• 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 present invention relates to a nacelle for a turbojet, comprising an outer cowling (3) comprising an inner wall defining, with a fixed internal structure, an annular channel (15) for the flow of a secondary air flow, and a nozzle ( 9) for ejecting said secondary air stream, said nozzle comprising: at least one opening (19), at least one continuous downstream end portion (21), downstream of said opening, at least one door (17), ) movable between a closed position and an open position allowing passage of a portion of said air flow through said opening (19). The nacelle according to the invention is remarkable in that it comprises means for actuating the shaped door, when activated from a closed position to an open position of the door, for driving said door in a movement combined translation upstream of the nacelle and rotation to the outside of the nacelle.
    公开号:FR3021704A1
    申请号:FR1454927
    申请日:2014-05-30
    公开日:2015-12-04
    发明作者:Sarah Tissot；Xavier Bouteiller；Olivier Kerbler；Patrick Gonidec
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The present application relates to a nacelle for an aircraft turbojet comprising a secondary nozzle with downstream doors. An aircraft is moved by several turbojets each housed in a nacelle.
    [0002] A nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing a thrust reverser device and intended to surround the combustion chamber of the turbojet engine. , and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine. This nacelle is intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow), from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular channel, also called vein, formed between a fairing of the turbojet engine and an inner wall of the nacelle. The two air flows are ejected from the turbojet engine from the rear of the nacelle. The thrust reversal device is, during landing of the aircraft, intended to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine. In this phase, the thrust reverser device obstructs the stream of cold air flow and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of The aircraft, the means used to achieve this reorientation of the cold air flow vary according to the type of inverter. The means used to achieve this reorientation of the cold flow vary according to the type of inverter. However, the structure of an inverter generally comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a retracted position. in which they close this passage. These covers can perform a deflection function or simply activation other means of deflection. Furthermore, in addition to its thrust reversal function, the inverter cover 35 belongs to the downstream section of the nacelle and has a downstream part forming the ejection nozzle for channeling the ejection of the air flows.
    [0003] 3021704 2 The optimum section of the ejection nozzle can be adapted according to the different flight phases, namely the take-off, climb, cruise, descent and landing phases of the aircraft. The already well-known advantages of such adaptive nozzles, also called variable section nozzles, include noise reduction or fuel consumption reduction. Among the nozzles with variable section according to the prior art, one notably knows that described in the patent application published under the number FR 2 622 929, an embodiment of which is shown in FIG.
    [0004] This application relates to a nacelle 1 for a turbojet, comprising a fixed internal structure 2 and an outer cowling 3 comprising an upstream section 5 and a downstream section 7 comprising a variable geometry nozzle 9. A ring 10 of the downstream section of the cowling 3 is mounted axially sliding so as to create an opening 11 in the outer cowling 3. This opening 11 allows a portion of the air flow 13 flowing in the annular channel 15 to be ejected, which amounts to widening the section of the nozzle formed by the hood. Although this type of nacelle makes it possible to vary the section of the nozzle effectively, it has certain drawbacks. The mechanical connection between the upstream section 5 and the downstream section 7 of the outer cowling 3 constitutes a mechanical weakening of the nacelle. In addition to weakening the thrust reverser hood, this mechanical linkage can also cause vibrations of the annular downstream section of the hood during engine operation. Also known from the prior art the variable geometry nozzle 9 described in the patent application published under the number FR 2 946 696, shown in Figure 2, wherein the variation of the output section is achieved via of doors 17 mounted movable in rotation 30 between a position in which they close an opening 19 of the outer cowling 3 and a position in which they release said opening so as to eject part of the secondary air flow 13 to the outside of the nacelle and, consequently, to increase or reduce the output section of the nacelle.
    [0005] As shown, this variable geometry nozzle 9 comprises a continuous downstream end portion 21, downstream of the opening 19 and the doors 3021704 3 17, which makes it possible to substantially increase the structural strength of the nacelle, and to solve the disadvantages of the prior art. However, for a significant opening of the door, that is to say for pivoting of the sufficiently large door 17 (position not shown) to let a sufficient quantity of secondary air flow from the annular channel 15 pass, the flow of air which passes through the opening of the outer cowl and which escapes from the nacelle diverges, and is directed in a direction substantially transverse to the longitudinal axis of the nacelle. Such divergence of the airflow greatly affects the aerodynamic profile of the nacelle, and deteriorates the thrust performance of the propulsion unit. In addition, the doors of this nozzle have a relatively wide and flat trailing edge 23, which causes a phenomenon of base drag, also affecting the aerodynamic profile of the nacelle and limit the performance of the nozzle. The present invention aims to solve these disadvantages, and relates to this effect to a nacelle for an aircraft turbojet comprising: a fixed internal structure at least partially defining a fairing of a turbojet, an external cowling comprising an upstream section and a downstream section, said downstream section comprising an outer wall and an inner wall defining, with the fixed internal structure, an annular flow channel of a secondary air flow, said downstream section comprising a nozzle for ejecting said flow of secondary air, said nozzle comprising: at least one opening defined in the downstream section of the outer cowling, at least one downstream end portion continuing, downstream of said opening, at least one door, acoustically treated or otherwise, movable alternately when activating actuating means, between a closed position closing said opening and ensuring aerodynamic continuity of the nacelle, and an open position allowing the passage of at least a portion of the secondary air flow through said opening, from the annular channel to the outside of the nacelle, said nacelle being remarkable in that the means of When actuating said means from a closing position to an open position of the door, said actuation is configured to drive said door in a combined upward movement of the nacelle and of rotation towards the door. outside the basket. Thus, by providing actuating means shaped to drive a secondary nozzle door both in translation upstream of the nacelle and in rotation towards the outside of the nacelle, the opening amplitude of the nacelle is limited. door while meeting the requirements of variation of the outlet section of the nozzle. In other words, such kinematic opening of the door makes it possible to move the door in a position which makes it possible to redirect the flow of secondary air escaping from the opening of the nacelle downstream of the nacelle in the direction of the longitudinal axis of the nacelle, along the outer wall of the outer casing of the nacelle. Thanks to this kinematics, the angle of rotation of the door remains modest; this limits the divergence of the air flow that escapes from the opening, which makes it possible to control and substantially improve the aerodynamic performance of the nacelle.
    [0006] Thus, by converging the flow of secondary air escaping from the opening provided in the outer casing of the nacelle, it improves, ultimately, the thrust performance of the propulsion system. According to all the optional features of the nacelle according to the invention: the actuating means comprise: at least one actuator comprising an upstream body integral with a fixed part of the nacelle, and a rod of which one end is directly connected an upstream wall of said door, and 30 o at least one connecting rod whose one end is connected to the outer cover of the nacelle and the other end is connected to the door of the nozzle; the door comprises a trailing edge shaped to at least partially cover the continuous downstream end portion of the nozzle, which makes it possible to define an aerodynamic continuity of the inner wall and the outer wall of the nacelle at the level of the zone between the door and the continuous downstream end portion of the nozzle; the trailing edge of the door has a curved profile, which makes it possible to improve the convergence of the flow of air ejected towards the longitudinal axis of the nacelle; the trailing edge of the door has a tapered profile so that the tangent to the underside of the door is substantially parallel to the wall of the continuous downstream end portion positioned facing the trailing edge of the door, which allows the channeling the secondary air flow in a direction substantially parallel to the longitudinal axis of the nacelle, thereby improving the thrust of the propulsion unit; - Sealing means are disposed between the door and the outer cover, and are arranged to oppose the flow of air around the door and through the opening when the door is in the closed position this prevents air circulating in the annular channel from flowing through the door and the associated opening when the door is in the closed position; - The door or the outer cowling further comprises at least one side flap fixed or movable near the opening; the upstream section of the outer cowling and the continuous downstream end portion of the nozzle are made in one piece, which ensures good structural strength of the nacelle; - The door in the closed position allows a controlled leakage flow through the channel to obtain a nacelle drag gain; the nozzle comprises a plurality of openings which are circularly distributed around a longitudinal axis of the nacelle and which are each closed off by a door when said door is in its closed position; - the door can be treated acoustically; a thrust reverser device, equips the nacelle according to the invention. Other features and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the accompanying drawings, in which: FIG. 1 illustrates in longitudinal section a nacelle of the art prior art, comprising a nozzle of variable geometry comprising a downstream ring movable in translation; FIG. 2 shows in longitudinal section a nacelle according to the prior art equipped with a nozzle of variable geometry in which the variation of the outlet section of the nozzle is achieved by means of rotating gates; FIG. 3 is an isometric view illustrating a propulsion assembly comprising a nacelle according to the invention surrounding an aircraft turbojet engine; - Figure 4 shows the nacelle in longitudinal section along lines A-A and B-B of Figure 3, the door being shown in the closed position; - Figure 5 is an isometric view of the door, illustrating an alternative embodiment of the connection between the actuator and the door; FIG. 6 is an isometric view of the door, centered on its side wall, illustrating a mode of connection between the door and the fixed structure of the nacelle; - Figure 7 is a view centered on the door of the nozzle equipping the nacelle according to the invention, the door being shown in the closed position; Figure 8 is a cross-sectional view along the line C-C of Figure 7; FIG. 9 represents the nacelle in longitudinal section along the lines A-A and B-B of FIG. 3, the door being represented in the open position; - Figures 10 to 13 illustrate the nacelle in longitudinal section 25 along the line A-A of Figure 3, on which are shown four alternative embodiments of the sealing means provided between the door and the outer cowl of the nacelle; FIG. 14 is a view centered on the door of the nozzle equipping the nacelle according to the invention, the door being shown in the closed position and being equipped with lateral flaps. Note that in the description and in the claims, the terms "upstream" and "downstream" must be understood in relation to the flow of air flow inside the propulsion assembly formed by the nacelle and the 35 turbojet, that is to say from left to right with reference to FIGS. 1 to 14.
    [0007] Likewise, the terms "internal" and "external" will be used in a nonlimiting manner with reference to the radial distance relative to the longitudinal axis of the nacelle, the expression "internal" defining a radially closer zone. the longitudinal axis of the nacelle, as opposed to the term "external". Moreover, in the description and the claims, to clarify the description and the claims, the longitudinal, vertical and transverse terminology will be adopted in a nonlimiting manner with reference to the direct trihedron L, V, T indicated in the figures, whose longitudinal axis L is parallel to the longitudinal axis 29 of the nacelle shown in FIG. 3. In addition, throughout the figures, identical or similar references represent identical or similar members or sets of members.
    [0008] Referring to FIG. 3, there is shown a propulsion unit 25 comprising a nacelle 1 according to the invention surrounding a turbojet engine 27. The nacelle 1 is intended to be suspended from a reactor pylon (not shown) by the intermediate an attachment island (not shown) forming a link interface. The nacelle 1 comprises an outer cowling 3 comprising an upstream section 5 and a downstream section 7 comprising a variable geometry nozzle 9 for ejecting a part of the secondary air stream circulating in an annular channel 15 defined between the fixed internal structure the nacelle and the inner wall of the outer cowl. The variable geometry nozzle 9 comprises a plurality of openings 19 (one of which is visible in FIG. 9), for example four (only two openings are visible in FIG. 3), distributed in a circular manner around a longitudinal axis 29 of the nacelle.
    [0009] Of course, the nozzle may well comprise more than four openings, for example six. It can also (on nacelles of small diameter) to understand only two or three. These openings each have a radially outwardly open slot shape 31 of the nacelle 1, and define a passage between the annular channel 15 for circulating the secondary air flow and the outside 31 of the nacelle.
    [0010] These openings are each closed by a door 17 movable alternately between a closed position closing its associated opening 19 and an open position allowing the passage through said opening 19 of at least a portion of the secondary air flow, from the annular channel 15 to the outside 31 of the nacelle. To avoid burdening the description, only an assembly consisting of an opening 19 and an associated door 17 is described in detail later, the openings 19 and the associated doors 17 being all similar. Downstream of these openings, the variable geometry nozzle 9 10 has a continuous downstream end portion 21, formed integrally with the upstream section 5 of the outer cowling 3. In other words, the entire outer cowling 3 , further comprising the upstream section 5 and the continuous downstream end portion 21, is made in one piece, and the openings 19 are formed in this outer casing.
    [0011] FIG. 4 illustrates the nacelle 1 seen in longitudinal section along planes passing respectively through the lines A-A and B-B of FIG. 3, the door 17 being represented in the closed position. The door 17 comprises an inner wall 33 and an outer wall 35. The inner 33 and outer 35 walls are immobile with respect to each other, which simplifies the design with respect to a door comprising an internal skin and a outer skin moving relative to each other. The inner and outer walls of the door are structurally interconnected by an upstream wall 37, two side walls 39 and a downstream wall 41 defining a trailing edge 43 of the door 17. This structure can of course be reinforced by rails or internal frameworks according to the practices recognized by those skilled in the art. The door 17 can receive an acoustic treatment, for example sandwich type. On thin lines this sandwich can advantageously fill the entire interior of the structure between the walls 33 and 35.
    [0012] When the door 17 occupies its closed position, the inner wall 33 of the door ensures an internal aerodynamic continuity of the nacelle, so as not to disturb the flow of the air flow in the annular channel 15, and the outer wall 35 of the the door provides external aerodynamic continuity of the fairing of the nacelle.
    [0013] The aerodynamic continuity of both the inner wall and the outer wall of the nacelle cowling is provided at the junction 3021704 9 between the trailing edge 43 of the door and the downstream end portion 21 of the nozzle, thanks to to a particular profile of the trailing edge. For this purpose, the trailing edge 43 of the door has a curved profile 44 advantageously covering an upstream portion 45 of the continuous downstream end portion 21 of the nozzle.
    [0014] The trailing edge 43 has a lower surface comprising a downstream portion 47 of reduced thickness with respect to an upstream portion 49 of said trailing edge. The trailing edge 43 has a tapered profile so that the tangent to the underside of the door 17 is substantially parallel to the wall of the extreme downstream portion 21 positioned opposite the trailing edge of the door. In other words, the trailing edge 43 is located in the extension of an outer wall of the outer casing of the nacelle so as to define an aerodynamic continuity of the outer casing of the nacelle. The door 17 is also capable of being set in motion by an actuator 51 of the jack type, comprising an upstream body (not shown) integral with a fixed part of the nacelle, for example the external cowling of the nacelle, and an actuating rod 53, a free end of which is directly connected to the upstream wall 37 of the door 17. This type of actuator, for example an electric actuator, is well known to those skilled in the art and will therefore not be described further. . The rod 53 of the actuator 51 is slidably mounted longitudinally in the associated body along an axis substantially parallel to the longitudinal axis of the nacelle, and the door 17 is pivotally mounted on the end 54 of the rod 53 of the actuator 51.
    [0015] A single actuator is sufficient for moving a door. However, if the person skilled in the art finds it of particular interest, several actuators 51 can be connected to the door 17. Alternatively, a single actuator 51 connected to a device for returning motion causes a plurality of moving doors.
    [0016] The door 17 is furthermore connected to the outer cowling of the nacelle by means of rods 55 mounted on the side walls 39 of the door 17. Each side wall 39 of the door 17 receives two connecting rods 55, the first of which is mounted near the upstream wall 37 of the door, and the second is mounted downstream of the first.
    [0017] The arrangement of the connecting rods is optimized according to the kinematics and their structural efficiency. The connecting rods 55 are almost tangent to the inner wall or to the outer wall of the door. This arrangement makes it possible to better transmit the forces of the door 17 towards the outer cowling 3. According to a variant shown in FIG. 5, the end 54 of the rod of the actuator (not shown) can be connected to the door 17 by two rods 56, 58 positioned in the continuity of the actuator and forming a "V", to stabilize the movement of the door 17 and to avoid a torsion of the door. According to another variant shown in FIG. 6, each side wall 10 of the door receives three connecting rods 55. According to this embodiment, two connecting rods forming a "V" are mounted near the upstream wall 37 of the door, and one connecting rod is mounted downstream of the connecting rods forming a "V". This embodiment allows a good stabilization of the movement of the door. As shown in more detail in FIGS. 7 and 8 to which reference is now made, a first end 57 of the connecting rod 55 is connected to the outer cowling 3 of the nacelle via a link 59, and a second end 61 of the rod 55 is connected to the side wall 39 of the door 17 via a link 63. The passage of a door from its closed position 20 shown in Figure 4 to its open position shown in Figure 9, is described below. The actuator 51 is activated so as to cause upstream translation of the nacelle of the rod 53, whose end 54 is connected to the upstream wall 37 of the door 17.
    [0018] Simultaneously with the translational movement of the door upstream of the nacelle, the connecting rods 55, connected to the door 17 and to the external cowling of the nacelle, which is fixed, cause the door 17 to rotate in the opposite direction 31 of the nacelle. The door 17 moves in one piece, that is to say that the inner and outer walls 33 and 35 of the door pivot about the same axis of instantaneous rotation, parallel to an axis connecting the dots. 59 tie connecting rods on the outer cowling 3 on both sides of the nacelle. The door 17 is then in an open position, permitting an escape of a portion of the secondary air flow flowing from the secondary flow towards the outside of the nacelle through the opening 19, as shown 3021704 11 schematic arrow F, and the output section of the secondary nozzle is thus increased. Thanks to the particular kinematics of door opening which has just been described, according to which the door is both driven in translation upstream and in rotation, the flow of air passing through the opening 19 of the nozzle is advantageously projected. downstream of the nacelle, in the direction of the longitudinal axis of the nacelle, along an outer wall 65 of the outer cowling 3 of the nacelle, which makes it possible to ensure the convergence of the flow of air which escape from the opening 19, and to control and substantially improve the aerodynamic performance of the nacelle. In addition, the curved profile 44 of the trailing edge 43 of the door 17 also improves the convergence of the air flow ejected towards the longitudinal axis of the nacelle. Referring now to Figures 10 to 13 illustrating the nacelle in longitudinal section along the line AA of Figure 1, which show four embodiments of sealing means disposed between the door 17 and the outer cover 3 of the nacelle to prevent air flowing in the annular channel 15 from flowing through the door 17 and the associated opening 19 when the door 17 is in the closed position.
    [0019] With reference to FIG. 10, the door 17 is equipped with an upstream seal 67 and a downstream seal 69, both formed of elastomeric material, forming a sealing means between the door 17 and the associated opening 19 of the outer cover 3, when the door 17 is in its closed position. For this purpose, the upstream gasket 67, for example bubble or lip, is interposed between an upstream end portion 71 of the outer wall 35 of the door 17 and the outer wall 65 of the outer cover 3. The upstream gasket 67 can regardless of being supported by the door 17 or by the outer cover 3. Similarly, the downstream gasket 69, for example flat, is interposed between the outer wall 35 of the door and the outer wall 65 of the outer cover. The downstream gasket 69 is supported by the door 17 so as not to disturb the flow when opening it. Alternatively, the seal 69 comprises reinforcements arranged so as to allow a recovery of the seal towards the inner face of the door during its opening. This ensures a good redirection of the air flowing at the trailing edge 43 of the door while providing a tapered profile of the trailing edge.
    [0020] In this embodiment the seal 69 is then resiliently constrained to align with the outer skin of the continuous downstream end portion 21 as the door moves from its open position to its closed position. The seal advantageously constitutes an excellent aerodynamic smoothing joint 5 of the junction zone between the door 17 and the continuous downstream end portion 21. With reference to FIG. 11, the sealing of the door 17 is ensured on the one hand by the seals 67 and 69 previously described, and secondly by a second downstream seal 73, also formed of elastomeric material, for example bubble or lip, interposed between the downstream wall 41 of the door 17 and the upstream part 45 of the continuous downstream end portion 21 of the external cowling nozzle 3. Referring to FIG. 12, the seal of the door 17 is provided on the one hand by the seal 67 and on the other hand by a downstream seal 75 formed of elastomeric material.
    [0021] The downstream seal 75 is integrated with the wall of the continuous downstream end portion 21 so as to limit the aerodynamic disturbance when the door is open, and to accommodate the shape of the trailing edge 43 of the door when the latter is sinking. in the seal 75 when the door 17 is in the closed position. The downstream gasket 75 may equally well be supported by the door 17 or by the outer casing 3, adapting its shape to these two different cases of different figures. Finally, with reference to FIG. 13, the seal of the door 17 is ensured by the upstream and downstream gaskets 73 and 75. The downstream gasket 75 is advantageously prestressed when the door 17 is in the closed position and deforms towards the end. on opening the door in order to align the secondary air flow through the opening 19 as parallel as possible to the outer wall 65 of the downstream end portion 21 of the outer casing 3, while minimizing the base drag at the trailing edge 43 of the door 17 when said door is in the open position. According to an alternative embodiment not shown, no sealing means is provided between the trailing edge 43 of the door 17 and the continuous downstream end portion 21. In this case contact points adapted in terms of stiffness and thickness are arranged between these two parts or at the interface of the door and the outer cowling. The channel obtained in this configuration is advantageously convergent and captures the boundary layer of the secondary flow to accelerate the outer boundary layer along the rear body, thereby contributing to a drag reduction of the nacelle.
    [0022] The door 17 may advantageously be equipped with a lateral sealing means provided between the door 17 and the associated opening 19 of the outer casing 3, to prevent lateral or transverse air leaks, that is to say ie in a direction perpendicular to the longitudinal axis of the nacelle, between the door 17 and the associated opening 19, when the door 17 is in its closed position. The lateral sealing means comprises a first lateral seal (not shown) interposed between a first longitudinal lateral edge 79 of the door 17 and a first longitudinal complementary lateral edge 81 of the outer wall 65 of the outer cowling 3. By symmetry, the lateral sealing means comprises a second lateral seal (not shown) interposed between a second longitudinal lateral edge 85 of the door 17 and a second longitudinal complementary lateral edge 87 of the outer wall 65 of the outer casing 3.
    [0023] In addition, in order to prevent air from flowing from the sides of the door 17, the door 17 may advantageously comprise rigid lateral flaps 89 arranged on each side of the door 17, as can be seen Figure 14. A movable lateral flap device connected to the door by means of knuckle connections may, however, replace the rigid lateral flaps 89 fixed to the door. The aforementioned flaps contribute to an axial flow of secondary air flow through the opening 19 downstream of the nacelle, which improves the thrust performance of the propulsion system.
    [0024] According to an alternative not shown in the figures, the lateral flaps are supported not by the door itself but by the outer cowling. As before, it may be provided to connect these lateral flaps to the outer cowl by means of ball joints so that the side flaps are in a closed position in which they are folded over the door when the door is in the closed position, and are in an open position in which the flaps extend along the side walls of the door when the door passes from its closed position to its open position.
    [0025] According to yet another alternative, the side flaps are both supported by the door and the outer cowling, which allows a smooth aerodynamic surface to be provided when the door is in the closed position and to avoid jets. diverging when the door is in the open position. It should be noted that the description was made in connection with a smooth, i.e., non-equipped, thrust reverser. However, the nozzle according to the invention can equip a nacelle provided with secondary flow thrust reversal means of all types, grids or doors.
    [0026] Such thrust reversal devices are well known to those skilled in the art and will not be further described in the present description. In this case, the doors of the nozzle are positioned downstream of the grids and / or doors of the inverter. When the platform is equipped with thrust reversal means, the actuators of the nozzle gates and the inverter cover (s) may be common or segregated. The upstream body of an actuator is mounted on the body 3 surrounding the door 17. In addition, primary locks are shaped to prevent deployment of the inverter regardless of the position of the doors 17. Thanks to the present invention, by providing actuating means shaped to drive a secondary nozzle door both in translation upstream of the nacelle and in rotation towards the outside of the nacelle, the range of opening of the door is limited while satisfying the requirements of variation of the outlet section of the nozzle. In other words, such a kinematic opening of the door makes it possible to move the door in a position which makes it possible to redirect the flow of secondary air escaping from the opening of the nacelle towards the downstream side of the door. nacelle, in the direction of the longitudinal axis of the nacelle, along the outer wall of the outer cowl of the nacelle. This limits the divergence of the air flow that escapes from the opening, which makes it possible to control and substantially improve the aerodynamic performance of the nacelle.
    [0027] Thus, by converging the flow of secondary air escaping from the opening provided in the outer cowling of the nacelle, it improves, ultimately, the thrust performance of the propulsion system. In addition, the continuous downstream end portion of the nozzle makes it possible to substantially increase the structural strength of the nacelle. Finally, it goes without saying that the invention is not limited to the embodiments of this nacelle, described above solely as illustrative examples, but it encompasses all the variants involving technical equivalents. described means and combinations thereof if they fall within the scope of the invention.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Nacelle (1) for an aircraft turbojet engine comprising: - a fixed internal structure (2) at least partially defining a fairing of a turbojet engine, - an external cowling (3) comprising an upstream section (5) and a downstream section ( 7), said downstream section comprising an outer wall (65) and an inner wall defining, with the fixed internal structure (2), an annular channel (15) for the flow of a secondary air flow, said downstream section comprising A nozzle (9) for ejecting said secondary air stream, said nozzle comprising: at least one aperture (19) defined in the downstream section of the outer casing, at least one continuous downstream end portion (21), downstream of said opening, 15 o at least one door (17), acoustically treated or not, movable alternately, when activating actuating means, between a closed position closing said opening and providing aerodynamic continuity of the nacelle , and an authorized open position passing at least a portion of the secondary air flow through said opening (19) from the annular channel (15) to the outside (31) of the nacelle, said nacelle being characterized in that the actuating means are formed, upon activation of said means from a closing position to an open position of the door, for driving said door (17) in a combined translational movement upstream of the nacelle and rotation to the outside of the nacelle.
    [0002]
    2. Nacelle (1) according to claim 1, characterized in that the actuating means comprise: - at least one actuator (51) comprising an upstream body integral with a fixed part of the nacelle, and a rod (53 ), one end of which is directly connected to an upstream wall (37) of said door (17), and - at least one connecting rod (55), one end (57) of which is connected to the outer casing (3) of the nacelle and another end (61) is connected to the door (17) of the nozzle (9). 3021704 17
    [0003]
    3. Nacelle (1) according to one of claims 1 or 2, characterized in that the door (17) comprises a trailing edge (43) shaped to cover at least partially the continuous downstream end portion (21) of the nozzle (9).
    [0004]
    4. Nacelle (1) according to claim 3, characterized in that the trailing edge (43) of the door (17) has a curved profile (44).
    [0005]
    Nacelle (1) according to one of claims 3 or 4, characterized in that the trailing edge (43) of the door (17) has a tapered profile so that the tangent to the underside of the door is substantially parallel to the wall of the continuous downstream end portion (21) positioned opposite said trailing edge.
    [0006]
    6. Nacelle (1) according to any one of claims 1 to 5, characterized in that it comprises sealing means disposed between the door (17) and the outer cowl (3) arranged to oppose the flow of air around the door (17) and through the opening (19) when the door (17) is in the closed position.
    [0007]
    7. Platform (1) according to any one of claims 1 to 6, characterized in that the door (17) or the outer cover (3) further comprises at least one lateral flap (89) fixed or movable near the 25 the opening (19).
    [0008]
    8. Nacelle (1) according to any one of claims 1 to 7, characterized in that the upstream section (5) of the outer cowling (3) and the continuous downstream end portion (21) of the nozzle (9) are realized in one piece.
    [0009]
    9. Platform (1) according to any one of claims 1 to 8 characterized in that the door (17) in the closed position passes a controlled leakage rate in the channel (19) to obtain a drag gain bucket . 35
    [0010]
    10. Nacelle (1) according to 1 to 9, characterized in that it further comprises a thrust reverser device.
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    FR2962492A1|2012-01-13|THRUST INVERSION DEVICE WITH FRONT FRAME AERODYNAMIC JUNCTION
    FR2943749A1|2010-10-01|RIBBON EQUIPPED WITH AT LEAST ONE MEANS OF SELF-ALIGNMENT
    CA2858504A1|2013-06-27|Door for a thrust reverser with doors
    EP2635789A2|2013-09-11|Aircraft turbojet engine thrust reverser with a lower number of actuators
    EP3488094B1|2020-04-22|System for actuating a panel of a turbojet engine pod
    FR3018863A1|2015-09-25|NON-GRILLED PUSH REVERSING DEVICE FOR AIRCRAFT TURBO BOREHOLE
    EP3004614A1|2016-04-13|Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls
    EP3740666A1|2020-11-25|Rear assembly of a nacelle of a turbojet engine of an aircraft comprising a sliding cascade thrust reverser
    同族专利:
    公开号 | 公开日
    RU2688082C2|2019-05-17|
    RU2016150900A3|2018-11-30|
    EP3149318A1|2017-04-05|
    CN106662040B|2019-10-08|
    CN106662040A|2017-05-10|
    WO2015181471A1|2015-12-03|
    US10100780B2|2018-10-16|
    US20170082064A1|2017-03-23|
    FR3021704B1|2016-06-03|
    RU2016150900A|2018-07-02|
    EP3149318B1|2018-08-22|
    CA2949746A1|2015-12-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3764096A|1972-02-24|1973-10-09|Rohr Industries Inc|Thrust reversing apparatus|
    WO2008003889A2|2006-07-05|2008-01-10|Airbus France|Method for reversing the thrust produced by a power plant of an aircraft, device for implementing it and nacelle equipped with said device|
    EP2433864A1|2010-09-23|2012-03-28|Airbus Operations|Air-discharge device for an airplane turbofan engine|
    WO2013021108A1|2011-08-05|2013-02-14|Aircelle|Turbojet engine nacelle having a variable nozzle|
    EP2730773A2|2012-11-13|2014-05-14|Rolls-Royce plc|A gas turbine engine exhaust nozzle|
    US4605169A|1983-12-27|1986-08-12|United Technologies Corporation|Exhaust nozzle construction|
    FR2622929A1|1987-11-05|1989-05-12|Hispano Suiza Sa|DRIVE INVERTER OF GRID TURBOREACTOR, WITH VARIABLE EJECTION SECTION|
    FR2741910B1|1995-11-30|1998-01-02|Hispano Suiza Sa|DOOR REVERSER OF TURBOJET WITH DOORS WITH ARTICULATED REAR PANEL|
    FR2910937B1|2007-01-02|2009-04-03|Airbus France Sas|AIRCRAFT REACTOR NACELLE AND AIRCRAFT COMPRISING SUCH A NACELLE|
    FR2929998B1|2008-04-14|2011-08-12|Aircelle Sa|DOUBLE FLOW TURBOREACTOR NACELLE|
    FR2946696B1|2009-06-10|2012-04-20|Aircelle Sa|PUSH REVERSING DEVICE|
    FR2967399B1|2010-11-16|2012-11-02|Aircelle Sa|NACELLE FOR TURBOJET DOUBLE FLOW OF AN AIRCRAFT|
    US9103298B2|2011-12-29|2015-08-11|Rohr, Inc.|Seal for a variable area fan nozzle|
    FR3011820B1|2013-10-11|2017-03-31|Aircelle Sa|NACELLE FOR AIRCRAFT ENGINE WITH VARIABLE SECTION TUBE|FR3054266B1|2016-07-25|2018-08-31|Safran Nacelles|SYSTEM FOR ACTUATING A PANEL OF TURBOJET CAPACITY|
    US10752371B2|2016-09-30|2020-08-25|General Electric Company|Translating nacelle wall for an aircraft tail mounted fan section|
    US10738737B2|2016-11-18|2020-08-11|Rohr, Inc.|Self-locking alignment at a nacelle interface|
    FR3075274B1|2017-12-14|2021-10-22|Airbus Operations Sas|AIRCRAFT TURBOREACTOR CONTAINING MEANS ALLOWING TO VARY ITS EXIT SURFACE|
    法律状态:
    2015-03-31| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-04| PLSC| Search report ready|Effective date: 20151204 |
    2016-04-28| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2018-05-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454927A|FR3021704B1|2014-05-30|2014-05-30|NACELLE FOR AIRCRAFT TURBOREACTOR COMPRISING A SECONDARY PIPE WITH ROTARY DOORS|FR1454927A| FR3021704B1|2014-05-30|2014-05-30|NACELLE FOR AIRCRAFT TURBOREACTOR COMPRISING A SECONDARY PIPE WITH ROTARY DOORS|
    PCT/FR2015/051323| WO2015181471A1|2014-05-30|2015-05-20|Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors|
    RU2016150900A| RU2688082C2|2014-05-30|2015-05-20|Turbojet engine nacelle comprises a secondary loop nozzle with rotatable flaps|
    EP15729539.5A| EP3149318B1|2014-05-30|2015-05-20|Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors|
    CA2949746A| CA2949746A1|2014-05-30|2015-05-20|Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors|
    CN201580028435.XA| CN106662040B|2014-05-30|2015-05-20|Aircraft turbojet engine nacelle including the secondary nozzle with revolving door|
    US15/364,623| US10100780B2|2014-05-30|2016-11-30|Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors|
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