• 专利附录
  • 专利说明
  • 权利要求
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    • 专利摘要:
    The present invention relates to a nacelle for an aircraft turbojet, comprising a thrust reverser device, said nacelle comprising: - a fixed structure and - a mobile structure displaceable in translation along an axis substantially parallel to a longitudinal axis of the nacelle, between a retracted position in which it provides aerodynamic continuity with said fixed structure of the nacelle during operation of the nacelle direct jet and a deployed position in which it opens a passage for the circulation of a flow of secondary air deflected during operation of the inverted jet nacelle. The nacelle is remarkable in that it comprises at least one position sensor (67) designed and arranged in the nacelle to detect a deformation of the mobile structure exceeding a predetermined predetermined deformation threshold.
    公开号:FR3059646A1
    申请号:FR1662073
    申请日:2016-12-07
    公开日:2018-06-08
    发明作者:Olivier KERBLER；Laurent Georges Valleroy；Corentin Hue；Alexis Heau
    申请人:Safran Nacelles SAS；
    IPC主号:
    专利说明:

    © Publication no .: 3,059,646 (to be used only for reproduction orders)
    ©) National registration number: 16 62073 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : B 64 D 29/00 (2017.01), F 02 K 1/70
    A1 PATENT APPLICATION
    ©) Date of filing: 07.12.16. (© Applicant (s): SAFRAN NACELLES Company by (30) Priority: simplified actions - FR. @ Inventor (s): KERBLER OLIVIER, VALLEROY LAURENT GEORGES, HUE CORENTIN and HEAU (43) Date of public availability of the ALEXIS. request: 08.06.18 Bulletin 18/23. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ©) Holder (s): SAFRAN NACELLES Joint-stock company related: simplified. ©) Extension request (s): © Agent (s): CABINET GERMAIN & MAUREAU.
    NACELLE FOR AN AIRCRAFT TURBOREACTOR EQUIPPED WITH A DEVICE FOR DETECTING DEFORMATION OF ITS MOBILE STRUCTURE.
    FR 3,059,646 - A1 The present invention relates to a nacelle for an aircraft turbojet engine, comprising a thrust reverser device, said nacelle comprising:
    - a fixed structure and
    - A mobile structure displaceable in translation along an axis substantially parallel to a longitudinal axis of the nacelle, between a retracted position in which it provides aerodynamic continuity with said fixed structure of the nacelle during operation of the nacelle in direct jet and a deployed position in which it opens a passage intended for the circulation of a deflected secondary air flow during operation of the nacelle in reverse jet.
    The nacelle is remarkable in that it comprises at least one position sensor (67) designed and arranged in the nacelle to detect a deformation of the mobile structure exceeding a predetermined authorized deformation threshold.
    ι
    The present invention relates to a nacelle for an aircraft turbojet engine comprising means for detecting the breakage of a thrust reverser actuator.
    An aircraft is powered by several turbojets each housed in a nacelle. The propulsion unit constituted by a turbojet engine and the nacelle which receives it is shown in FIG. 1.
    The propulsion unit 1 comprises a nacelle 3 supporting a turbojet engine 5. The propulsion unit 1 is connected to the aircraft fuselage (not visible) for example by means of a pylon 7 intended to be suspended under a wing of the aircraft.
    The nacelle 3 generally has a tubular structure comprising an upstream section 9 defining an air inlet upstream of the turbojet engine 5, a middle section 11 intended to surround a fan of the turbojet engine, a downstream section 13 comprising an external cover 15 which can house a device thrust reverser and intended to surround the combustion chamber of the turbojet, and is generally terminated by an ejection nozzle whose outlet is located downstream of the turbojet.
    This nacelle houses the turbojet engine 5 which can be of the double flow type, capable of generating via the blades of the rotating fan a flow of hot air (also called primary flow), coming from the combustion chamber of the turbojet engine, and a cold air flow (secondary flow) which circulates outside the turbojet engine through a vein, also called annular channel, formed between a fairing of the turbojet engine and an internal wall of the external cowling 15 of the nacelle. The two air flows are ejected from the turbojet engine from the rear of the nacelle.
    The thrust reversal device is, when the aircraft lands, intended to improve the braking capacity of the latter by redirecting forward at least part of the thrust generated by the turbojet engine.
    In this phase, the thrust reversal 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 flow vary depending on whether the thrust reverser device is of the door type or is of the grate type.
    However, in all cases, the external cowling 15 comprises a movable structure which can be moved between, on the one hand, a deployed position in which it opens in the nacelle a passage intended for the diverted flow, and on the other hand, a position of retraction in which it closes this passage.
    Regarding thrust reversing devices with deflection grids, two types of thrust reversing devices with deflection grids are known from the prior art.
    A first thrust reverser device with deflection grids is of the “fixed grate” type, device shown in FIGS. 2 and 3 to which reference is now made.
    Figures 2 and 3 are views in longitudinal section of the nacelle, centered on the middle and downstream sections of the nacelle, the nacelle being illustrated respectively in direct jet operation (Figure 2) and in reverse jet operation (Figure 3).
    The mobile structure of the nacelle comprises two substantially semi-cylindrical half-covers (forming the external cover 15 visible in FIG. 1).
    Each half-cover is movable in translation along upper guide rails (conventionally called “12-hour rails” because of their positions at the top of the nacelle) fixed in the nacelle and registering on either side of the pylon 7 (or mast) visible in Figure 1, and along a lower guide rail (conventionally called "6 o'clock rail" because of its position in the lower part of the nacelle) also fixed in the nacelle.
    The two semi-cylindrical half-covers form an inverter cover 17. The inverter cover is substantially annular. In the retracted position, corresponding to direct jet operation of the nacelle, the reverser cover 17 provides external aerodynamic continuity with a fixed structure of the nacelle and covers annular deflection grids 19 associated with reversing flaps 21.
    In known manner, the deflection grids 19 are attached to a fan casing 23 of the turbojet engine, using a fixed front frame 27.
    The reversing flaps 21 form, for their part, blocking doors which can be activated by the sliding of the cover causing a closure of the vein V downstream of the grids, as illustrated in FIG. 3, so as to optimize the reorientation of the cold air flow F.
    When the reverser cover 17 moves downstream of the nacelle until it reaches a deployed position corresponding to an operation of the nacelle in reverse jet in which it discovers the deflection grids 19, it creates a passage in the nacelle intended for the circulation of a diverted secondary air flow.
    The reorientation of the air flow is carried out thanks to the deflection grids associated with the reversing flaps 21, the cover 17 having a simple sliding function aimed at discovering or covering these deflection grids.
    A second thrust reversing device with deflection grids is of the “translating grate” type, device represented in FIGS. 4 and 5 to which reference is now made.
    Figures 4 and 5 are views in longitudinal section of the nacelle, centered on the middle and downstream sections of the nacelle, the nacelle being illustrated respectively in direct jet operation and in reverse jet operation.
    As illustrated in FIG. 4, deflection grids 29 are enclosed in direct jet operation in an envelope defined by the annular space E formed by a fan cover 25 and the fan casing 23 of the turbojet engine.
    The deflection grids 29 are supported in a known manner at their upstream end by a movable front frame 31 and at their downstream end by a movable rear frame 33, integral with an upstream edge 35 of an inverter cover 37.
    As for the thrust reversing device with fixed grids illustrated in FIGS. 2 and 3, the reverser cover 37 is substantially annular and is formed by two semi-cylindrical half-covers. The two semi-cylindrical half-covers form the external cover 15 visible in FIG. 1. Each half-cover is movable in translation along upper rails (“12-hour rails”) fixed in the nacelle and registering on both sides. other from the pylon, and along a lower rail ("6-hour rail") fixed in the nacelle. However, the mobile structure of the nacelle here comprises the reverser cover 37 and the translating deflection grids 29 which are integral with the reverser cover 37.
    In the retracted position, corresponding to a direct jet operation of the nacelle (FIG. 4), the reverser cover 37 of the mobile structure ensures aerodynamic continuity with the fixed structure of the nacelle.
    Reversal flaps 39 are also integral with the rear frame 33 of the deflection grids 29. In direct jet operation of the nacelle, such as that shown in FIG. 4, the flaps are in a so-called closed position.
    According to this type of thrust reversing device with translating grids, the deflection grids 29 are movable and translate with the reverser cover 37 during the thrust reversal phases.
    FIG. 5 illustrates the nacelle in the reverse jet position. In such a position, the deflection grids 29 and the reverser cover 37 are moved back downstream of the nacelle. When the mobile structure moves downstream of the nacelle until it reaches a deployed position corresponding to an operation of the nacelle in reverse jet, the mobile structure creates a passage in the nacelle intended for the circulation of a flow of secondary air deflected.
    The deflection grids 29 are downstream of the envelope formed by the fan cover 25 and the fan casing 23, thus becoming functional to allow at least part of the air flow F passing through the vein V to escape of the nacelle and to be redirected upstream of the nacelle.
    In reverse jet operation of the nacelle, such as that shown in FIG. 5, the thrust reversal flaps 39 have pivoted relative to the direct jet operation of the nacelle. These flaps are then in a so-called open position and at least partially obstruct the flow stream V of the air flow F. They contribute to the redirection of at least part of the air flow F through the deflection grids 29 .
    Whatever the type of thrust reversing device with grids (fixed or translating) selected, the displacement of the mobile structure, structure comprising the reverser cover alone when the thrust reversing device is of the type with fixed grids or comprising the reverser cover and the translating grids when the thrust reversing device is of the type with translating grids, is obtained by activating an actuation system comprising a set of hydraulic, pneumatic or electric. These actuators are distributed over the circumference of the nacelle and typically have a first end secured to the fixed structure of the nacelle and a second end secured to the movable structure of the nacelle. A known configuration consists of two actuators arranged in an upper zone located near the upper rails ("12 hour rail") and two actuators arranged in a lower zone located near the lower rail ("6 hour rail").
    The actuators of the reverser cover are subjected to significant stresses during each actuation occurring during the activation of the thrust reversing device.
    These constraints can, potentially, cause several damage to these actuators such as, in particular, a rupture of the tube of one or more of the actuators of the inverter cover, a loss of connection between one or more of these actuators and the mobile structure of the nacelle, a break in the pinion of one or more of these actuators, breakage which can cause a partial loss of the force path between the fixed and mobile structures.
    When one or more of these failures occur on one of the actuators of the thrust reversing device, the thrust reversing device remains operational, however, because the forces are taken up by the actuators which are healthy.
    However, the resumption of the forces by the actuators which are healthy eventually leads to a deformation of the mobile structure, deformation which is only detectable during a thorough control of the nacelle. Thus, the aircraft can continue to fly as long as no in-depth control of the nacelle is carried out.
    However, the mobile structure of the nacelle can be deformed more during special events such as a forced landing for example, due to the poor distribution of forces at the level of the actuators.
    In order to avoid such deformation, the mobile structure of the nacelle is today oversized from a fatigue point of view, this in order to allow it to take up the forces generated by the loss of an actuator of the reversing device of thrust, while avoiding its deformation especially during particular events.
    This fatigue oversizing of the mobile structure of the nacelle has the disadvantage that the reverser cover has a high mass.
    The present invention aims to solve the drawbacks encountered in the thrust reversing devices with fixed and translating grids of the prior art, by proposing a device capable of detecting a deformation of the mobile structure which is not detectable in the art anterior than during a thorough inspection of the nacelle.
    To do this, the present invention relates to a nacelle for an aircraft turbojet engine, comprising a thrust reversal device, said nacelle comprising:
    a fixed structure, and a mobile structure, displaceable in translation along an axis substantially parallel to a longitudinal axis of the nacelle, between a retracted position in which it provides aerodynamic continuity with said fixed structure of the nacelle during a operation of the nacelle in direct jet and a deployed position in which it opens a passage intended for the circulation of a deflected secondary air flow during operation of the nacelle in reverse jet, said nacelle being remarkable in that it comprises at least one position sensor, designed and arranged in the nacelle for detecting a deformation of the mobile structure exceeding a predetermined authorized deformation threshold.
    Thus, by planning to equip the nacelle with sensors designed and arranged in the nacelle to detect a deformation of the mobile structure exceeding a predetermined deformation threshold authorized, it is now possible to detect any event outside the dimensioning framework in fatigue fatigue the structure.
    If a deformation of the mobile structure is detected, a maintenance operation aimed at inspecting and potentially restoring the actuators of the thrust reverser device and the mobile structure can be provided.
    Alternatively, the pilot can choose to limit the application of the maximum counter-thrust during a thrust reversal phase (for example by reducing the engine speed) following the detection of the deformation of the structure (taking into account the fact that the pilot is aware of this deformation of the structure, which is not the case in the prior art).
    Thus, thanks to the detection of a deformation of the structure, it is now possible to act on the mobile structure or on the application of the load applicable during a thrust reversal operation upstream of a irreversible deformation of the structure.
    It is therefore no longer necessary, unlike the prior art, to oversize the mobile structure from a fatigue point of view.
    By succeeding in this way in reducing the fatigue dimensioning of the mobile structure, the mass of the mobile structure is reduced considerably compared to the prior art.
    According to all optional features of the invention: the position sensor comprises:
    • a detector, integral with the fixed structure of the nacelle, and • a target, integral with the movable structure of the nacelle, the position sensor being further designed to send a signal to an external device when the target is substantially in opposite the detector;
    the position sensor is a proximity sensor whose detector is secured to the fixed structure of the nacelle and whose target is secured to the mobile structure of the nacelle and is adapted to change the state of a magnetic field emitted by the detector when said target is substantially opposite said detector; this sensor is capable of detecting the position of the mobile structure without physical contact, which makes it possible not to wear the structure in an area of high potential friction and high speeds of movement of the mobile structure;
    alternatively, the position sensor is an optical sensor, the detector of which is secured to the fixed structure of the nacelle and emits a light flux and the target of which is secured to the mobile structure of the nacelle and includes means for reflecting said light flux; as for the proximity sensor, this sensor is capable of detecting the position of the mobile structure without physical contact, which makes it possible not to wear the structure in an area of high potential friction and high speeds of movement of the mobile structure;
    according to another alternative, the position sensor is an electromechanical sensor whose detector is secured to the fixed structure of the nacelle and comprises a contact lever and whose target is secured to the mobile structure of the nacelle and is designed to actuate said contact lever when said target is substantially opposite said detector;
    in the nacelle according to the invention:
    • the fixed structure includes:
    • an upper guide system of said mobile structure, positioned near a pylon intended to connect said nacelle to an aircraft wing, and • a lower guide system of said mobile structure, substantially diametrically opposite to said upper guide system , and • the mobile structure includes:
    • a set of deflection grids, contained in an envelope defined by a fan cover and by a fan casing of a turbojet engine during operation of the nacelle in direct jet, • an inverter cover, integral with said set deflection grids, • a slide, designed to allow the movement of said movable structure along the lower guide system, said nacelle being remarkable in that the position sensor detector is mounted on at least one of said guide systems, and in that the target is mounted on said slide;
    the fixed structure further comprises a deflection edge, ensuring an aerodynamic line with a downstream part of a fan casing of a turbojet engine, and the detector of said position sensor is mounted near said deflection edge;
    As a variant, in the nacelle of the invention:
    • the fixed structure includes:
    • an upper guide system of said mobile structure, positioned near a pylon intended to connect said nacelle to an aircraft wing, and • a lower guide system of said mobile structure, substantially diametrically opposite to said upper guide system , and • the mobile structure comprises an inverter cover, displaceable in translation along an axis substantially parallel to a longitudinal axis of the nacelle, between a retracted position in which it provides aerodynamic continuity with said fixed structure of the nacelle during operation of the nacelle in direct jet and a deployed position in which it opens a passage intended for the circulation of a deflected secondary air flow during operation of the nacelle in reverse jet, said nacelle being remarkable in that the position sensor detector is mounted on at least one of said guidance systems, and in that the target is mounted on said inverter cover, near an upstream edge of said inverter cover;
    the upper guide system comprises two guide rails profiled along the pylon and in which the lower guide system comprises a single guide rail, said nacelle being characterized in that it comprises a detector on each rail of the upper guide system and a detector on the rail of the lower guide system.
    According to another variant of the invention in which:
    • the fixed structure includes:
    • an upper guide system of said mobile structure, positioned near a pylon intended to connect said nacelle to an aircraft wing, and • a lower guide system of said mobile structure, substantially diametrically opposite to said upper guide system , and • the mobile structure includes:
    • a set of deflection grids, contained in an envelope defined by a fan cover and by a fan casing of a turbojet engine during operation of the nacelle in direct jet, • an inverter cover, integral with said set deflection grids, the nacelle further comprising a plurality of actuators designed to move said movable structure during their activation, the nacelle is remarkable in that the position sensor is a linear position sensor of the “LVDT” or magnetostrictive type , positioned near at least one of said actuators; Advantageously, a linear position sensor is positioned close to each of said actuators;
    According to a variant common to all of the embodiments, the nacelle of the invention comprises at least one end-of-travel stop mounted on at least one system for guiding the mobile structure.
    Other characteristics and advantages of the invention will appear on reading the following detailed description for the understanding of which reference will be made to the appended drawings in which:
    FIG. 1 represents a propulsion unit of the prior art; Figures 2 and 3 are views in longitudinal section of a nacelle of the prior art provided with a thrust reversing device with fixed grids, respectively illustrated in direct jet and reverse jet operation;
    Figures 4 and 5 are views in longitudinal section of a nacelle of the prior art provided with a thrust reversing device with translating grids, respectively illustrated in direct jet and reverse jet operation;
    FIG. 6 illustrates a propulsion unit according to the invention, the nacelle of which is provided with a thrust reversing device with translating grids;
    Figure 7 is an enlarged view of area A of Figure 6, the nacelle being obtained according to a first embodiment of the invention;
    ίο Figure 8 is an enlarged view of area A of Figure 6, the nacelle being obtained according to a second embodiment of the invention;
    Figure 9 is an enlarged view of area A of Figure 6, the nacelle being obtained according to a third embodiment of the invention;
    Figures 10 and 11 show the nacelle of the invention obtained according to a fourth embodiment, respectively illustrated in direct jet and reverse jet operation;
    Figures 12 and 13 show a nacelle obtained according to the invention, provided with a thrust reversing device with fixed grids, respectively illustrated in direct jet and reverse jet operation;
    FIG. 14 is an enlargement of zone XIV of FIG. 13.
    In all of the figures, identical or analogous references represent identical or analogous organs or sets of organs.
    Note that in the description and in the claims, the terms “upstream” and “downstream” must be understood with respect to the circulation of the air flow inside the propulsion assembly formed by the nacelle and the turbojet , that is to say from left to right with reference to all of the figures.
    Referring to Figure 6 in which there is shown a propulsion unit according to the invention, the nacelle 41 is provided with a thrust reversing device with translating grids illustrated in reverse jet operation.
    In accordance with the nacelle presented in FIGS. 4 and 5 of the prior art, the nacelle 41 of the invention comprises a fixed structure 43 and a mobile structure 45.
    As regards the fixed structure 43, this structure is fixed relative to the rest of the nacelle 41. The fixed structure comprises a fan cover 25 defining, with the fan casing 23 of the turbojet engine, an annular space E forming an envelope 47.
    Regarding the movable structure 45, this structure is movable relative to the fixed structure 43 of the nacelle. The mobile structure of the nacelle comprises a set of deflection grids 49 and an inverter cover 51. An upstream edge of the inverter cover is integral with a rear frame of the set of grids. Thus, a displacement of the reverser cover in the nacelle causes the displacement of the deflection grids in the nacelle in concert.
    When the nacelle is in direct jet operating mode (operating mode not shown in FIG. 6), the deflection grilles 49 are contained in the casing 47 defined by the fan cowl and by the fan casing belonging to the turbojet engine. The inverter cover 51 and the deflection grilles 49 are in a so-called retracted position, in which the inverter cover 51 provides aerodynamic continuity with the fan cover 25 of the fixed structure 43 of the nacelle.
    When the nacelle is in reverse jet operating mode (operation shown in FIG. 6), the mobile structure 45 has been translated along an axis 53 substantially parallel to a longitudinal axis of the nacelle. The reverser cover 51 and the deflection grids 49 are in a so-called deployed position, in which a passage in the nacelle is open. The deflection grids 49 are downstream of the casing 47 defined by the fan cover 25 and the fan casing 23. The deflection grids 49 thus become functional to allow part of an air flow passing through the vein to escape from the nacelle and to be redirected upstream from the nacelle.
    The movement of the mobile structure is ensured according to a set of guide systems.
    The set of guide systems comprises for this purpose an upper guide system 55, positioned near a pylon intended to connect the nacelle to an aircraft wing and a lower guide system 57, substantially diametrically opposite to the system of upper guide.
    The upper guide system 55 and the lower guide system 57 are both fixed in the nacelle and thus belong to the fixed structure 43 of the nacelle.
    The upper guide system 55 has two guide rails (“12-hour rails” because of their position at the top of the nacelle). These guide rails are for example profiled along the pylon, on either side of the pylon. These rails can also alternatively be arranged on an intermediate element integral with the pylon when the propulsion unit is mounted.
    The lower guide system 57 comprises a single guide rail 59 (better visible in FIGS. 7 to 9), also called "6-hour rail" because of its position in the lower part of the nacelle.
    The mobile structure 45 of the nacelle further comprises a slide 61 (better visible in FIGS. 7 to 9) secured to a movable front frame 63 (better visible in FIGS. 7 to 9) supporting an upstream end of the deflection grilles 49. The slide 61 is designed to allow movement of the movable structure 45 along the lower guide system 57.
    In known manner, the displacement of the mobile structure between its retracted position and its deployed position is obtained by activating a plurality of actuators 65 which may be of hydraulic, pneumatic or electrical nature.
    These actuators 65 are distributed over the circumference of the nacelle (only two actuators are visible in FIG. 6, but it should be understood that two other actuators are positioned on the circumference of the nacelle, symmetrically with the two actuators shown).
    More specifically, two actuators 65 are arranged in an upper region of the nacelle, located near the upper guide system 55 and two actuators 65 are arranged in a lower region of the nacelle, located near the lower guide system 57.
    According to the invention, the nacelle comprises one or more position sensors designed and arranged in the nacelle to detect a deformation of the mobile structure exceeding a predetermined deformation threshold authorized.
    Unlike certain position sensors used in the nacelles of the prior art to track the movement of the actuators of the thrust reverser device, it is envisaged in the context of the present invention to design a position sensor not for measuring the displacement of the actuators but to detect a deformation of the mobile structure exceeding a predetermined authorized deformation threshold.
    The position sensor of the invention comprises a detector, integral with the fixed structure of the nacelle, and a target, integral with the mobile structure of the nacelle, the position sensor being designed to send a signal to an external device when the target is located substantially opposite the detector.
    According to a first embodiment of the invention, illustrated in FIG. 7 obtained by enlarging the zone A of FIG. 6, a position sensor used in the context of the present invention is a proximity sensor 67.
    The proximity sensor 67 includes a detector 69 secured to the fixed structure of the nacelle and includes a target 71 secured to the mobile structure of the nacelle.
    The detector 69 of the proximity sensor 67 is mounted on the guide rail 59 of the lower guide system 57. Preferably but not limited to, the detector is mounted near a deflection edge 73, fixed relative to the nacelle , ensuring an aerodynamic line with a downstream part of the fan casing 23 of the turbojet engine.
    The target 71 is preferably mounted on the slider 61.
    The operation of the proximity sensor is known to those skilled in the art. The detector 69 emits a magnetic field, and the target 71 is adapted to change the state of this magnetic field when it is substantially opposite the detector 69.
    According to a second embodiment of the invention, illustrated in FIG. 8 obtained by enlarging the zone A of FIG. 6, a position sensor used in the context of the present invention is an optical sensor 75.
    The optical sensor 75 comprises a detector 77 secured to the fixed structure of the nacelle and comprises a target 79 secured to the mobile structure of the nacelle.
    As for the detector 69 of the proximity sensor 67, the detector 77 of the optical sensor 75 is mounted on the guide rail 59 of the lower guide system 57. Preferably but not limited to, the detector is mounted near the deflection edge 73. The target 79 is also preferably mounted on the slide 61.
    The operation of the optical sensor is known to those skilled in the art. The detector 77 emits a light flux, for example by means of a set of diodes or lasers, and the target 79 comprises a means for reflecting the light flux, such as a mirror, adapted to reflect the emitted light flux by the detector when the target 79 is substantially vis-à-vis the detector 77.
    According to a third embodiment of the invention, illustrated in FIG. 9 obtained by enlarging the zone A of FIG. 6, a position sensor used in the context of the present invention is an electromechanical sensor 81.
    The electromechanical sensor comprises a detector 83 secured to the fixed structure of the nacelle and comprises a target 85 secured to the mobile structure of the nacelle.
    As for the proximity sensor 67 and for the optical sensor 75, the detector 83 of the electromechanical sensor 81 is mounted on the guide rail 59 of the lower guide system 57. Preferably but not limited to, the detector is mounted near the deflection edge 73. The target 85 is preferably mounted on the slide 61.
    The detector 83 of the electromechanical sensor 81 comprises a contact lever 87, which can be actuated by the target when the target 85 is substantially opposite the detector 83.
    According to a fourth embodiment represented in FIGS. 10 and 11 in which the nacelle of FIGS. 6 to 9 is represented, respectively according to a mode of operation in direct jet and in reverse jet, the fan cover having been obscured for better understanding , a position sensor used in the context of the present invention can be a linear position sensor 89 of the “LVDT” type (English acronym for “Linear Variable Differential Transformer”) known to those skilled in the art, or a magnetostrictive sensor or equivalent.
    According to the invention, the linear position sensor 89 “LVDT” is positioned close to at least one of the actuators 65, which makes it possible to detect any event on the actuators or on the mobile structure.
    The linear position sensor 89 comprises a fixed body 91 mounted on a fitting 93 fixed to the fan casing 23, fitting to which is attached a fixed body 95 of the actuator 65, and a movable body 97, telescopic relative to said body fixed 91, attached to the mobile structure of the nacelle, for example to the inverter cover 51 of the mobile structure.
    Advantageously, the linear position sensor 89 “LVDT” is positioned close to each actuator of the thrust reversing device, this in order to finely detect the events occurring on the actuators or on the areas of the mobile structure near the actuators.
    According to a variant shown in Figures 12 to 14, the nacelle can be provided with a thrust reverser device with fixed grids.
    Reference is made to FIG. 12 in which a propulsion unit according to the invention has been shown, the nacelle 101 of which is provided with a thrust reversing device with fixed grids, illustrated in direct jet operation.
    In accordance with the nacelle presented in FIGS. 2 and 3 of the prior art, the nacelle 101 of the invention comprises a fixed structure 103 and a mobile structure 105.
    Regarding the fixed structure 103, this structure is fixed relative to the rest of the nacelle 101. The fixed structure comprises a fan cover (not visible here).
    Regarding the movable structure 105, this structure is movable relative to the fixed structure 103 of the nacelle. The mobile structure of the nacelle includes an inverter cover 107.
    When the nacelle is in direct jet operating mode (operating mode represented in FIG. 12), the reverser cover 107 (whose representation is in cutaway view in FIGS. 12 and 13) is in the retracted position in which it provides a aerodynamic continuity with the fan cover and covers deflection grilles (not shown here for clarity of the figure). The deflection grids are attached to the fan casing (not shown) of the turbojet engine and to a fan cover (not shown), using a fixed front frame 111.
    When the nacelle is in reverse jet operating mode (shown in FIG. 13), the reverser cover 107 has been translated along the axis 53 (visible in FIG. 6) substantially parallel to a longitudinal axis of the carrycot. The reverser cover 107 is in a deployment position in which a passage in the nacelle is open. The deflection grids are then discovered and thus become functional to allow part of an air flow passing through the vein to escape from the nacelle and to be redirected upstream of the nacelle.
    The movement of the mobile structure is ensured by the set of upper and lower guide systems conforming to the upper 55 and lower 57 guide systems discussed with reference to FIGS. 6 to 9 when the nacelle is equipped with a reversing device for thrust with translating grids and belonging to the fixed structure 103 of the nacelle.
    According to the invention, the nacelle comprises one or more position sensors 113 designed and arranged in the nacelle to detect a deformation of the mobile structure exceeding a predetermined authorized deformation threshold.
    As illustrated in FIG. 12, the position sensor 113 comprises a detector 115, integral with the fixed structure of the nacelle, and a target 117, integral with the reverser cover 107.
    The detector 115 is preferably mounted on the upper guide rail. The target 117 is preferably mounted directly on the inverter cover 107.
    The position sensor is designed to send a signal to an external device when the target 117 is substantially opposite the detector 115, as shown in Figures 13 and 14 illustrating the nacelle in reverse jet operating mode.
    The sensors used when the nacelle is equipped with a thrust reversing device with fixed grids are also proximity sensors, optical sensors or electromechanical sensors in accordance with those discussed with reference to FIGS. 6 to 9.
    According to a variant common to all of the embodiments described with reference to FIGS. 6 to 14, one or more end-of-travel stops can be fitted to one or more guide rails of all of the guiding systems in translation of the structure mobile, this in order to limit the travel of the mobile structure, thus limiting the associated constraints.
    It goes without saying that the present invention is not limited to the 5 embodiments of this nacelle, described above only by way of illustrative examples, but on the contrary embraces all the variants involving the technical equivalents of the means described as well as their combinations if these fall within the scope of the invention.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Nacelle (41, 101) for an aircraft turbojet engine, comprising a thrust reversal device, said nacelle comprising:
    a fixed structure (43, 103), and a mobile structure (45, 105) displaceable in translation along an axis (53) substantially parallel to a longitudinal axis of the nacelle, between a retracted position in which it provides aerodynamic continuity with said fixed structure (43, 103) of the nacelle during operation of the nacelle in direct jet and a deployed position in which it opens a passage intended for the circulation of a flow of secondary air deflected during operation of the nacelle in reverse jet, said nacelle (41,101) being characterized in that it comprises at least one position sensor (67, 75, 81, 89, 113), designed and arranged in the nacelle to detect a deformation of the mobile structure (45, 105) exceeding a predetermined authorized deformation threshold.
    [2" id="c-fr-0002]
    2. Nacelle (41, 101) according to claim 1, characterized in that the position sensor (67, 75, 81, 113) comprises:
    a detector (69, 77, 83, 115) integral with the fixed structure (43, 103) of the nacelle, and a target (71, 79, 85, 117), integral with the mobile structure (45, 105) of the nacelle, the position sensor (67, 75, 81,113) being furthermore designed to send a signal to an external device when the target (71, 79, 85,117) is substantially opposite the detector (69, 77, 83 , 115).
    [3" id="c-fr-0003]
    3. Nacelle (41, 101) according to claim 2, characterized in that the position sensor is a proximity sensor (67) whose detector (69) is integral with the fixed structure (43,103) of the nacelle and whose target (71) is integral with the mobile structure (45, 105) of the nacelle and is adapted to change the state of a magnetic field emitted by the detector when said target is substantially opposite said detector.
    [4" id="c-fr-0004]
    4. Nacelle (41, 101) according to claim 2, characterized in that the position sensor is an optical sensor (75) whose detector (77) is integral with the fixed structure (43, 103) of the nacelle and emits a light flux and the target (79) of which is integral with the mobile structure (45, 105) of the nacelle and comprises a means for reflecting said light flux.
    [5" id="c-fr-0005]
    5. Nacelle (41, 101) according to claim 2, characterized in that the position sensor is an electromechanical sensor (81) whose detector (83) is integral with the fixed structure (43, 103) of the nacelle and comprises a contact lever (87) and whose target (85) is integral with the mobile structure (45, 105) of the nacelle and is designed to actuate said contact lever (87) when said target is substantially opposite -vis of said detector.
    [6" id="c-fr-0006]
    6. Nacelle (41) according to any one of claims 2 to 5, in which:
    the fixed structure (43) comprises:
    • an upper guide system (55) of said mobile structure, positioned near a pylon intended to connect said nacelle to an aircraft wing, and • a lower guide system (57) of said mobile structure, substantially diametrically opposite to said upper guide system, and the mobile structure (45) comprises:
    • a set of deflection grids (49), contained in an envelope (47) defined by a fan cover (25) and by a fan casing (23) of a turbojet engine during operation of the jet nacelle direct, • an inverter cover (51), integral with said set of deflection grids (49), • a slide (61), designed to allow the movement of said mobile structure (45) along the lower guide system ( 57), said nacelle being characterized in that the detector (69, 77, 83) of the position sensor (67, 75, 81) is mounted on at least one of said guidance systems, and in that the target is mounted on said slide (61).
    [7" id="c-fr-0007]
    7. Nacelle (41) according to claim 6, in which the fixed structure (43) further comprises a deflection edge (73), ensuring an aerodynamic line with a downstream part of a fan casing of a turbojet, characterized in that the detector (69, 77, 83) of the position sensor (67, 75, 81) is mounted near said deflection edge (73).
    [8" id="c-fr-0008]
    8. Nacelle (101) according to any one of claims 2 to 5, in which:
    the fixed structure (103) comprises:
    • an upper guide system (55) of said mobile structure, positioned near a pylon intended to connect said nacelle to an aircraft wing, and • a lower guide system (57) of said mobile structure, substantially diametrically opposite to said upper guide system, and the mobile structure (105) comprises a reverser cover (107), movable in translation along an axis (53) substantially parallel to a longitudinal axis of the nacelle, between a retracted position in which it provides aerodynamic continuity with said fixed structure (103) of the nacelle during operation of the nacelle in direct jet and a deployed position in which it opens a passage intended for the circulation of a secondary air flow deflected during operation of the nacelle in reverse jet, said nacelle being characterized in that the detector (115) of the position sensor (113) is mounted on at least one of said system e guide, and in that the target (117) is mounted on said inverter cover, near an upstream edge of said inverter cover.
    [9" id="c-fr-0009]
    9. Nacelle (41,101) according to any one of claims 6 to 8, in which the upper guide system (55) comprises two guide rails profiled along the pylon and in which the lower guide system (57) comprises a single guide rail (59), said nacelle being characterized in that it comprises a detector on each rail of the upper guide system and a detector on the rail of the lower guide system.
    [10" id="c-fr-0010]
    10. Nacelle (41) according to claim 1, in which:
    the fixed structure (43) comprises:
    • an upper guide system (55) of said mobile structure, positioned near a pylon intended to connect said nacelle to an aircraft wing, and • a lower guide system (57) of said mobile structure, substantially diametrically opposite to said upper guide system, and the mobile structure (45) comprises:
    • a set of deflection grids (49), contained in an envelope (47) defined by a fan cover (25) and by a fan casing (23) of a turbojet engine during operation of the jet nacelle direct, • an inverter cover (51), integral with said set of deflection grids (49), said nacelle further comprising a plurality of actuators designed to move said mobile structure (45) during their activation and being characterized in that the position sensor is a linear position sensor (89) of the “LVDT” type, positioned near at least one of said actuators (45).
    [11" id="c-fr-0011]
    11. Nacelle (41) according to claim 10, characterized in that it comprises a linear position sensor (89) positioned close to each of said actuators (45).
    [12" id="c-fr-0012]
    12. Nacelle (41, 101) according to any one of claims 6 to 11, characterized in that it comprises at least one end-of-travel stop mounted on at least one guide system (55, 57) of the structure mobile.
    1/5
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    同族专利:
    公开号 | 公开日
    FR3059646B1|2019-05-17|
    US20200031485A1|2020-01-30|
    EP3551870A1|2019-10-16|
    WO2018104632A1|2018-06-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20020157377A1|2001-04-30|2002-10-31|Terry Ahrendt|System and method for controlling the stowage of jet engine thrust reversers|
    EP1972548A2|2007-03-20|2008-09-24|Goodrich Actuation Systems Ltd.|Actuator arrangement|
    GB2510635A|2013-02-12|2014-08-13|Ge Aviat Systems Ltd|Predicting faults in an aircraft thrust reverser system|
    FR3019229A1|2014-03-31|2015-10-02|Aircelle Sa|THRUST INVERTER OF A TURBOJET NACELLE COMPRISING MOBILE HOOD CONTROL JIGS AND A VARIABLE SECONDARY TUBE|FR3098862A1|2019-07-15|2021-01-22|Airbus Operations|DOUBLE-FLOW TURBOREACTOR CONTAINING A SERIES OF ROTATING BLADES FOR CLOSING THE SECONDARY FLOW VEIN|
    WO2021023947A1|2019-08-07|2021-02-11|Safran Nacelles|Position sensor for aircraft nacelle thrust reverser door|
    EP3868667A1|2020-02-24|2021-08-25|Airbus Operations|Aircraft nacelle comprising a fan blower with articulated flaps|
    法律状态:
    2017-11-23| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-08| PLSC| Publication of the preliminary search report|Effective date: 20180608 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-11-17| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1662073|2016-12-07|
    FR1662073A|FR3059646B1|2016-12-07|2016-12-07|NACELLE FOR AIRCRAFT TURBOREACTOR EQUIPPED WITH A DEVICE FOR DETECTING DEFORMATION OF ITS MOBILE STRUCTURE|FR1662073A| FR3059646B1|2016-12-07|2016-12-07|NACELLE FOR AIRCRAFT TURBOREACTOR EQUIPPED WITH A DEVICE FOR DETECTING DEFORMATION OF ITS MOBILE STRUCTURE|
    US16/467,718| US20200031485A1|2016-12-07|2017-12-01|Nacelle for an aircraft turbojet engine provided with a device for detecting deformation of its movable structure|
    PCT/FR2017/053352| WO2018104632A1|2016-12-07|2017-12-01|Nacelle for an aircraft turbojet engine provided with a device for detecting deformation of its movable structure|
    EP17816965.2A| EP3551870A1|2016-12-07|2017-12-01|Nacelle for an aircraft turbojet engine provided with a device for detecting deformation of its movable structure|
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