• 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 essentially to a nacelle for a turbojet engine intended to surround a removable blade blower (340) of the turbojet engine, the nacelle comprising an air inlet section (310) intended to be arranged upstream of the fan, an inner wall (311) of the air inlet section (310) of the nacelle having at least one recess (312) and a movable panel (313) associated with the recess (312), the movable panel (313) can be placed in two positions: - a closed position in which the movable panel (313) covers the recess (312); and - an open position in which the movable panel (313) discovers the recess (312); the recess (312) having dimensions so that, when the movable panel (313) is in the open position, at least one blade (340) of the blower can be deposited, the blade (340) having a head (342); ) fed to the interior of the recess (312) while the blade (340) is disengaged.
    公开号:FR3044053A1
    申请号:FR1561356
    申请日:2015-11-25
    公开日:2017-05-26
    发明作者:Christian Sylvain Vessot；Laurent Soulat
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    NACELLE FOR A TURBOJET ENGINE
    TECHNICAL FIELD OF THE INVENTION
    The technical field of the invention is that of aeronautics, and more particularly that of nacelles of turbojet engines intended to equip aircraft.
    BACKGROUND OF THE INVENTION
    An aircraft turbojet is generally disposed in an outer shell called "nacelle". A partial schematic view in longitudinal section of a conventional example of nacelle is illustrated in FIG. 1. The nacelle of the turbojet engine comprises an upstream air intake section 110, which extends downstream by a section 120 comprising a housing 121 called fan casing and intended to surround a blower of the turbojet engine. The blower comprises a blade which comprises a plurality of vanes 140.
    The role of the air intake section 110 is to capture the air for supplying the turbojet, while ensuring optimal air flow to an inlet plane of the fan. In particular, it is necessary to decelerate the flow of air to the inlet plane of the blower. For example, during cruising, the Mach number thus goes from 0.8 in outdoor conditions to 0.6 at the inlet plane of the fan. To do this, the air intake section 110 has an inner wall 111 of curved shape extending longitudinally to a fan casing 121.
    The blower of the turbojet engine comprises a rotary disc 130 whose periphery comprises a plurality of cavities 131. The blades 140 of the blower each comprise a fastener 141 housed in one of the cavities 131 of the disc 130.
    Document FR 2903154 A1 describes a procedure for removing a fan blade. To deposit a blade 140 of the fan in a conventional manner, a cone 150 located upstream of the disk 130 of the fan is previously disassembled, as shown in Figure 1. Next, a shim disposed in the cell 131 of the disk 130, between a fastener 141 of the blade 140 and the bottom of the cell 131, is removed. The blade 140 is then moved radially by a certain height permitted by the removal of the shim, then the blade 140 is disengaged from the cell 131 by sliding longitudinally upstream the fastener 141 in the cell 131 In this way, the blade 140 is deposited through the air inlet section 110 without coming into contact therewith.
    However, the trend is currently to increase the dilution ratio of the turbofan engines, also called BPR for "By-Pass Ratio" in English. The dilution ratio corresponds to the ratio between the flow rate of the secondary flow and the flow rate of the primary flow of air in the turbojet engine. To increase the dilution ratio, the diameter of the fan, and a fortiori that of the nacelle, is increased, which has disadvantages such as an increase in the mass and drag of the nacelle.
    The design of the nacelle is then revised to reduce the impact of these disadvantages. For this purpose, the length of the air intake section is reduced. This is called a "short" air intake section. A partial schematic view in longitudinal section of an example of a nacelle comprising a short air inlet section is illustrated in FIG.
    Despite a reduced length, it is necessary that the air inlet section 110 retain the same ability to provide optimum airflow to the blower inlet plane. For this, the inner wall 111 of the air inlet section 110 penetrates further under the housing 121 surrounding the fan.
    In this configuration, the inner wall 111 prevents the removal of a blade 140 of the fan. Indeed, the space is insufficient to completely release the fastener 141 of the blade 140 of the cell 131 of the disk 130, the blade 140 coming into contact with the inner wall 111 before it can be completely removed.
    It would then be necessary to disassemble the air inlet section 110 of the nacelle so that the blade 140 can be disengaged longitudinally. However, this solution has the disadvantage of consuming a lot of time due to the presence of numerous devices in the air intake section 110 of the nacelle, for example de-icing systems, but also because of the dimensions and the masses. pieces to deposit. This important time is not compatible with the requirements of airlines wanting a quick and efficient disassembly of the blades of the blower.
    SUMMARY OF THE INVENTION
    The present invention aims to solve the problems that have just been exposed by proposing a nacelle for a turbojet engine for depositing a fan blade of the turbojet engine without the need to dismantle the air intake of the nacelle.
    A first aspect of the invention therefore relates to a nacelle for a turbojet engine intended to surround a blower with removable vanes of the turbojet engine, the nacelle comprising an air inlet section intended to be arranged upstream of the fan, an inner wall of the inlet air section of the nacelle comprising at least one recess and a movable panel associated with the recess, the movable panel being able to be placed in two positions: a closed position in which the movable panel covers the recess; recess; and an open position in which the movable panel discovers the recess; the recess having dimensions so that, when the movable panel is in the open position, at least one blade of the blower can be deposited, the blade of the blower having a head fed to the inside of the recess while the dawn of the blower is clear.
    Thus, thanks to the nacelle according to the first aspect of the invention, it is possible to clear a blade of the fan using the space provided by the recess when the movable panel is in the open position. It is therefore not necessary to disassemble the air intake section to get out the dawn.
    The nacelle according to the first aspect of the invention may also comprise one or more of the following characteristics, considered individually or according to the technically possible combinations.
    Preferably, the recess has a width of between 1 and 1.5 times the width of the head of the blade.
    Alternatively, the dimensions of the recess are provided so that the recess can accommodate at least two blade heads at a time.
    In a first embodiment, the movable panel is removable. Thus the movable panel can be completely disassembled so that it does not interfere with the removal of the blade.
    In a second embodiment, the movable panel is connected to the nacelle by a pivot type mechanical connection, the movable panel pivoting towards the inside of the nacelle to move from the closed position to the open position.
    Advantageously, the nacelle comprises an automatic return system of the movable panel in the closed position. Thus, the transition from the open position to the closed position of the movable panel is facilitated. The automatic return system of the movable panel in the closed position comprises for example a metal spring.
    In a third embodiment, the movable panel is connected to the nacelle by a mechanical slide-type connection, the movable panel translating into the nacelle to move from the closed position to the open position.
    Preferably, the nacelle comprises an acoustic insulation, the movable panel also comprising an acoustic insulation. Thus, the nacelle retains its acoustic properties despite the presence of the movable panel. Indeed, the acoustic insulation makes it possible to reduce the noise nuisance due to the turbojet engine. The higher the acoustically treated nacelle surface, the better the sound insulation efficiency. The acoustic insulation is for example in the form of honeycomb structures in the walls of the nacelle and the movable panel.
    Advantageously, the inner wall of the air inlet section has a plurality of recesses circumferentially distributed about a longitudinal axis of the nacelle, each recess being covered by a movable panel. Thus several blades of the blower can be deposited simultaneously, without the need to rotate the blower to align the blades with a single recess.
    A second aspect of the invention relates to a propulsion unit for an aircraft comprising a nacelle according to the first aspect of the invention and a turbojet engine equipped with a removable blade blower mounted on a disc, each removable blade comprising a clip able to be moved. in a corresponding cell of the disk so as to clear the blade of the disk.
    Preferably, the dimensions of a recess in a longitudinal direction of the nacelle are provided so that during the dismounting of a blade, the head of the blade is at least partly inside the recess during that the attachment of the blade is disengaged from the corresponding cell of the disk.
    BRIEF DESCRIPTION OF THE FIGURES The invention and its various applications will be better understood on reading the description which follows and on examining the figures which accompany it, among which: FIG. 1 is a partial diagrammatic view in longitudinal section of FIG. a first example of a nacelle comprising an air intake section having a conventional configuration according to the prior art; FIG. 2 is a partial schematic view in longitudinal section of a second example of a nacelle comprising a short air intake section according to the prior art; FIGS. 3A and 3B are two partial diagrammatic views in longitudinal section of a first embodiment of a propulsion unit for an aircraft comprising a nacelle according to the invention, the nacelle comprising a movable panel respectively in the closed position and in the open position. ; - Figure 4 is a partial schematic view in longitudinal section of a second embodiment of a propulsion unit comprising a nacelle according to the invention. - Figure 5 is a partial schematic view in longitudinal section of a third embodiment of a propulsion unit comprising a nacelle according to the invention. FIG. 6 is a partial schematic perspective view of an exemplary embodiment of a nacelle according to the invention; - Figure 7 schematically illustrates how the width of the head of a fan blade is measured.
    The figures are presented only as an indication and in no way limit the invention.
    For clarity, identical or similar elements are marked with identical reference characters in all the figures.
    DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION The object of the invention is notably to propose, in the case of a nacelle with short air intake, a device intended to facilitate the removal of a fan blade, without it being necessary to dismantle the basket. Such a device saves time during the procedure of removing a fan blade, and thus meet ever more demanding operational constraints.
    FIG. 3A is a partial schematic view in longitudinal section of a first embodiment of a propulsion unit for an aircraft comprising a nacelle according to the invention and a turbojet engine. The nacelle comprises a front air inlet section 310 and a central section 320 intended to surround a fan of the turbojet engine.
    The air intake section 310 has the particular role of decelerating a flow of air entering the turbojet engine. To this end, the air inlet section 310 has an inner wall 311 having a curved shape, and which for example has a symmetry of revolution about a longitudinal axis X. Therefore, a cross section of this inner wall 311, that is to say orthogonal to the longitudinal axis X of the nacelle, is for example of circular shape.
    The blower of the turbojet engine comprises a disc 330 centered on the axis of rotation of the blower and whose periphery comprises a plurality of cells 331. The blower further comprises a plurality of blades 340 arranged radially on the periphery of the disc, each blade 340 having a blade head 342 and a fastener 341 housed in one of the cavities of the disc 330. A wedge (not shown) is disposed in the cavity 331 of the disc 330, between the fastener 341 of the blade 340 and the disk 330. This wedge is used to radially block the fastener 341 of the blade 340 in the cavity 331 of the disk 330. The fan has a diameter D measured between the heads of two diametrically opposed blades.
    The fan is surrounded by a housing 321 disposed in the central section 320 of the nacelle.
    Furthermore, a cone 350 is disposed upstream of the disc 330 of the blower. The role of this cone 350 is in particular to maintain the blades 340 axially in the disk 330 of the fan.
    The air inlet section 310 has an upstream end edge which extends for example in a plane perpendicular to the axis of rotation of the fan. This air intake plane may nevertheless have a different inclination of 90 ° relative to the axis of rotation of the fan. In addition, the upstream end edge of the air inlet is not necessarily inscribed in a plane. By making an analogy with a clock dial, it is possible to assign one hour to an azimuthal position in the cross section. Generally, the position called "12h" corresponds to the highest point of the nacelle when the latter is mounted on an aircraft, the position called "6h >> corresponding to the lowest point. In the partial schematic views of FIGS. 3A, 3B, 4 and 5, the illustrated part of the propulsion unit is in position at 12 o'clock. The air inlet section 310, in the azimuth position at 12 o'clock, extends longitudinally along a length L to a leading edge of a head 342 of a blade 340 in the same position at 12 o'clock. The invention is particularly interesting when the air inlet section 310 is described as "short", that is to say that in all azimuth positions (12h, 6h, or other), and although the length L is not necessarily the same from one position to another, the air inlet section 310 has a ratio between its length L and the diameter D of the fan less than 0.6.
    The nacelle further comprises a recess 312 formed in the inner wall 311 of the air inlet section 310 and a movable panel 313 can be placed in two positions. The recess has a width at least equal to that of the blade head 342 in the circumferential direction. In a configuration where the recess is intended to accommodate a single blade head 342 at a time, the width of the recess 312 is preferably between 1 and 1.5 times the width of the blade head 342. In this relation, the width W of the recess 312 as for example shown in Figure 6 is considered in a cross section at half the length of the recess.
    In a first position of the movable panel 313, called "closed position", the movable panel 313 covers the recess 312, as illustrated in Figure 3A. When the movable panel 313 is in the closed position, it marries the inner wall 311 of the air inlet section 310 so that the latter does not have a discontinuity that would generate aerodynamic disturbances.
    In a second position of the movable panel 313, called "open position", the movable panel discovers the recess 312 so that access to the recess 312 is cleared. The open position of the movable panel 313 is not necessarily a predetermined position. For example, in the case of a removable panel, this position simply means that the panel is removed to bring the recess 312 into an open state. We can also speak of closed state and open state of the recess rather than closed position and open position respectively of the movable panel. Thus, the recess 312 provides additional space to allow the passage of a blade 340 when desired to disengage the disk 330de the fan. Without this extra space, the blade 340 would contact the inner wall 311 of the air inlet 310 and could not be completely removed.
    The movable panel 313 is for example kept in the closed position by a screw fastening system to prevent the movable panel 313 unexpectedly opens or detaches, at the risk of disrupting the operation of the engine or even to damage it .
    The nacelle generally comprises an acoustic insulation in order to reduce the noise nuisance due to the turbojet engine. Sound insulation is for example in the form of honeycomb structures in the walls of the nacelle. Advantageously, the movable panel 313 also comprises an acoustic insulation. Thus, the surface of the walls of the nacelle comprising acoustic insulation remains maximum and the acoustic performance of the nacelle is not affected by the presence of the movable panel 313.
    As seen in Figure 3B, in a first embodiment, the movable panel 313 is removable and has been removed. Thus the movable panel 313 can be separated from the nacelle to obtain the open position of the recess 312. Once removed, the movable panel 313 certainly does not interfere with the passage of the blade 340, which provides great ease of handling .
    As can be seen in FIG. 4, in a second embodiment, the movable panel 313 is connected to the nacelle by a pivot-type mechanical connection. Thus, unlike the first embodiment, it is not necessary to remove the movable panel 313 to deposit a blade 340.
    To move from the closed position to the open position, the movable panel 313 preferably pivots to the inner compartment of the nacelle. The inner compartment of the nacelle means the volume inside the walls of the nacelle. Thus, the movable panel 313 does not hinder the passage of the blade 340.
    The nacelle advantageously comprises an automatic return system 414 of the movable panel 313 in the closed position. Thus, when the removal of the blade 340 is completed, the movable panel 313 returns to its closed position automatically. The automatic return system 414 is for example a leaf spring having two ends. A first end of the leaf spring is fixed to the movable panel 313. A second end of the leaf spring is for example fixed to the housing 321.
    The movable panel 313 is then held in the open position by means of a wedge 415. The wedge 415 advantageously has a shape and dimensions such that the passage of the blade 340 is not obstructed.
    As can be seen in FIG. 5, in a third embodiment, the nacelle comprises a movable panel 313 connected to the nacelle by a mechanical slide-type connection. Thus, unlike the first embodiment, it is not necessary to remove the movable panel 313 to deposit a blade 340.
    To move from the closed position to the open position, the movable panel 313 advantageously performs a translational movement upstream of the nacelle by penetrating inside a compartment of the nacelle. Thus, the movable panel 313 does not hinder the passage of the blade 340.
    In other embodiments, the nacelle may comprise a plurality of recesses 312 formed in the inner wall 311 of the air inlet section 310, each recess 312 being covered by a movable panel 313. The recesses 312 may be distributed circumferentially around the longitudinal axis X of the nacelle, regularly or irregularly. Thus, for the same position of the fan, several blades 340 are aligned with recesses 312. This avoids rotating the fan for each blade 340 to deposit.
    Advantageously, the distance between two recesses 312 consecutive is equal to a multiple of the distance between two blades 340 consecutive. Thus, when a blade 340 is aligned with a recess 312, each of the other recesses 312 is also aligned with a blade 340. For example for a nacelle having two recesses 312 in two diametrically opposed positions, two diametrically opposite blades 340 may be deposited simultaneously or sequentially without the need to rotate the blower. It is also possible to provide that the width of a recess 312 in the circumferential direction is sufficiently large to allow several consecutive blades 340 to be disengaged without having to rotate the fan. For example, a width intended to accommodate both two or three heads 342 of blades 340 is possible.
    As shown in Figure 6, a recess 312 is formed in the inner wall 311 of the air inlet section 310 of a nacelle according to the invention. The obvious 312 is clear and has a width W measured along a cross section of the inner wall 311, that is to say orthogonal to the longitudinal axis of the nacelle. This width W is not necessarily constant, the recess 312 may take a shape other than the rectangular shape shown in the example of FIG. 6.
    To remove a blade 340 from the blower, for example during a maintenance operation, the cone 350 is disassembled beforehand as shown in FIG. 4. If necessary, the blower is rotated in order to align the blade. blade 340 which is to be deposited with the circumferential position of the recess 312.
    Then, the wedge disposed in the cavity 331 of the disk 330, between the fastener 341 of the blade 340 and the disk 330, is removed. The blade 340 is then moved radially by a certain height so that its fastener 341 can be displaced axially without hindrance in the cell 331, and then the fastener 341 of the blade 340 is disengaged from the cell 331 according to FIG. longitudinal axis X of the nacelle. With the recess 312, the blade 340 does not come into contact with the air inlet section 310 and can be deposited without the need to disassemble the air inlet section.
    Thus, thanks to the nacelle according to the invention, it is no longer necessary to disassemble the air intake section of the nacelle to output a blade of the fan of the turbojet engine. The removal of the dawn is therefore greatly facilitated technically, and the time saved for this operation is substantial.
    Figure 7 schematically illustrates how the width I of the head 342 of a fan blade 340 is measured. The disk 330 of the fan has an axis of rotation A, which generally coincides with the longitudinal axis of the nacelle. The blade 340 has a leading edge 344 and a trailing edge 345. The head 342 of the blade 340 extends between an upstream end 342a joining the leading edge 344, and a downstream end 342b joining the edge leakage 345.
    The width I of the head 342 of the blade 340 is the shortest distance measured between a first straight line D1 parallel to the axis of rotation A of the disk 330 and passing through the upstream end 342a of the head 342 of the blade 340, and a second straight line D2 also parallel to the axis of rotation A of the disc 330 and passing through the downstream end 342b of the head 342 of the blade 340.
    Naturally, the invention is not limited to the embodiments described with reference to the figures and variants could be envisaged without departing from the scope of the invention.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    claims
    1. Nacelle for a turbojet engine for surrounding a removable blower (340) of the turbojet, the nacelle having an air inlet section (310) to be arranged upstream of the fan, the nacelle being characterized in that an inner wall (311) of the air intake section (310) of the nacelle has at least one recess (312) and a movable panel (313) associated with the recess (312), the movable panel (313) can be placed in two positions: - a closed position in which the movable panel (313) covers the recess (312); and - an open position in which the movable panel (313) discovers the recess (312); the recess (312) having dimensions so that, when the movable panel (313) is in the open position, at least one blade (340) of the blower can be deposited, the blade (340) having a head (342); ) fed to the interior of the recess (312) while the blade (340) is disengaged.
    [2" id="c-fr-0002]
    2. The nacelle according to claim 1 wherein the recess (312) has a width (W) between 1 and 1.5 times the width (I) of the head (342) of the blade (340).
    [3" id="c-fr-0003]
    3. The nacelle of claim 1 wherein the dimensions of the recess (312) are provided so that the recess can accommodate at least two heads (342) of blades (340) at a time.
    [4" id="c-fr-0004]
    4. Nacelle according to any one of claims 1 to 3 wherein the movable panel (313) is removable.
    [5" id="c-fr-0005]
    5. Nacelle according to any one of claims 1 to 3 wherein the movable panel (313) is connected to the nacelle by a mechanical connection of the pivot type, the movable panel (313) pivoting towards the inside of the nacelle to pass from the closed position to the open position.
    [6" id="c-fr-0006]
    6. Platform according to claim 5 comprising an automatic return system (414) of the movable panel (313) in the closed position.
    [7" id="c-fr-0007]
    7. Nacelle according to any one of claims 1 to 3 wherein the movable panel (313) is connected to the nacelle by a mechanical linkage of the slide type, the movable panel (313) performing a translational movement inside of the nacelle to move from the closed position to the open position.
    [8" id="c-fr-0008]
    8. Platform according to any one of claims 1 to 7 wherein the inner wall (311) of the air inlet section (310) has a plurality of recesses (312) distributed circumferentially about a longitudinal axis. (X) of the nacelle, each recess (312) being covered by a movable panel (313).
    [9" id="c-fr-0009]
    9. Aircraft propulsion unit comprising a nacelle according to any one of claims 1 to 8 and a turbojet engine with a removable blade blower (340) mounted on a disc (330), each removable blade comprising a fastener (341). adapted to be moved in a corresponding cell (331) of the disk so as to clear the blade of the disk.
    [10" id="c-fr-0010]
    10. Propulsion unit according to claim 9, wherein the dimensions of a recess (312) in a longitudinal direction of the nacelle are provided so that when removing a blade, the head (342) of the blade ( 340) is at least partly within the recess while the blade attachment (341) disengages from the corresponding recess (331) of the disc (330).
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    同族专利:
    公开号 | 公开日
    FR3044053B1|2019-06-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4734007A|1987-03-03|1988-03-29|Rolls-Royce Plc|Fan casing and fan blade loading/unloading|
    EP2305985A2|2009-09-25|2011-04-06|Rolls-Royce plc|Containment casing for an aero engine|
    EP2628919A2|2012-02-20|2013-08-21|Rolls-Royce plc|An aircraft propulsion system nacelle|
    US20150226231A1|2014-02-13|2015-08-13|United Technologies Corporation|Fan Blade Removal Panel|EP3616844A1|2018-08-20|2020-03-04|Rolls-Royce plc|Fan blade removal method and tooling|
    FR3086643A1|2018-09-28|2020-04-03|Safran Nacelles|PLATFORM FOR AIRCRAFT AND ASSOCIATED AIR INTAKE|
    WO2020216712A1|2019-04-26|2020-10-29|Safran Nacelles|Nacelle air intake with acoustic panel|
    法律状态:
    2016-11-03| PLFP| Fee payment|Year of fee payment: 2 |
    2017-05-26| PLSC| Publication of the preliminary search report|Effective date: 20170526 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-10| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200304 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1561356|2015-11-25|
    FR1561356A|FR3044053B1|2015-11-25|2015-11-25|NACELLE FOR A TURBOJET ENGINE|FR1561356A| FR3044053B1|2015-11-25|2015-11-25|NACELLE FOR A TURBOJET ENGINE|
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