• 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:
    An air ejection device comprising an airfoil provided with a slot (36) and which includes an ejection nozzle (42). The device comprises a flexible tongue (48) fixed flush with the aerodynamic profile, so as to obstruct the slot (36), the tongue (48) being able to lift under the effect of a pressure differential between the air located in the ejection nozzle (42) and the outside air. The tongue (48) makes it possible to obstruct the slot (36) formed in the profile during the flight phases during which the ejection of the air is not necessary, and to prevent the outside air from coming off. to engulf. The flow of air on the aerodynamic profile is not impaired and there is no increase in drag. The tongue (48) lifting by pressure differential, it does not require a control mechanism provided for this purpose.
    公开号:FR3014413A1
    申请号:FR1362160
    申请日:2013-12-05
    公开日:2015-06-12
    发明作者:Julien Guillemaut；Arnaud Hormiere；Jerome Colmagro；Cesar Garnier
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to an aerodynamic profile provided with an air ejection device. According to a particular embodiment, the invention applies to a pylon supporting an aircraft propulsion assembly comprising such an aerodynamic profile and to an aircraft comprising such a pylon.
    [0002] During a trip, any aerodynamic vehicle profile is exposed to the wakes of other profiles of this vehicle, or disruptive phenomena of its boundary layer of air. Aircraft whose propulsion system is located on a pylon are particularly concerned because the pylon generates a wake, regardless of its design.
    [0003] This is particularly due to the fact that the height of the boundary layer of the pylon profile increases in the downstream direction of the profile. Thus, there occurs at the trailing edge of the pylon a "speed defect" (or "speed deficit") materialized by a difference between the speed of the free flow of air and the local speed of the air in the air. the downstream area of the profile.
    [0004] The zone presenting this speed defect is also the seat of a "mass flow rate defect" (or "mass flow deficit") of air. As a result, air tends to be dragged into the area due to lack of speed, causing turbulence. The discontinuity of the speeds and the turbulences of the wake cause, among others, an increase of the noise generated by the propellers of the turbine of the assembly of propulsion, being able to harm the comfort of the passengers and the environment, when said propellers pass in the wake of the pylon. This is called "masking" effect. There is therefore a need to limit this "masking" effect inducing a pressure variation in the wake of the pylon. In the specific case of pylons supporting propulsion units, there is a need to eliminate the deficit of air flow and thus reduce the speed deficit on their surface.
    [0005] One of the solutions to achieve this is to blow air from a high pressure source near the trailing edge of the profile to eliminate the deficit of air flow, and thus reduce the speed deficit. For this purpose, the document US 4917336 describes an air ejection device comprising an ejection nozzle sending air, into which the air escapes through slots made at the extrados and the intrados of a pylon supporting an aircraft propulsion unit. This solution has the disadvantage of not allowing the obstruction of the openings in the pylon. Indeed, a permanent opening located on the aerodynamic profile of the pylon at its trailing edge is a rupture of the aerodynamic profile. Such a rupture causes disturbances of the flow of air, and consequently an increase in the drag induced during the phases of the flight during which the ejection of air is not necessary. Moreover, without closing the aperture, the air tends to engulf it, which further disrupts the flow. To solve this problem, the document FR 2971765 proposes a similar ejection device, further comprising two grids comprising holes through which air is ejected. The grids are movable relative to each other, allowing partial or complete obstruction of the holes depending on the situations, for example when the incidence of the tower varies. Such a device is however complex to use because it effectively imposes a gate opening and closing control system. It is difficult to achieve with regard to manufacturing tolerances, and also not very resistant. The invention proposes to remedy at least one of the disadvantages of the prior art, by providing an air ejection device comprising a profile provided with an opening and an ejection nozzle opening into the opening. The invention is distinguished by the fact that the ejection device comprises a flexible tongue fixed in the continuity of the profile, so as to obstruct the opening, said flexible tongue being able to lift under the effect of a differential pressure between the air in the ejection nozzle and the outside air. The tongue makes it possible to obstruct the opening made in the profile during displacements (flight phases for an aircraft aerodynamic profile) during which the ejection of the air is not necessary. Thus, it prevents the outside air from coming to engulf. The flow of air on the surface of the profile is not altered, which avoids an increase in the induced drag.
    [0006] In particular, the tongue can be fixed flush with the aerodynamic profile, to extend in the continuity of the profile. The latter thus has no discontinuity or roughness likely to disturb the flow of air. The fact that the tongue is flexible and able to lift under the effect of a simple differential pressure between the air located in the ejection nozzle and the outside air has the advantage of not having to provide no mechanism to control its opening. According to an advantageous characteristic, the air ejection device comprises a pressurized chamber ("blowing-box" in English terminology), the ejection nozzle constituting a narrowing of said pressurized chamber, said narrowing being curved in such a manner that the air contained in the pressurized chamber is ejected through the opening tangentially to the profile. In a particular embodiment, the pressurized chamber further comprises stiffeners extending in a plane perpendicular to the longitudinal direction of the opening. In a particular embodiment, the pressurized chamber comprises an air homogenisation plate ("flat baffle" in English terminology) located at the inlet of the ejection nozzle, disposed in said chamber so as to the air entering the ejection nozzle passes through said homogenizer plate. In a particular embodiment, the pressurized chamber, the ejection nozzle and the air homogenization plate located at the inlet of the ejection nozzle are made in one piece. In a particular embodiment, the opening is a slot 30 made over the entire length of the profile. In a particular embodiment, the section of the ejection nozzle in a plane perpendicular to a longitudinal direction of the opening is in the form of a comma.
    [0007] In a particular embodiment, the ejection device comprises, at the opening, stiffeners uniformly distributed over the length of the profile. In a particular embodiment, the flexible tongue consists of several parts of different stiffness along the length of the profile. The invention also relates to a pylon supporting an aircraft propulsion assembly comprising an ejection device according to the invention and finally an aircraft comprising such a device. Other features and advantages will become apparent from the following description, given by way of nonlimiting example and with reference to the accompanying drawings, in which: - Figure 1 is a schematic perspective view of an airplane propelled by two contra-rotating propeller engines mounted downstream of the wings of the aircraft; FIG. 2 is a diagrammatic perspective view of a detail of FIG. 1, including the zone subjected to the swirls caused by a pylon supporting one of the motors; FIG. 3 is a diagrammatic view of a section of the aerodynamic profile of the pylon of FIG. 2, also illustrating the viscous boundary layer on its surface and the air velocity profile downstream of the velocity profile; FIG. 4 is a diagrammatic perspective view of a portion of a pylon for supporting an aircraft propulsion assembly provided with an aerodynamic profile according to one embodiment of the invention; FIG. 5 is a schematic perspective view of a detail of FIG. 4; Figure 6 is a sectional view of a portion of an airfoil according to one embodiment of the invention; FIG. 7a is a diagrammatic perspective view of an air ejection device provided with an air homogenization plate located at the inlet of the ejection nozzle according to a first embodiment; FIG. 7b is a schematic perspective view of an air ejection device provided with an air homogenization plate located at the inlet of the ejection nozzle according to a second embodiment. ; and FIG. 8 is a diagrammatic perspective view of an aerodynamic profile provided with an air ejection device according to a third embodiment of the invention. FIG. 1 (prior art) illustrates an aircraft fuselage 1 comprising a propulsion system 2 comprising a motor contained in a nacelle 4 and thrust propellers 6. A single propeller per propulsion system can also be envisaged. This nacelle 4 is supported and connected to the fuselage 1 by a pylon 8. The term tower refers here to an aerodynamic fairing including the structure 10 supporting the propulsion system and the devices that can be connected to it. These are not represented. As explained above, during the flight, the pylon 8 causes eddies in its wake 10 and turbulence illustrated in Figure 2. Figure 3 illustrates that the thickness of the boundary layer 12 increases progressively in the downstream direction of the profile of the pylon 8, which leads to the velocity profile 14. The velocity profile 14 at the trailing edge 16 of the pylon 8 has a defect (or deficit) in speed Vd in the zone 18 situated downstream of the pylon 8. This speed defect Vd corresponds to the difference between the speed of the free flow 20 Vo and the local speed V in the example considered in FIG. 3. The zone 18 exhibiting this speed defect Vd also has a "mass flow rate defect". Which has the effect of causing air therein in a path shown schematically by the arrow 17. The ejection device 19 illustrated in Figures 4 to 8 overcomes this defect (deficit) speed. In the following, the profile of the ejection device is integrated with that of an aircraft pylon, but it can be mounted on other surfaces of the aircraft. We will therefore speak indifferently of tower, pylon profile or profile of the ejection device. This is an aerodynamic profile. FIG. 4 illustrates a pylon 20 which extends along an axis X and which comprises a primary structure 22 provided with a pressurized chamber ("blowing box" in English terminology) 24 supplied with air by a pipe feeding 26 ("blowing pipe" in English terminology). 3014 4 13 6 The pressurized chamber 24 is located in the trailing edge 28 of the pylon 20. In FIG. 4, for example, it is located at more than half (in fact, it is preferably located at 75% of the tower rope 20) of the tower rope 20, the rope extending along the Z axis.
    [0008] The air coming from the supply pipe 26 comes for example from the engine of the aircraft. It is therefore compressed air recovered by a recovery system not shown, but known from the prior art. It should be noted that in the embodiment shown in FIG. 5, the supply pipe 26 stops at the inlet 29 of the pressurized chamber 24.
    [0009] The inlet 29 is formed in a lateral rib 30 of the pressurized chamber 24 of the trailing edge of the pylon 20. The inlet 29 is dimensioned so as to allow the volume 31 of the pressurized chamber 24 to be supplied with air. In the embodiment shown in FIG. 5, the volume 31 of the pressurized chamber 24 extends from a front rib 32a of the pylon 20 (furthest from the trailing edge 28) to a rear rib 32b (the most close to the trailing edge 28). Thus, this volume 31 includes an intermediate rib 32c of the pylon 20. In an embodiment not shown, the supply pipe 26 may extend beyond the rear spar 30 in the pressurized chamber 24. In this case, the supply pipe 26 passes through the rear spar 30 and extends over all or part of the length of the pylon 20, that is to say along the axis X. In a particular embodiment not shown the supply pipe 26 can be pierced regularly to allow air to escape inside the pressurized chamber 24. The advantage associated with this alternative is to better uniformize the air inside the chamber. volume 31 of the pressurized chamber 24. Once out of the supply pipe 26, the air diffuses into the pressurized chamber 24 as previously seen and escapes through the ejection zone 30 34. ejection 34 forms part of the volume 31 of the pressurized chamber 24 and is s ituated near the front rib 32a. In other words, the ejection zone 34 is remote from the trailing edge 28 of the pylon 20.
    [0010] The ejection zone 34 being the place by which the air escapes from the pressurized chamber 24, it comprises an opening 36 formed in the outer surface of the aerodynamic profile of the pylon 20 and visible more particularly in FIG. 6.
    [0011] In this case, the opening 36 is a slot that extends over the entire length of the profile of the tower 20, in other words along the axis X. It is indeed preferable, in the case of an integrated profile. at a pylon supporting a propulsion propulsion unit, extending the opening 36 along a maximum length along the X axis in order to blow the air over the entire blade of the propeller, or even to - of the. The opening 36 may, however, also extend over only a portion of the length of the profile of the tower 20. In what follows, without limitation, the opening 36 will be called slot.
    [0012] The slot 36 is made here in the extrados 38 of the pylon 20. However, it is also conceivable to practice such a slot 36 in the underside of the aerodynamic profile of the pylon 20, or both on the extrados and the In the following, reference will be made, in a nonlimiting manner, to the embodiment shown in the figures, namely with a slot 36 made in the extrados 38 of the profile of the pylon 20. The ejection zone 34 and the elements of the ejection device 19 which are therewith will now be described in greater detail with reference to FIG. 6, which is a view of the YZ plane perpendicular to the X axis. ejection device 19 comprises an ejection nozzle 42 whose end 44 (end facing the outside of the profile 20) opens into the slot 36. This end 44 is directed more particularly facing the trailing edge 28 of the pylon 20, so that the air that in The end 44 of the ejection nozzle 42 is delimited by a reinforcing edge 46 which extends over all or part of the length of the pylon 20. on the one hand, and on the other hand, by the extrados 38 of the pylon 20. The reinforcing edge 46 is located in an excess thickness with respect to the extrados 38 of the pylon 20, so that the air remains in contact with the extrados 38 of the pylon 20 during its ejection and is directed towards the trailing edge 28. It will be noted that the slot 36 extending over the entire length of the pylon 20, the reinforcing edge 46 extends here over the entire length of the tower 20. The ejection device 19 further comprises a flexible tongue 48 flush with the extrados 38, so as to obstruct the slot 36. It is here attached to the edge of 46. Thus, when no flow of air from the pressurized chamber 24 is ejected by the ejection nozzle 42, the slot 36 is found obstructed. This makes it possible to prevent the air boundary layer flowing on the extrados 38 from rushing into the slot 36. Moreover, since the flexible tongue 48 is fixed flush with the extrados 38, it ensures continuity of the profile of the extrados 38 on both sides of the slot 36. In other words, because of the presence of the flexible tongue 48, the extrados 38 is continuous and smooth from the trailing edge 28 to the reinforcement edge 46. The flow of air on the extrados 38 is not disturbed by the presence of the slot 36, because the flexible tongue 48 does not form any roughness on the surface of the extrados 38 .
    [0013] In an embodiment not shown, the flexible tongue 48 may consist of several parts of different stiffness along the pylon 20 (along the X axis). This allows, as a function of the flexibility of each of the parts, to vary the dimensions of the slot 36 along the pylon 20 and therefore the flow of air blown on the propeller blades of the propulsion system 2.
    [0014] It is thus possible to blow more air on the end of a blade than on the base of the blade. The flexible tongue 48 is also able to lift under the effect of a pressure differential between the air located in the ejection nozzle 42 and the outside air.
    [0015] Preferably, the flexible tongue 48 is made of aluminum, composite material such as carbon fiber reinforced plastic (CFRP for "carbon fiber reinforced plastic" in English terminology) or elastomeric material.
    [0016] Thus, the flexible tongue 48 is raised only during an ejection of the air, in other words only when necessary. The flexible tongue 48 is for example fixed to the reinforcing edge 46 by means of fasteners 49 uniformly distributed over the length of the pylon 20.
    [0017] For example, the fasteners 49 are countersunk fasteners with a diameter of 3.2 mm. Alternatively, in an embodiment not shown, the flexible tongue 48 is fixed to the reinforcing edge 46 by gluing or welding. The interior of the pressurized chamber 24 will now be described in relation to the ejection nozzle 42. In the embodiment shown in the figures, the ejection nozzle 42 constitutes a narrowing of the pressurized chamber 24. In other words, , the air included in the volume 31 of the pressurized chamber 24 passes continuously from the pressurized chamber 24 to the ejection nozzle 42. The surface of the section of the ejection nozzle 42 in the plane YZ perpendicular to the longitudinal direction of the pylon 20 is smaller than the section in the same plane YZ of the rest of the surface of the pressurized chamber 24. The ejection nozzle 42 also has a curved shape so that the air contained in the pressurized chamber 24 is ejected by its end 44 tangentially to the extrados 38 of the pylon. More specifically, the section of the ejection nozzle 42 in a plane perpendicular (YZ plane) to the longitudinal direction (along the X axis) of the slot 36 is comma-shaped, whose curved end 44 is directed towards the trailing edge 28 of the pylon. The other enlarged end of the ejection nozzle 42 opens into the pressurized chamber 24. Such a configuration takes into account the aerodynamic conditions allowing an ejection of the air tangentially to the surface of the aerodynamic profile (in this case profile of pylon 20). In particular, the curved shape of the end 44 implies that the air "turns around" before being ejected. In addition, the curved shape of the end 44 makes it possible to produce an assembly consisting of a pressurized chamber 24 and an ejection nozzle 42 that is compact. This allows in particular to place such an assembly closer to the rear spar 30 of the pylon 20.
    [0018] This has the advantage of moving back as far as possible the position of the rear spar 30 of the primary structure 22 of the pylon, thus making it possible to maximize the rope of the pylon 20 and thus to facilitate its mechanical strength. The comma shape of the ejection nozzle 42 further optimizes the aerodynamic conditions providing air ejection tangentially to the surface of the aerodynamic profile of the pylon 20. FIGS. 7 and 8 illustrate two modes of In the preferred embodiment illustrated in FIG. 7, the pressurized chamber 24 comprises a first portion 24a extending from the curved shape of the ejection nozzle 42. this first portion 24a widening to a second portion 24b. The second portion 24b has a section in the YZ plane of substantially rectangular shape. It thus comprises a flat surface 24e comprising an air homogenization plate 50 ("flat baffle" in English terminology), or separating filter, located at the inlet of the ejection nozzle 42. planar surface 24e is connected firstly to the first portion 24a through a lower joint surface 24c which is perpendicular to the planar surface 24e, and is connected on the other hand to the first portion 24a across a joint surface. upper 24d, slightly oblique with respect to the lower junction surface 24c. The flat surface 24e, and therefore the air homogenizer plate 50, are arranged in the pressurized chamber 24 substantially perpendicular to the extrados 38, in other words in a plane substantially parallel to the XY plane. In the air path from the feed pipe 26, the air homogenizer plate 50 is disposed upstream in the pressurized chamber 24 with respect to the ejection nozzle 42. the supply pipe 26 advantageously crosses the air homogenizer plate 50 in order to be homogenized before it is expanded in the volume 31 of the pressurized chamber 24. In other words, the air homogenisation plate 50 constitutes the inlet of the pressurized chamber 24, through which air from the supply pipe 26 is introduced.
    [0019] Figures 7a and 7b illustrate two possibilities of air homogenizer plate 50 having holes of section and of different shape. Thus, the air homogenizer plate 50 of FIG. 7a includes rectangular holes extending the full length of the filter. In Figure 7b, the air homogenizer plate 50 comprises circular holes, uniformly distributed over several rows, here seven along the entire length and the entire width of the plate. It goes without saying that the size, number, arrangement and shape of the holes 10 may be varied to better suit the ejection requirements, ie the desired pressure and flow rate in the ejection nozzle 42. Thus, preferably, the holes are dimensioned so as to obtain a homogeneous flow. Still according to the embodiment illustrated in FIGS. 7a and 7b, the pressurized chamber 24 further comprises internal stiffeners 52 extending in a plane perpendicular to the longitudinal direction of the slot 36 (the X direction), ie In this case, the internal stiffeners 52 extend in planes parallel to the plane YZ, or else perpendicular to the axis X. structurally the pressurized chamber 24, and thus avoid excessive deformation of the end 44 of the ejection nozzle 42 and therefore of the slot 36 when it undergoes forces during the flight. Indeed, any alteration of the shape of the end 44 may be detrimental to the required constancy of the air flow to be ejected. The reinforcement provided by the internal stiffeners 52 makes it possible to avoid it. The internal stiffeners 52 are preferably uniformly distributed over the length of the pressurized chamber 24. In a particular embodiment, the internal stiffeners 52 are for example made of aluminum and of thickness 2 mm, and arranged every 150 mm. The number of internal stiffener 52 can naturally vary according to the forces experienced by the end 44.
    [0020] The fact that at least one internal stiffener 52 is placed inside the pressurized chamber 24 has the advantage of reinforcing the end 44 of the ejection nozzle 42 without altering the external surface of the pylon 20. This allows the do not disturb the flow of air on its aerodynamic profile.
    [0021] It will be noted that the interval (spacing) between each internal stiffener 52 depends on several factors. Thus, for a manufacturing tolerance of the slot 36 given, the more the material used will be rigid (for example if using titanium rather than aluminum), or even more the internal stiffeners 52 will be thick, and the more it It will be possible to increase the interval between the internal stiffeners 52. On the other hand, for a given material and thickness of the internal stiffener 52, the greater the manufacturing tolerance of the slot 36 will be binding, and the longer the interval between two successive internal stiffeners 52 will have to be reduced. Preferably, the pressurized chamber 24, the ejection nozzle 42 and the air homogenizer plate 50 are made in one piece. The manufacture of such a part is preferably done by three-dimensional printing ("Additive Layer Manufacturing" in English terminology) or foundry. Preferably, the material chosen will be titanium or aluminum, a good compromise between mechanical strength and reduction of the on-board weight. This method of manufacture ensures a better flow of air in the pressurized chamber 24 and in the slot 36 and a better homogenization thereof, thanks in particular to the limitation of defects in the shape of the part. In addition, it allows easy positioning of internal stiffeners 52, which are more difficult to achieve with machining methods. It is therefore not necessary to place external stiffeners on the aerodynamic surface of the tower 20, further limiting the disturbances of its air boundary layer during flight. In an alternative embodiment illustrated in FIG. 8, more suited to conventional machining fabrication, a pressurized chamber 124 is limited to a lower base 126 and an upper base 128, separated by a void space in which the air flows. broadcasts.
    [0022] In this embodiment, the supply pipe (not shown) passes through the pylon 20 along its entire length (along the X axis). The upper base 128 includes an ejection device 119 similar to that of the ejection device 19 of the previous embodiment, except that the reinforcing edge 146 includes external stiffeners 147 distributed evenly along the slot 36. These external stiffeners 147 play the role of the internal stiffeners 52, namely to reinforce the end 44 of the ejection nozzle 42 to prevent its deformations and those of the slot 36 during the flight.
    [0023] The lower base 126 comprises an air homogenizer plate 150 which plays the same role as in the previous embodiment, namely the fact that it is placed so that the air coming from the air duct supply (not shown in this figure), the cross before diffusing into the pressurized chamber 124.
    [0024] This solution is a more economical alternative to the embodiment because it does not rely on three-dimensional printing technology. In an alternative embodiment not shown linked to the preceding, the homogenizing plate is integrated with the ejection nozzle. In this case, the supply pipe stops at the inlet of the pressurized chamber. An advantage of this embodiment is the reduction of the mass of the air ejection device. Of course, the present invention is not limited to the embodiments described above.
    [0025] It will be noted that the air ejection device according to the invention operates regardless of the shape of the pressurized chamber, or even without a pressurized chamber. Conversely, the pressurized chamber as described above can be adapted to any ejection device. Its use, however, is particularly beneficial to the performance of the air ejection device according to the invention.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. An air ejection device comprising a profile (20) provided with an opening (36) and an ejection nozzle (42) opening into the opening (36), characterized in that it comprises a flexible tongue (48) fixed in the continuity of the profile (20) so as to obstruct the opening (36), said flexible tongue (48) being able to lift under the effect of a differential pressure between the air located in the ejection nozzle (42) and the outside air. 10
    [0002]
    2. An air ejection device according to claim 1, characterized in that it further comprises a pressurized chamber (24; 124), the ejection nozzle (42) constituting a narrowing of said pressurized chamber (24). said narrowing being bent so that the air contained in the pressurized chamber is ejected through the opening (36) tangentially to the profile (20). 15
    [0003]
    An air ejection device according to claim 2, characterized in that the pressurized chamber (24; 124) comprises stiffeners (52) extending in a plane perpendicular to the longitudinal direction of the opening (36). .
    [0004]
    An air ejection device according to claim 2 or 3, characterized in that the pressurized chamber (24; 124) comprises an air homogenizer plate (50; 150) located at the inlet of the ejection nozzle (42) disposed in said chamber (24; 124) so that air entering the ejection nozzle (42) passes through said homogenizer plate (50; 150).
    [0005]
    5. An air ejection device according to claim 4, characterized in that the pressurized chamber (124), the ejection nozzle (42) and the air homogenizer plate (50) are made of one piece.
    [0006]
    6. An air ejection device according to one of the preceding claims, characterized in that the opening (36) is a slot made over the entire length of the profile (20).
    [0007]
    7. An air ejection device according to one of the preceding claims, characterized in that the section of the ejection nozzle (142) in a plane perpendicular to a longitudinal direction of the opening (36) is in comma form.
    [0008]
    8. An air ejection device according to any one of the preceding claims, characterized in that it comprises, at the opening (36), stiffeners (52; 147) uniformly distributed over the length of the profile. (20).
    [0009]
    9. An air ejection device according to any one of the preceding claims, characterized in that the flexible tongue (48) consists of several parts of different stiffness along the length of the profile (20).
    [0010]
    10. Pylon supporting an aircraft propulsion unit comprising an air ejection device according to any one of the preceding claims. 10
    [0011]
    Aircraft comprising an air ejection device according to any one of claims 1 to 9.
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    同族专利:
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    法律状态:
    2015-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-22| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210805 |
    优先权:
    申请号 | 申请日 | 专利标题
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    GB1421454.8A| GB2522531B|2013-12-05|2014-12-03|Air ejection device comprising an aerodynamic profile provided with a slot obturating flexible tongue|
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    US14/561,488| US9656742B2|2013-12-05|2014-12-05|Air ejection device comprising an aerodynamic profile provided with a slot obturating flexible tongue|
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