intended to evacuate a fluid from said fluid circuit to outside said fairing, through said discharge end; - said downstream end and said discharge end are flush; said downstream end is configured to discharge said fluid outside said fairing in a second direction, said first direction and said second direction forming between them an angle greater than or equal to 00; - The drainage mast comprises heating means of said drainage duct; said heating means cover said downstream end; said heating means comprise at least one heating wire wound around said drainage duct; said at least one heating wire is brazed on said drain duct; the drainage mast comprises electrical power supply means capable of electrically supplying said heating means with a first power when the aircraft is on the ground and with a second power, strictly greater than said first power, when the aircraft is in operation; flight ; said heating means comprise a first and a second heating wire wound around said drain duct, and said supply means are adapted to electrically supply the first heating wire excluding the second heating wire when the aircraft is on the ground and feeding the first and second heating wires when the aircraft is in flight; each of said first and second heating wires is wound around said drainage duct in turns, and in the turns of said first wire and the turns of said second wire are alternated around said drainage duct; the drainage mast comprises a peripheral air channel extending inside said tubular cavity around said drainage duct. According to one embodiment, said heating means are thermoregulated.
    [0004] The subject of the invention is also a method for draining a fluid flowing in an emptying circuit of the aircraft to an opening in a fuselage of the aircraft, said method being characterized in that it comprises: - supplying a drainage mast according to the invention, said drainage mast being fixed to said fuselage in the extension of said draining circuit, - evacuation of said fluid to the outside of the aircraft through said cavity tubular by said discharge end. According to a second aspect, the invention relates to a drainage mast for discharging fluids from an aircraft, said drainage mast comprising: a fairing intended to be fixed on an outer surface of the aircraft, said fairing comprising a tubular cavity therethrough, - at least one drainage duct of a fluid, said drainage duct extending inside said tubular cavity, - means for heating said drainage duct, the drainage mast being characterized in that it comprises power supply means adapted to electrically supply said heating means with a first power when the aircraft is on the ground and with a second power, strictly greater than said first power, when the aircraft is in flight. According to this second aspect, the fairing does not necessarily include a profiled section of air guide configured to guide a mass of air incident on the profiled section towards a discharge end. The drainage mast may comprise one or more of the following characteristics, taken in isolation or in any technically possible combination: said heating means comprise first and second heating wires wound around said drainage duct; said means power supply are adapted to electrically power the first heating wire excluding the second heating wire when the aircraft is on the ground and to feed the first and second heating son when the aircraft is in flight, - said means of power supply comprises a power source, said first and second heating wires being connected in parallel with said power supply, said power supply means comprising a switchable switch between an open position, wherein said second wire heater is not electrically connected to the power source and a closed position, wherein said first and second heating wires are electrically connected to the power source, - the power supply means comprises control means for determining whether the aircraft is in flight or at ground and switch the switch to its open position when the aircraft is on the ground and in its closed position when the aircraft is in flight.
    [0005] The invention will be better understood on reading the description which will follow, given solely by way of example and with reference to the drawings in which: FIG. 1 is a diagram illustrating a set of wastewater drainage d an aircraft comprising a drainage mast according to one embodiment of the invention; - Figure 2 is a longitudinal sectional view of the drainage mast of Figure 1; - Figure 3 is a side view, in perspective, of a section of the drainage mast of Figure 2; - Figure 4 is a perspective view of a drainage pylon according to one embodiment of the invention; and FIG. 5 is a diagram of a power supply circuit for heating means of the drainage mast of FIG. 2. FIG. 1 shows a set 1 of drainage of wastewater from an aircraft 3. The drainage assembly 1 is intended for the evacuation of the water flowing from a sink 5 of the aircraft 3 and water resulting from the melting of ice cubes contained in ice trays 7 of the aircraft 3, in which are stored drinks. The drainage assembly 1 comprises a drain circuit 11 and a drainage mast 13. The drain circuit 11 is fluidly connected to an outlet of the sink 5 and to the ice cube trays 7, and extends inside the aircraft to an opening 15 formed in the fuselage 17 of the aircraft 3. The drainage mast 13 is fixed on the skin of the fuselage 17, at the opening 15. The drainage mast 13 extends the drain circuit 11 outside the fuselage 15 of the aircraft and thus allows the discharge of the wastewater flowing from the sink 5 and the ice cube trays 7, via the drain circuit 11, to the outside of the aircraft 3. As can be seen in FIGS. 2 to 4, the mast 13 of drainage comprises a fairing 21 intended to be fixed on the skin of the fuselage 17, at the opening 15, and a plate 22 for fixing the shroud 21 on the skin of the fuselage 17. The drainage mast 13 further comprises a duct 23 water drainage received in a tubular cavity formed in the shroud 21 and an air channel 25.
    [0006] The drainage mast 13 further comprises means 27 for heating the drainage conduit 23 and means 29 for supplying power to the heating means 27. The shroud 21 comprises a base 33, a discharge nozzle 35 and a profiled section 37 for guiding air.
    [0007] The base 33 is intended to be fixed on the fuselage of the aircraft by projecting from this fuselage outside the aircraft. When the drainage mast 13 is fixed on the fuselage of the aircraft, the base 33 extends in an elongation direction with an angle α of between 55 ° and 65 °, for example equal to 600, with respect to the fuselage surface.
    [0008] The base 33 comprises an upstream section 33a and a downstream section 33b. The upstream section 33a is intended to be fixed on the skin of the fuselage 17, by means of the mounting plate 22. The downstream section 33b protrudes from the upstream section 33a, away from the fuselage 17 when the drainage mast 13 is fixed on the fuselage 17.
    [0009] The discharge nozzle 35 protrudes from the downstream section 33h in a first direction relative to the base 33, to a discharge end 39. The base 33 and the discharge nozzle 35 define a through-tubular cavity 43 powered by cabin air. The cavity 43 has a bent shape. The cavity 43 extends through the base 33 and the discharge nozzle 35 from the upstream section 33a and ends with a convergent section to join the discharge end 39. Through the cavity 43 is generated a channel of tubular air blown at the outlet of the portion 23b of the drainage duct, which isolates any seepage of water from the cold structure of the discharge nozzle 35. The conduit 23 allows in particular an evacuation of wastewater flowing from the 5 and the ice drawers 7, via the drain circuit 11, through the opening 15 and the discharge end 39, outside the aircraft 3. When the drainage mast 13 is fixed at the aircraft 3, the first direction is oriented towards the rear of the aircraft 3. Thus, when wastewater is discharged through the discharge end 39, this evacuation takes place in a direction opposite to the direction of flight of the aircraft, which facilitates the evacuation of waste water outside the drainage mast 13. The profiled section 37 protrudes from the downstream section 33b in a direction opposite to the first direction. When the drainage mast 13 is attached to the aircraft 3, the profiled section 37 thus extends the evacuation nozzle towards the front of the aircraft 3.
    [0010] The profiled section 37 has a shape tapering towards its free end. The outer surface of the profiled section 37 is configured to orient a mass of air A incident on the guide section towards the discharge end 39 when the aircraft 3 is in flight. Indeed, in the absence of such a profiled section, the flow of air in the vicinity of the exhaust end 39, when the aircraft 3 is in flight, is a turbulent flow, which disrupts the channel blown air from the cavity 43 and tends to drive the water droplets exiting the drainage mast 13 via the discharge end 39 to the fairing 21 or to the fuselage 17 and thus to cause a recollement and a gel of these droplets on the shroud 21 or on the fuselage 17. The profiled section 37 is thus configured to stabilize the flow of air incident on the drainage mast 13 and make this flow as turbulent as possible to the right of the end 39. The base 33 of the drainage mast 13 is for example a profile NACA0012. For example, the profile has a rope of 86mm and a thickness of 22mm. Furthermore, the discharge nozzle 35 and the profiled section 37 form a shell 44 which protrudes from the downstream section 33b on either side of the base 33. The shell 44 is for example a profile NACA0012. For example, the profile forming the shell has a rope between 200mm and 250mm, including 230mm and a thickness between 30mm and 40mm, including 34mm. The fairing 21, that is to say the base 33 and the shell 44, is formed of two parts assembled along a longitudinal plane. The two pieces are for example made in Ultem CRS 5301/5311. They are for example assembled by gluing. The length of the profiled section 37 protruding beyond the base 33 taken along the axis of the profiled section 37 is between 50% and 60% of the width of the base. The mounting plate 22 is a plate comprising an inner face 22a intended to be fixed on the upstream section 33a of the base 33 and an outer face 22b intended to be fixed on the fuselage 17. The mounting plate 22 comprises two through openings 45 and 46 for the passage of conduits. The mounting plate 22 further comprises a connection pad 48 protruding from the outer face 22b of the mounting plate 22 to the outside of the mast 13 drainage. The connection pad 48 is intended to receive electrical conductors 49 for the power supply of the heating means 27. The fixing plate 22 is for example fixed by gluing on the fairing 21.
    [0011] The water drainage conduit 23 is received in the tubular cavity 43. It extends partially inside the tubular cavity 43, between an upstream portion 23a intended to be fluidly connected to the circuit 11 for emptying the aircraft. when the mast 13 is fixed on the aircraft 3, and a downstream end 23b for a discharge of water flowing in the conduit 23 towards the outside of the conduit 23. The conduit 23 has a bent shape.
    [0012] The duct 23 has, for example, a cross section of between 45 and 55 mm 2, for example a tube with an outside diameter of 9.52 mm and a thickness of 0.71 mm, hence a cross section of approximately 50 mm 2. . Advantageously, the downstream end 23b of the duct 23 and the discharge end 39 of the nozzle 35 are flush.
    [0013] The downstream end 23b is configured to discharge the fluid water outside the shroud 21 in a second direction relative to the mast 13 drainage. The first direction and the second direction form between them an angle greater than or equal to 0 °, preferably strictly greater than 0 °, for example equal to 7 °. The upstream portion 23a protrudes from the upstream section 33a of the base 33, through the opening 45 of the mounting plate 22, in the extension of the base 33. This upstream portion 23a comprises a connection end 51 suitable for being connected to a corresponding end of the drain circuit 11. The upstream portion 23a is for example fixed to the plate 22 for fixing by brazing. The air channel 25 extends inside the tubular 43 around the duct 23. The air channel 25 is intended to allow a flow of a pressurized air volume coming from the inside of the aircraft. , through the opening 15, through the cavity 43 and its converging end to the discharge end 39, where the air flow is discharged outside the shroud 21. The evacuation of the air flow makes it possible to confine the water droplets and to avoid their gluing on the cold parts of the fairing.
    [0014] The air channel 25 is formed by a chamber 53 delimited by the inner wall of the cavity 43 and the outer wall of the duct 23, and by an air injection tube 55 intended for the injection of pressurized air in the chamber 53. The air injection tube 55 protrudes from the upstream section 33a of the base 33, through the opening 46 of the fixing plate 22, outside the fairing 21. The tube For example, the air injection 55 is attached to the solder plate 22. The air injection tube 55 comprises a connection end 57 adapted to be connected to a corresponding end of an air circuit of the aircraft. The air circuit comprises, for example, a duct connected to the pressurized cabin of the aircraft 7. The air injection tube 55 has, for example, a circular cross section of between 20 and 30 mm 2, for example a tube of outer diameter of 6.35 mm, wall thickness 0.46 mm and a through section of about 23 mm2.
    [0015] The heating means 27 are intended to heat the drainage duct 23, thereby preventing a freeze of the water circulating in this duct 23 on the internal walls of the duct 23 and at the outlet of the duct 23. The heating means 27 cover at least partially the outer surface of the conduit 23. Preferably, the outer surface portion of the conduit 23 covered by the heating means 27 includes the outer surface of the discharge end 39. Thus, this exhaust end 39 is heated directly by the heating means 27. The heating means 27 are electrically connected to the power supply means 29, visible in FIG. 5. The power supply means 29 comprise a voltage generator 61 located in the aircraft 3 and electrical conductors 63 electrically connecting the generator. voltage to the heating means 27. The power supply means 29 are adapted to electrically power the heating means 27 with a first power when the aircraft 3 is on the ground and with a second power, strictly greater than said first power, when the aircraft is in flight. Indeed, when the aircraft is in flight, the drainage mast 13 is subjected to an outside temperature of the order of -55 ° C., generally well below the temperature at which the drainage mast 13 is subjected when the aircraft is on the ground. Thus, a power required in flight to avoid a water gel on the inner walls of the conduit 23 and the exit of the conduit 23 could generate damage to the drainage mast 13 if it was applied to the ground. The power supply means 29 make it possible to heat the conduit 23 so as to reach at the discharge end 39 a first temperature when the aircraft is in flight, and a second temperature, lower than the first temperature, when the aircraft is on the ground. As illustrated in FIGS. 3 and 5, the heating means 27 advantageously comprise two heating wires 65, 66 wound around the duct 23, on the outer surface of the duct 23. The heating wires 65, 66 are electrically conductive, resistance wires respectively Rs01 and R, 01. These resistances R 'and Kol depend on the ambient temperature. The variation of these resistances Rs., And R 'with the temperature depends on the material of the heating wires 65, 66.
    [0016] Preferably, the heating wires 65, 66 are brazed to the outer surface of the duct 23, so as to ensure a better heat exchange between the heating wires 65, 66 and the duct 23. Each of the heating wires is wound around the duct 23 by forming turns.
    [0017] The turns of the first of the second wire are alternated around the conduit 23. Thus, the first and second heating son substantially cover the same portion of the outer surface of the conduit 23, and substantially heat the same portion of the outer surface of the conduit 23. Preferably, the winding of the turns is denser in an area of the surface of the conduit 23 next to the discharge end 39 than on the rest of the surface of the conduit 23. Thus, the linear power of heating is greater in this zone that on the rest of the duct surface, which provides, in the vicinity of the exhaust end 39, a higher temperature than that which would be obtained if the turns were wound in a regular manner around the duct 23.
    [0018] The power supply means 29 are configured to electrically supply the first heating wire 65 only when the aircraft is on the ground and to feed the two heating wires 65 and 66 when the aircraft is in flight. For this purpose, as shown diagrammatically in FIG. 5, the first and second heating wires 65, 66 are supplied in parallel by the voltage generator 61. The power supply means 29 also comprise a switch 69 switchable between a open position, wherein the second heating wire 66 is not electrically powered and a closed position, wherein the second heating wire 66 is electrically powered by the voltage generator 61. In the open and closed positions, the heating wire 65 is supplied by the voltage generator 61. The power supply means 29 further comprise control means 70 for determining whether the aircraft 3 is in flight or on the ground and switching the switch 69 to its open position when the aircraft 3 is on the ground and in its closed position when the aircraft 3 is in flight.
    [0019] Thus, when the aircraft 3 is on the ground, only the first heating wire 65 is energized and heats the conduit 23, whereas when the aircraft 3 is in flight, the first and second heating wires 65, 66 are both powered and both heat the conduit 23. To guard against damage when the ambient temperature is high, a skin thermostat 71 has been provided in the mat to allow a power cut of the heater 65 when the ambient temperature is greater than 15 ° vs.
    [0020] The voltage V generated by the voltage generator, the resistors R ', and R', the heating wires 65, 66 and the materials of the heating wires 65 and 66 are chosen such that when the aircraft 3 is on the ground, the heating wire 65 is adapted to heat the conduit 23 to a temperature such that all icing is avoided, but without the risk of damaging the mast 13. The voltage V generated by the voltage generator, the resistors R801 and R ', heating wires 65, 66 and the heating wire materials 65 and 66 are further selected such that when the aircraft 3 is in flight, the heating wires 65 and 66 are adapted to heat the end of the conduit 23 to a temperature such that ice accretion is avoided even under severe flight conditions.
    [0021] On the ground, a temperature at the discharge end 39 of about 220 ° C is sufficient to prevent icing. It has also been estimated, by means of tests, that a temperature at the end 39 of the exhaust duct 23 of at least 210 ° C., seen under laboratory conditions, allows, when the aircraft is in operation, flight in ISA conditions, to avoid any accretion of ice. Nevertheless, in order to avoid any accretion of ice under extreme conditions, it is desirable to provide a heating power such that the temperature of the discharge end 39 has a margin of 50% relative to the temperature sufficient to ensure good operation under ISA conditions, ie 315 ° C or 80%, ie 380 ° C.
    [0022] Thus, preferably, the voltage V generated by the voltage generator, the resistors R801 and R, o, heating wires 65, 66 and the materials of the heating wires 65 and 66 are chosen such that: - when the aircraft is on the ground, with an ambient temperature between + 10 ° C and -55 ° C, the heating wire 65 heats the conduit 23 with a power of between 20 and 30W, and the temperature of the discharge end 39 reaches a Tsol temperature between 200 and 250 ° C, in particular substantially equal to 220 ° C, and - under laboratory conditions simulating a flight of the aircraft, with an ambient temperature of -55 ° C, the heating son 65 and 66 heat the conduit 23 with a power between 110 and 120W, for example equal to 112W, and the temperature of the exhaust end 39 reaches a temperature between 315 and 390 ° C, in particular substantially equal to 380 ° C. For example, the voltage V is chosen equal to 27V, the first heating wire 65 is made of Balco and has a resistance Rsol = 14.58 S2 +/- 5% at an ambient temperature of 0 ° C., and the second heating wire 66 is made of nickel and has a resistance Rvol = 3.35 +/- 5% at an ambient temperature of 0 ° C.
    [0023] These values make it possible to obtain, on the ground, a power of between 26W and 29W, depending on the ambient temperature between + 10 ° C and -55 ° C, and a temperature Tsol at the discharge end 23 about 220 ° C, and in flight, a power of about 112W (under laboratory conditions) at a temperature of -55 ° C, and a temperature Tvol at the discharge end 39 of about 380 ° C. The drainage mast 13 according to the invention thus makes it possible, when it is fastened to the fuselage 17 of the aircraft, to evacuate the wastewater flowing in the circuit 11 from the sink 5 and the ice drawers 7. without ice accretion occurring in the conduit 13 or at the exit of the conduit 23 when the aircraft 3 is on the ground or in flight, even in extreme flight conditions. In particular, no accretion of ice occurs during a sudden drainage of 5L of water, a permanent trickle of water at a rate of 3L / min, or a drop of 100 drops / min. In particular, the profiled section 37 makes it possible to stabilize the flow of the incident air on the drainage mast 13 and to make this flow as turbulent as possible to the right of the discharge end 39. Thus, the water droplets from the drainage mast 13 via the end of the drainage duct 23 at the outlet 39 are discharged by this flow and do not come to rest on the mast 13 drainage or on the fuselage 17.
    [0024] Furthermore, the heating means 27 allow, by heating the conduit 23, and more specifically the discharge end 39, to avoid a gel of the water discharged into the conduit 23 or the outlet of the conduit 23. In in addition, the air channel 25 makes it possible to isolate the water droplets at the outlet of the drainage mast 13 and thus facilitates their evacuation into the air flow at the outlet of the drainage mast 13. Other embodiments may be envisaged. In particular, according to one variant, the power supply means 29 do not include a thermostat.
    权利要求:
    Claims (15)
    [0001]
    CLAIMS1.- A drainage mast (13) for evacuating fluids from an aircraft (3), said drainage mast (13) comprising a fairing (21) intended to be fixed on an outer surface (17) of the aircraft (3), said fairing (21) comprising: - a base (33) comprising an upstream section (33a) intended to be fixed on said outer surface (17) of the aircraft (3) and a downstream section (33b) and an exhaust nozzle (35) having a discharge end (39) opening out of said shroud (21), said exhaust nozzle (35) projecting from said downstream section (33b) in a first direction relative to said base (33), said base (33) and said discharge nozzle (35) defining a tubular cavity (43) therethrough, said tubular cavity (43) extending from said upstream section (33a) up to said discharge end (39), said drainage mast (13) being characterized in that said fairing (21) comprises d further an air guiding profiled section (37) projecting from said downstream section (33b), in a direction opposite to said first direction, said profiled section (37) being configured to orient an air mass incident on said shaped section (37) towards said discharge end (39).
    [0002]
    2.- drainage mast (13) according to claim 1, characterized in that said profiled section (37) and said discharge nozzle (35) form a shell (44) projecting from said downstream section (33b) from and other of said upstream section (33a).
    [0003]
    3.- Mast (13) drainage according to any one of claims 1 or 2, characterized in that it further comprises at least one conduit (23) for drainage of a fluid, said conduit (23) drainage extending into said tubular cavity (43).
    [0004]
    4.- drainage mast (13) according to claim 3, characterized in that said duct (23) comprises an upstream end end (23a) intended to be connected to a fluid circuit (11) of the aircraft (3) when said drainage mast (13) is fixed on said outer surface (17) of the aircraft (3) and a downstream end (23b) for discharging a fluid from said fluidic circuit (11) outside said fairing ( 21) through said discharge end (39).
    [0005]
    5.- Mast (13) drainage according to claim 4, characterized in that said downstream end (23b) and said end (39) discharge are flush.
    [0006]
    6.- Mast (13) drainage according to any one of claims 4 or 5, characterized in that said downstream end (23b) is configured to discharge said fluid to the outside of said fairing (21) in a second direction, said first direction and said second direction forming between them an angle greater than 00.
    [0007]
    7.- Mast (13) drainage according to any one of claims 3 to 6, characterized in that it comprises means (27) for heating said duct (23) drainage.
    [0008]
    8.- Mast (13) drainage according to claim 7 taken in combination with any one of claims 4 to 6, characterized in that said means (27) for heating cover said downstream end (23b).
    [0009]
    9.- drainage mast (13) according to any one of claims 7 or 8, characterized in that said means (27) for heating comprise at least one heating wire (65, 66) wound around said conduit (23) of drainage.
    [0010]
    10.- drainage mast (13) according to claim 9, characterized in that said at least one heating wire (65, 66) is brazed on said duct (23) drainage.
    [0011]
    11.- Mast (13) drainage according to any one of claims 7 to 10, characterized in that it comprises means (29) for supplying electrical power to electrically supply said means (27) for heating with a first power when the aircraft (3) is on the ground and with a second power, strictly greater than said first power, when the aircraft (3) is in flight.
    [0012]
    12.- drainage mast (13) according to claim 11 taken in combination with any one of claims 9 or 10, characterized in that said means (27) for heating comprise a first (65) and a second (66) heating wires wound around said drain duct (23), and in that said supply means (29) are adapted to electrically supply the first heating wire (65) to the exclusion of the second heating wire (66) when the aircraft (3) is on the ground and to feed the first (65) and second (66) heating son when the aircraft (3) is in flight.
    [0013]
    13.- drainage mast (13) according to claim 12, characterized in that each of said first (65) and second (66) heating son is wound around said duct (23) of drainage in turns, and in that the turns of said first wire (65) and turns of said second wire (66) are alternated around said drainage conduit (23).
    [0014]
    14.- drainage mast (13) according to any one of claims 3 to 13, characterized in that it comprises a peripheral air channel (25) extending inside said tubular cavity (43) around said drainage duct (23).
    [0015]
    15.- Method for draining a fluid flowing in a circuit (11) for emptying an aircraft (3) to an opening (15) formed in a fuselage (17) of the aircraft (3) said method being characterized by comprising: providing a drainage mast (13) according to any one of claims 1 to 14, said drainage mast (13) being attached to said fuselage (17); ) in the extension of said drain circuit (11), - evacuation of said fluid to the outside of the aircraft (3) through said tubular cavity (43) by said discharge end (39).
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    同族专利:
    公开号 | 公开日
    CA2888851A1|2015-11-15|
    US9688378B2|2017-06-27|
    BR102015011054A2|2018-03-13|
    US20150329195A1|2015-11-19|
    FR3021028B1|2016-06-24|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE4408493C1|1994-03-14|1995-02-09|Deutsche Aerospace Airbus|Device for waste-water drainage from aircraft|
    WO2002036426A2|2000-08-18|2002-05-10|Goodrich Corporation|Aircraft drainmast assembly with lightning protection|
    WO2002030745A1|2000-10-12|2002-04-18|Goodrich Corporation|Bottom discharge drainmast for an aircraft|
    US2248308A|1938-03-07|1941-07-08|Beatrice W Rice|Method and apparatus for valving inflammable fluids|
    US2573207A|1946-06-06|1951-10-30|Republic Aviat Corp|Liquid discharge mechanism|
    US2827911A|1954-05-25|1958-03-25|Kenyon Instr Company Inc|Fluid pressure regulating valve|
    US2966160A|1957-08-28|1960-12-27|Aero Supply Mfg Co Inc|Fluid sensing device|
    US3409253A|1966-12-02|1968-11-05|Whittaker Corp|Retractable fuel tank for aircraft|
    US3691730A|1971-05-18|1972-09-19|Parker Hannifin Corp|Fuel tank inerting system|
    US3748111A|1971-06-11|1973-07-24|W Klose|Flame arrestor|
    US3788040A|1972-06-09|1974-01-29|Parker Hannifin Corp|Fuel tank inerting system|
    US5794707A|1988-12-06|1998-08-18|Alhamad; Shaikh Ghaleb Mohammad Yassin|Flame arrestor|
    US6105676A|1991-03-19|2000-08-22|Alhamad; Shaikh Ghaleb Mohammad Yassin|Flame arrester|
    US5588617A|1993-04-14|1996-12-31|The Boeing Company|Motor operated restrictor valve|
    US5381742A|1993-09-17|1995-01-17|Landa, Inc.|Waste liquid evaporator|
    US6823831B2|1998-09-28|2004-11-30|Parker-Hannifin Corporation|Flame arrestor system for fuel pump discharge|
    US6211494B1|1999-08-25|2001-04-03|The B. F. Goodrich Company|Drainmast with integral electronic temperature control|
    US8011033B2|2005-04-08|2011-09-06|The Boeing Company|Aircraft sink with integrated waste disposal function|
    US7651055B2|2005-05-05|2010-01-26|Honeywell International Inc.|Non-streaking drainmast|
    US7731127B2|2005-05-18|2010-06-08|Airbus Deutschland Gmbh|Drain mast connector|
    DE102008037142B4|2008-08-08|2011-12-22|Airbus Operations Gmbh|Extendable deflector for releasing structure-damaging fluids|
    US9315253B2|2013-09-18|2016-04-19|Goodrich Corporation|Drain masts|US10808577B2|2017-03-28|2020-10-20|The Boeing Company|Aerodynamic drainage device|
    US10717514B2|2018-03-09|2020-07-21|Senior Ip Gmbh|Integrated drain mast structure|
    FR3090582B1|2018-12-20|2020-11-27|Airbus Operations Sas|Drain configured to drain leaking fluid, such as fuel, from an aircraft leak collection system, and associated aircraft.|
    US11186354B2|2019-05-06|2021-11-30|Rohr, Inc.|Unitary drain mast|
    法律状态:
    2015-05-20| PLFP| Fee payment|Year of fee payment: 2 |
    2015-11-20| PLSC| Search report ready|Effective date: 20151120 |
    2016-04-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 4 |
    2018-04-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-30| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-14| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1401095A|FR3021028B1|2014-05-15|2014-05-15|DRAINAGE MAT AND METHOD THEREOF|FR1401095A| FR3021028B1|2014-05-15|2014-05-15|DRAINAGE MAT AND METHOD THEREOF|
    CA2888851A| CA2888851A1|2014-05-15|2015-04-22|Drainmast and associated process|
    US14/711,699| US9688378B2|2014-05-15|2015-05-13|Drain mast and associated method|
    BR102015011054-5A| BR102015011054A2|2014-05-15|2015-05-14|DRAIN MAST AND METHOD TO DRAIN A FLUID|
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