• 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 invention relates to a propulsion system comprising: a nacelle of substantially tubular shape around a longitudinal axis, delimited by an inner wall extending from the front of the nacelle to the rear of the nacelle and by a outer wall, outside the inner wall, extending from the front of the nacelle to the rear of the nacelle, - a turbojet engine comprising a fan and located inside the inner wall of said nacelle, - at least one tank (410a-b) containing an extinguishing fluid, and - a network of pipes hydraulically connected to said or each tank (410a-b), the propulsion system being characterized in that the or each tank (410a -b) is placed in said nacelle, around the inner wall and inside the outer wall. Such a propulsion system makes it possible to move the tank or tanks that no longer encumber the space at the mast and allows to board a large volume of extinguishing fluid that can accommodate future regulation.
    公开号:FR3041936A1
    申请号:FR1559380
    申请日:2015-10-02
    公开日:2017-04-07
    发明作者:Alain Porte；Jean Michel Rogero
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    Aircraft propulsion system comprising at least one fire-fighting tank
    TECHNICAL AREA
    The present invention relates to an aircraft propulsion system comprising at least one fire reservoir and an aircraft comprising at least one such propulsion system.
    STATE OF THE PRIOR ART
    An aircraft conventionally comprises at least one propulsion system, comprising a nacelle inside which is disposed an engine, for example of the turbojet type, and which is fixed to the aircraft structure via a fixed mast. under the wing of the aircraft.
    In order to avoid damage to the structure of the aircraft when a motor catches fire, the aircraft conventionally comprises for each nacelle two tanks containing an extinguishing fluid, which may be a liquid or gaseous agent
    Fig. 1 is a schematic representation of a propulsion system of the state of the art including a nacelle 16 and a motor 17 which is disposed inside the nacelle 16. This nacelle 16 is fixed under the mast 12 which extends under wing 14 of the aircraft.
    To detect the beginning of a fire in the propulsion system, it is equipped with a plurality of fire sensors 18 which are distributed in the propulsion system and which are connected to a detection unit 20.
    For each propulsion system, the aircraft embeds two tanks 22a and 22b, generally of spherical shape, which are fixed at the mast 12, equipped with explosive cartridges 23a-b and filled with a fire extinguishant fluid.
    A pipe network 24 extends between each tank 22a-b and different zones of the propulsion system.
    When a fire sensor 18 detects a fire in the propulsion system, it informs the fire detection unit 20 which triggers a warning means present in the cockpit. The pilot then actuates an activation button which controls the explosion of one of the explosive cartridges 23a-b in order to release the extinguishing fluid from the associated reservoir 22a-b which then spreads in the propulsion system through the network of pipes 24.
    Such an anti-fire system is entirely satisfactory, but the extinguishing fluid used is generally based on bromotrifluoromethane, also called "halon". As this product is a relatively polluting product, it tends to disappear and to be replaced by other products. These new products require tanks with larger capacities, and these increases are not always compatible with the space available at the mast which is an area already relatively congested.
    SUMMARY OF THE INVENTION
    An object of the present invention is to provide an aircraft propulsion system comprising at least one fire reservoir which does not have the drawbacks of the prior art and in particular the tanks have a larger capacity without further encumbering the place available at the mast. For this purpose, there is provided a propulsion system comprising: a nacelle of substantially tubular shape around a longitudinal axis, delimited by an inner wall extending from the front of the nacelle to the rear of the nacelle and by an outer wall, outside the inner wall, extending from the front of the nacelle to the rear of the nacelle, - a turbojet comprising a blower and located inside the inner wall of said nacelle, - at least one reservoir containing an extinguishing fluid, and - a network of pipes hydraulically connected to said or each reservoir, the propulsion system being characterized in that the or each reservoir is placed in said nacelle, around the wall inside and inside the outer wall.
    Thus, with such a propulsion system, the extinguisher fluid reservoir (s) are housed in the nacelle and do not encumber the space at the mast and allow to board a large volume of extinguishing fluid. In addition, it advantageously allows the tank or reservoirs are close to the areas to be protected in order to limit the length of the pipes, and therefore the volume of the pipes and tanks.
    According to a particular embodiment, the or each tank has a shape comprising at least one circular section in a plane perpendicular to the longitudinal axis.
    Advantageously, the or each reservoir has a shape comprising at least one portion of open core in a plane perpendicular to the longitudinal axis.
    According to another particular embodiment, the or each reservoir has a shape comprising at least two portions of non-aligned cylinders.
    Advantageously, the or each reservoir extends angularly around the periphery of said nacelle so that the lowest part of said or each reservoir is located above a horizontal plane tangential to the lower edge of said inner wall. of said nacelle.
    Advantageously, the reservoir or at least one of the reservoirs is located in the portion of the nacelle which extends to the front of the turbojet fan.
    Advantageously, the reservoir or at least one of the reservoirs is located in the portion of the nacelle which surrounds the fan of the turbojet engine.
    According to a particular embodiment, the connection between the or each tank and the pipe network is located in the lowest part of said tank.
    According to another particular embodiment, the or each tank has a membrane separating the internal volume of the tank in an upper part and a lower part, the lower part contains a gas under pressure, the upper part contains the extinguishing fluid, and the connection between said tank and the pipe network is in the upper part of said tank.
    According to a particular embodiment, the propulsion system comprises a plurality of fasteners distributed along the or each tank and ensuring the fixing of said tank on the inner wall of the nacelle.
    According to another particular embodiment, the propulsion system comprises a plurality of fasteners distributed along the or each tank and fixing said tank to an intermediate wall which extends around the engine between the inner wall and the outer wall of the tank. Platform.
    Advantageously, the fasteners have a flexible or deformable element. The invention also proposes an aircraft comprising at least one propulsion system according to one of the preceding variants.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in connection with the attached drawings, among which: FIG. . 1 is a schematic representation of a propulsion system of the state of the art seen from the side, FIG. 2 is a schematic representation of an aircraft according to the invention in a view from above, FIG. 3 is a schematic representation of a propulsion system according to the invention viewed from the side, FIG. 4 is a perspective view of a pair of tanks according to a first embodiment of the invention, FIG. 5 is a front view of a pair of tanks installed in a nacelle, according to a second embodiment of the invention, FIG. 6 is a front view of a reservoir according to a third embodiment of the invention, FIG. 7 is a front view of a tank according to a fourth embodiment of the invention. FIG. 8 is a perspective view of a first method of attaching a tank to the nacelle, FIG. 9 is a perspective view of a second method of attaching a tank to the nacelle, FIG. 10 is a perspective view of a variant of the first method of attaching a tank to the nacelle, FIG. 11 is a perspective view of a variant of the second method of fixing a tank to the nacelle, FIG. 12 is a perspective view of another variant of the first method of attaching a reservoir to the nacelle, FIG. 13 is a perspective view of a third method of attaching a tank to the nacelle, FIG. 14 is a diagrammatic representation, in longitudinal section, of a propulsion system in which reservoirs are attached to the nacelle according to a fourth mode of attachment, and FIG. 15 is a diagrammatic representation, in longitudinal section, of a propulsion system in which reservoirs are fixed to the nacelle according to a fifth mode of attachment,
    In the following description, the terms relating to a position are taken with reference to an aircraft in normal flight position.
    DETAILED DESCRIPTION OF EMBODIMENTS
    Fig. 2 shows an aircraft 200 which comprises at least one propulsion system 202. Each propulsion system 202 comprises at least one nacelle surrounding a motor and at least one tank 210 filled with a fire extinguishing fluid. The following description is made for a propulsion system but it applies to all the propulsion systems of the aircraft 200 regardless of the number of propulsion systems that the aircraft 200 has.
    Fig. 3 shows the propulsion system 202 seen from the side which contains a motor 17 surrounded by a nacelle 16. The engine 17 is a turbojet comprising a fan 19 placed in front of the body 15 of the engine, this body 15 comprising the compressor, the chamber of combustion and the turbine. The nacelle 16 which surrounds and carries the engine 17 comprises in particular an air inlet 204, formed by the portion of the nacelle 16 which is at the front of the fan 19, a fan surround 205 surrounding the fan 19 of the engine and a thrust reverser 207 formed by the portion of the nacelle which is at the rear of the fan 19.
    The nacelle 16 has a generally cylindrical shape around its longitudinal axis. The generally cylindrical shape fits between an inner wall 206, taking the approximate shape of a cylinder, and an outer wall 208, taking the approximate shape of a cylinder disposed outside the inner wall 206. The inner wall 206 and the outer wall 208 extend from the front to the rear of the nacelle 16 and meet at the front of the nacelle 16 to form the leading edge of the nacelle and the rear of the nacelle 16 and the nacelle 16 to form the trailing edge of the nacelle 16. The nacelle 16 thus has a generally tubular general shape about its longitudinal axis. In the present description, it is considered that the fan casing, which is a component of the motor, forms a portion of the inner wall 206 defining the nacelle 16, at the level of the fan surround 205.
    The propulsion system 202 also comprises a plurality of fire sensors 18 distributed in the propulsion system 202 and connected to a detection unit 20. As for the state of the art, the propulsion system 202 is attached to the structure of the aircraft 200 via a mast 12 fixed under the wing 14 of the aircraft 200. The triggering of the fire alarm is identical to that of the state of the art. In the same way, the triggering by a pilot of the response to this fire alarm is identical to that of the state of the art, that is to say that the actuation of an activation button controls the explosion of an explosive cartridge to allow the extinguishing fluid contained in the tank 210 to circulate in a pipe network 212 to spread at different points of the propulsion system 202.
    Each tank 210 is fixed in the nacelle 16 of the propulsion system 202, between the inner wall 206 and the outer wall 208 of this nacelle 16. This positioning of the tanks 210 makes it possible to free up space in the mast 12. It also allows a significant reduction in the length of the pipe network 212, which reduces the mass of these pipes, and reduce the volume of extinguishing fluid that remains in these pipes and is not used to extinguish a fire, and therefore optimize the volume of tanks for the same efficiency.
    In a first embodiment shown in FIG. 4, there are two tanks 410a-b which are intended to be placed in the nacelle 16. Each tank 410a-b takes the form of a portion of torus open in a plane substantially perpendicular to the longitudinal axis of the nacelle 16 to fit the shape of the nacelle 16, and is filled with a fire extinguishant fluid.
    Each tank 410a-b is hydraulically connected to a drain pipe 412 which is part of the pipe network 212 and thus allows the supply of the latter extinguishing fluid. In the embodiment of the invention presented here, most of the exhaust line 412 is common to both tanks 410a-b.
    Between each tank 410a-b and the evacuation pipe 412 is arranged a valve 414a-b, for example of the explosive cartridge type, which when activated by a pilot allows the release of the extinguishing fluid of the tank 410a-b associated with the network of pipes 212.
    In the embodiment of the invention of FIG. 4, each tank 410a-b extends over a portion of the periphery of the inner wall 206 representing an angular zone of about 180 °.
    In a second embodiment of the invention presented in FIG. 5, there are also two tanks 510a-b placed in the nacelle 16. Each tank 510a-b takes the form of a portion of torus open to fit the shape of the nacelle 16, and is filled with a extinguishing fluid. Each tank 510a-b is hydraulically connected to a drain pipe 512a-b which is part of the pipe network 212 and thus allows the supply of the latter extinguishing fluid.
    In the embodiment of the invention presented here, there is a drain line 512a-b per tank 510a-b.
    Between each tank 510a-b and the associated evacuation line 512a-b is arranged a valve 514a-b, for example of the explosive cartridge type, which when activated by a pilot allows the release of the extinguishing fluid from the tank 510a. associated with the mains network 212.
    In the embodiment of the invention of FIG. 5, each tank 510a-b extends angularly so that the lowest part of each tank 510a-b is located above a safety plane 550 which is a horizontal plane tangential to the lower edge of the inner wall 206 of the nacelle surrounding the fan blades 19, forming the fan casing. Indeed, the nacelle 16 is normally dimensioned so that the portion of the nacelle 16 above this plane undergoes no major damage in case of landing of the aircraft 200 with the landing gear raised. Thus, even in the event of landing with the landing gear raised, the tanks 510a-b remain intact and can be used. Here each tank 510a-b extends over a portion of the perimeter of the nacelle representing an angular zone of about 120 °.
    In the embodiments presented here, there are in each case two reservoirs in the form of an open torus portion, but in general there may be at least one reservoir in the form of a portion of open toroid fixed in the nacelle 16, around the inner wall 206 and inside the outer wall 208.
    In the same way, in the embodiments presented here, the two tori are coplanar, but they could be more than two and be in different planes and thus be arranged one behind the other around the inner wall 206 with each , an angular amplitude greater than 180 °, increasing the volume of extinguishing fluid available. The angular amplitude of each tank 210, 410a-b, 510a-b varies as a function of the bulk around the tank 210, 410a-b, 510a-b and can be up to 360 °. A wide angular amplitude allows a distribution of weight and relatively uniform stiffness around the engine 17.
    Each reservoir 210, 410a-b, 510a-b preferably extends over an angular zone of at least 90 ° so that it contains a minimum quantity of extinguishing fluid while adapting to the space available in the nacelle 16.
    In the preferred embodiments shown in Figs. 4 and 5, the tanks 410a-b and 510a-b are in the form of portions of open torus. Such a shape allows the tanks to adapt well to the shape of the nacelle 16. It is also possible, however, that the tanks have other shapes adapted to be contained in the nacelle 16. Thus, FIG. 6 shows a part of a nacelle 16 in which a reservoir 910 is placed around the inner wall 206 and inside the outer wall 208. This reservoir 910 has a shape consisting of assembled cylinder portions, forming between them angles allowing the reservoir 910 to adapt to the shape of the nacelle 16. The reservoir 910 shown in FIG. 6 has two portions of rolls assembled, but it is also possible to assemble a larger number.
    Likewise, FIG. 7 shows a part of a nacelle 16 in which a reservoir 911 is placed around the inner wall 206 and inside the outer wall 208. This reservoir 911 has a cylindrical shape. In this embodiment, the length of the tank 911 is limited, to allow it to be housed in the nacelle 16. In the embodiments shown in Figs. 6 and 7, the tanks 910 and 911 are connected to the pipe network 212 in a manner similar to the embodiments of FIGS. 4 and 5 and which is not further described herein. Other forms of tank adapted to a nacelle can also be imagined by those skilled in the art. However, the tank shapes having a circular section in a plane substantially perpendicular to the longitudinal axis of the nacelle 16 are preferred, because they allow a better resistance to pressure. Among these shapes, the tank shapes having at least one portion of open torus in a plane substantially perpendicular to the longitudinal axis of the nacelle 16 are preferred because they allow a better adaptation of the reservoir to the shape of the inlet of air, and can thus allow a larger useful volume of the tank with limited space.
    The extinguishing fluid is generally associated with a pressurized gas also present in each tank 210, 410a-b, 510a-b, 910, 911. Insofar as the gas is lighter than the extinguishing fluid, it is placed in the upper part each tank 210, 410a-b, 510a-b, 910, 911. To allow the flow of extinguishing fluid, the connection between the tank 210, 410a-b, 510a-b, 910, 911 and the pipe network 212 through the evacuation line 412, 512a-b is located in the lowest part of the reservoir 210, 41a-b, 51a-b, 910, 911.
    In another embodiment of the invention, the reservoir 210, 410a-b, 510a-b, 910, 911 has a membrane separating the interior volume of the reservoir 210, 410a-b, 510a-b, 910, 911 into a upper part and a lower part. In this case, the pressurized gas can be maintained in the lower part of the tank 210, 410a-b, 510a-b, 910, 911 and the extinguishing fluid can be maintained in the upper part. The connection between the tank 210, 410a-b, 510a-b, 910, 911 and the pipe network 212 via the evacuation pipe 412, 512a-b is then located in the highest part of the tank. 210, 410a-b, 510a-b, 910, 911.
    In an advantageous embodiment, the reservoir or tanks are located in the portion of the nacelle 16 forming the air inlet 204, in front of the fan 19. The tanks are in this case in an area which, being in front of the engine, is well protected in case of fire of the engine, and which is unlikely to be damaged in the event of breakage of a blade of the fan 19. In other possible embodiments, the tank or tanks may be located in the portion of the nacelle 16 forming the fan casing 19.
    Fig. 8 shows a first method of fixing the tanks 410a-b in the air inlet 204 of a nacelle. Although FIG. 8 is applied to the tanks 410a-b according to the first embodiment, it can be applied to all types of tanks according to the invention.
    The fixing of each tank 41 Oa-b on the inner wall 206 is provided by a plurality of fasteners 602, only one of which is shown in FIG. 8, and which are distributed along the or each tank 41 Oa-b. Each attachment 602 takes the form of a flange 606 which encloses the reservoir 41 Oa-b and which has a foot 608 fixed on the inner wall 206, here by means of bridges 604.
    In the context of maintenance, access to the tanks 41 Oa-b can be done for example by local disassembly of the outer wall 208.
    Fig. 9 shows a second method of fixing the tanks 41 Oa-b in the air inlet 204 of a nacelle. Although FIG. 9 is applied to the tanks 410a-b according to the first embodiment, it can be applied to all types of tanks according to the invention.
    The fixing of each tank 41a-b is provided by a plurality of fasteners 702, only one of which is shown in FIG. 9, and which are distributed along the tank 410a-b. Each fastener 702 secures the reservoir 410a-b on an intermediate wall 710 which extends around the motor 17 between the inner wall 206 and the outer wall 208. Each fastener 702 takes the form of a flange 706 which encloses the reservoir 410a-b and which has a foot 708 fixed on the intermediate wall 710.
    It should be noted that the intermediate wall 710 can extend in a plane perpendicular to the axis of the motor, or be inclined relative to this plane. This intermediate wall 710 may also have various shapes, for example truncated cone.
    In the context of maintenance, access to the tanks 410a-b can be done for example by dismounting a portion of the outer wall 208.
    Such an implantation tanks 410a-b also allows these tanks 410a-b form a reinforcement of the structure surrounding the engine 17 and participate in the rigidity of the nacelle 16, for example in case of rupture of a blade of the fan.
    To enable the tanks 410a-b to withstand the deformations of the nacelle 16, the fasteners 602, 702 may advantageously incorporate a flexible element, such as a rubber block or deformable, able to absorb a portion of the energy of a deformation of the nacelle 16.
    Figs. 10, 11, 12 and 13 show variants of the attachment modes shown in FIGS. 6 and 7, which allow different distributions of the mechanical forces experienced by the nacelle 16. These variants can be applied to all types of tanks according to the invention.
    Thus, FIG. 10 shows a variant of the attachment mode shown in FIG. 8, in which the bridges 604 which carry the feet 608 of the fasteners 602 are fixed on a support 801 extending along the inner wall 206. This support 801 comprises a cylindrical portion which carries bridges 604 and a portion forming a profile annular U-shaped which can be secured directly to the fan casing (not shown in Fig. 10) through a detachable connection.
    Fig. 11 shows a variant of the attachment mode shown in FIG. 9, in which the intermediate partition 710 which carries the feet 708 of the fasteners 702 is assembled to the inner wall 206 by means of a U-shaped annular profile 802, which can be secured directly to the fan casing (not shown in FIG. Fig. 11) and / or the motor via a removable link.
    Fig. 12 shows another variant of the attachment mode shown in FIG. 8, in which the feet 608 of each fastener 602 are fixed on short bridges 604, themselves fixed to a support 804. Each support 804 extends substantially parallel to the axis of the motor, and parallel to the inner wall 206, and is fixed, at its front end, to a portion of the inner wall 206 near the leading edge of the nacelle 16, and at its rear end to the intermediate partition 710 and, through the partition 710 to an annular profile in U 803 which can be directly attached to the fan casing (not shown in Fig. 12) by means of a detachable connection.
    Fig. 13 shows another variant of the attachment mode shown in FIG. 9, in which the feet 708 of the fasteners 702 are assembled on the rear face of the intermediate partition 710, which is inclined and has the shape of a truncated cone. This intermediate partition 710 is assembled to the inner wall 206 by means of a support 805, which can be secured directly to the fan casing (not shown in Fig. 13) and / or to the motor by means of a removable connection. In the case where the tanks are installed in an area likely to be exposed to fire, they can be covered by a complementary wall forming screen, to avoid subjecting the tanks to high temperatures.
    Fig. 14 shows another embodiment of a nacelle 16 engine 17, adapted to a very high engine dilution rate. In this embodiment, the tanks 510 are located in the portion of the nacelle 16 surrounding the fan 19, between the outer wall 208 and the inner wall 206 of the nacelle 16, and are carried by an intermediate wall 710 connecting these inner walls. 206 and external 208.
    Fig. 15 shows yet another embodiment of a nacelle 16 engine 17, adapted to a very high engine dilution ratio. In this embodiment, the tanks 510 are located in the portion of the nacelle 16 surrounding the fan 19, between the outer wall 208 and the inner wall 206 of the nacelle 16, and are carried by a support 806 fixed to the fan casing 30, which forms the inner wall 206 of the nacelle at the level of the fan 19.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1) propellant system comprising (202): - a nacelle (16) of substantially tubular shape about a longitudinal axis, defined by an inner wall (206) extending from the front of the nacelle (16) to at the rear of the nacelle and by an outer wall (208), outside the inner wall (206), extending from the front of the nacelle (16) to the rear of the nacelle (16), - a turbojet engine (17) comprising a fan (19) and located inside the inner wall (206) of said nacelle (16), - at least one reservoir (210, 410a-b, 510a b, 910, 911) containing an extinguishing fluid, and - a pipe network (212) hydraulically connected to said or each tank (210, 410a-b, 510a-b, 910, 911), the propulsion system (202) being characterized in that the or each reservoir (210, 410a-b, 510a-b, 910, 911) is placed in said nacelle (16), around the inner wall (206) and at the within the outer wall (208).
    [0002]
    2) propulsion system (202) according to claim 1, characterized in that the or each tank (210, 410a-b, 510a-b) has a shape having at least one circular section in a plane perpendicular to the longitudinal axis.
    [0003]
    3) Propulsive system (202) according to claim 2, characterized in that the or each tank (210, 410a-b, 510a-b) has a shape comprising at least a portion of open torus in a plane perpendicular to the axis longitudinal.
    [0004]
    4) Propulsive system (202) according to claim 1, characterized in that the or each tank (910) has a shape comprising at least two portions of non-aligned cylinders.
    [0005]
    5) propulsion system (202) according to any one of the preceding claims, characterized in that the or each tank (210, 410a-b, 510a-b, 910, 911) extends angularly around the periphery of said nacelle (16) so that the lowest part of said or each tank (210, 410a-b, 510a-b, 910, 911) is above a horizontal plane (550) tangential to the lower edge said inner wall (206) of said nacelle (16).
    [0006]
    6) propulsion system (202) according to one of the preceding claims, characterized in that the reservoir or at least one of the tanks (210, 410a-b, 510a-b, 910, 911) is located in the portion of the nacelle (16) which extends to the front of the fan (19) of the turbojet engine (17).
    [0007]
    7) propulsion system (202) according to one of the preceding claims, characterized in that the reservoir or at least one of the tanks (210, 410a-b, 510a-b, 910, 911) is located in the portion of the nacelle surrounding the blower (19) of the turbojet engine (17).
    [0008]
    8) propulsion system (202) according to one of the preceding claims, characterized in that the connection between the or each tank (210, 410a-b, 510a-b, 910, 911) and the pipe network (212) is located in the lowest part of said tank (210, 410a-b, 510a-b).
    [0009]
    9) propulsion system (202) according to one of claims 1 to 7, characterized in that the or each tank (210, 410a-b, 510a-b, 910, 911) has a membrane separating the interior volume of the reservoir ( 210, 410a-b, 510a-b, 910, 911) in an upper part and a lower part, in that the lower part contains a gas under pressure, in that the upper part contains the extinguishing fluid, and in that the connection between said tank (210, 410a-b, 510a-b, 910, 911) and the pipe network (212) is in the upper part of said tank (210, 410a-b, 510a-b, 910, 911 ).
    [0010]
    10) propulsion system (202) according to one of the preceding claims, characterized in that it comprises a plurality of fasteners (602) distributed along the or each tank (210, 410a-b, 510a-b, 910, 911) and fixing said tank (210, 410a-b, 510a-b, 910, 911) on the inner wall (206) of the nacelle (16).
    [0011]
    11) propulsion system (202) according to one of claims 1 to 9, characterized in that it comprises a plurality of fasteners (702) distributed along the or each tank (210, 410a-b, 510a-b, 910, 911) and securing said tank (210, 410a-b, 510a-b, 910, 911) to an intermediate wall (710) which extends around the motor (17) between the inner wall (206) and the outer wall (208) of the nacelle (16).
    [0012]
    12) Propulsive system (202) according to one of claims 10 or 11, characterized in that the fasteners (602, 702) have a flexible or deformable element.
    [0013]
    13) Aircraft (200) comprising at least one propulsion system (202) according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3041936A1|2017-04-07|PROPULSIVE AIRCRAFT SYSTEM COMPRISING AT LEAST ONE FIRE RESISTANT
    EP1571080A1|2005-09-07|Aircraft engine attachment onto a wing pylon
    CA2589873C|2013-02-12|Device for increasing the effectiveness of the pressurizing gas in an extinguisher bottle
    EP2205325B1|2012-02-22|Fluid ejection device with enhanced leaktightness
    CA2520464C|2012-04-03|Turbojet with a one-piece servicing connector arm and one-piece servicing connector arm
    EP3087265B1|2018-02-07|Aircraft propulsion assembly with fire extinguishing system and ventilation method
    EP2234886B1|2013-10-09|Nacelle for turbojet engine
    EP1902757B1|2010-04-21|Propulsion device for an agent contained in a cavity
    EP0893344B1|2002-12-11|Compact monolithic propulsion system using monergol for small satellite
    EP1899021A1|2008-03-19|Liquid mist fire extinguisher and use thereof
    EP2572919A1|2013-03-27|Fuel storage system and vehicle
    EP2161198A1|2010-03-10|Fagot comprising two pairs of tanks and airborne launcher comprising such a fagot
    EP3701171B1|2021-12-01|Propulsion unit for aircraft
    FR3060652B1|2019-08-23|NACELLE FOR AIRCRAFT TURBOJET ENGINE EQUIPPED WITH A FIRE EXTINGUISHING DEVICE
    FR3094892A1|2020-10-16|FIRE FIGHTING SYSTEM FOR AN AIRCRAFT CONTAINING A DOUBLE CHAMBER TANK
    WO2019193274A1|2019-10-10|Aircraft engine assembly with a supply path to an inter-flow compartment tank of a turbine engine
    WO2005098346A1|2005-10-20|Radiation-emitting device, which is intended in particular for infrared radiation
    EP1961459A1|2008-08-27|Fire extinguishing device
    CA2929951C|2022-03-08|Aircraft propulsion assembly with fire extinguishing system
    CA2879133C|2019-12-31|Device for protecting the front spar structure of a central casing of an aircraft wing and at least one piece of equipment located in said wing
    EP3945033A1|2022-02-02|Aircraft propulsion unit
    FR3099465A1|2021-02-05|SET FOR AN AIRCRAFT, LEDIT SET CONTAINING A MAST AND A TANK CONTAINING AN EXTINGUISHING FLUID
    FR2922972A1|2009-05-01|Fluid e.g. hydraulic oil, ejection device for use as e.g. emergency hydraulic generator, in aircraft, has valve in end part adopting closed configuration in presence of gas in reservoir to ensure sealing of enclosure
    FR3105177A1|2021-06-25|SET FOR AN AIRCRAFT, LEDIT SET CONTAINING A MAST AND A TANK CONTAINING AN EXTINGUISHING FLUID
    FR3078952A1|2019-09-20|WORKING ORBIT SYSTEM FOR A SATELLITE
    同族专利:
    公开号 | 公开日
    US10618670B2|2020-04-14|
    FR3041936B1|2018-08-17|
    US20170096238A1|2017-04-06|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2952125A|1959-02-17|1960-09-13|Boeing Co|Fire protective system for jet engines|
    FR3015568A1|2013-12-24|2015-06-26|Snecma|VENTILATION OF A PROPELLANT AIRCRAFT ASSEMBLY|
    EP3464864A1|2016-05-30|2019-04-10|C Series Aircraft Limited Partnership|Aircraft engine assembly|
    FR3068392A1|2017-06-29|2019-01-04|Airbus Operations |DEVICE FOR MONITORING A TURBOMACHINE OF AN AIRCRAFT|
    FR3075761A1|2017-12-21|2019-06-28|Airbus Operations|ANTERIOR PLATFORM PART OF A NACELLE COMPRISING AN INCLINE RIGIDIFICATION FRAME|
    CN111997760B|2019-05-27|2022-01-21|中国航发商用航空发动机有限责任公司|Aircraft engine|
    FR3099465A1|2019-07-30|2021-02-05|Airbus Operations|SET FOR AN AIRCRAFT, LEDIT SET CONTAINING A MAST AND A TANK CONTAINING AN EXTINGUISHING FLUID|
    FR3099914A1|2019-08-13|2021-02-19|Airbus Operations|Front part of the nacelle of an aircraft propulsion unit comprising a thermal transition zone|
    法律状态:
    2016-10-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Publication of the preliminary search report|Effective date: 20170407 |
    2017-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-28| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559380A|FR3041936B1|2015-10-02|2015-10-02|PROPULSIVE AIRCRAFT SYSTEM COMPRISING AT LEAST ONE FIRE RESISTANT|
    FR1559380|2015-10-02|FR1559380A| FR3041936B1|2015-10-02|2015-10-02|PROPULSIVE AIRCRAFT SYSTEM COMPRISING AT LEAST ONE FIRE RESISTANT|
    US15/280,130| US10618670B2|2015-10-02|2016-09-29|Aircraft propulsion system having at least one anti-fire tank|
    [返回顶部]