• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    An air intake structure (150) having an air inlet lip (158) and a front reinforcing frame (160) disposed within the air inlet lip (158). The front portion of the air inlet lip (158) has a plurality of sectors (120) angularly distributed along the leading edge of the air inlet lip (158), two sectors (120). neighbors being separated by an intermediate portion having an extra thickness. Each sector (120) has four edges (130a-b), each having an extra thickness (122a-b) relative to the remainder of the sector (120). Thus, the air inlet lip has a lighter structure.
    公开号:FR3060650A1
    申请号:FR1662817
    申请日:2016-12-20
    公开日:2018-06-22
    发明作者:Alain Porte；Patrick Oberle；Gregory ALBET
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to an air intake structure for an aircraft nacelle, an aircraft nacelle comprising such an air intake structure, an aircraft comprising at least one such nacelle, as well as a method of repair of such an air intake structure.
    STATE OF THE PRIOR ART
    An aircraft engine includes a nacelle in which the engine itself is housed. The basket, which takes an annular shape, has an air intake structure at the front.
    By convention, the terms front and rear are used throughout the text taking as reference the front and rear of the engine.
    The air intake structure generally comprises an inner face and an outer face in contact with the outside air, while the inner face delimits a vein which constitutes the blower channel.
    The function of the air intake structure is in particular to ensure the aerodynamic flow of air, on the one hand, towards the blower channel and, on the other hand, towards the outside of the nacelle.
    The air intake structure includes an air intake lip, a front reinforcement frame, an acoustic panel and an exterior panel.
    The air intake lip has the shape of a U open towards the rear in section. It forms the outer envelope of the front part of the air intake structure and it distributes the air between the part which enters the blower channel and the part which flows around the nacelle.
    The exterior panel extends the air intake lip on the exterior side and forms part of the exterior face.
    The front reinforcement frame also has the shape of a U open towards the rear in section and is placed inside and behind the air intake lip. The front reinforcement frame ensures the mechanical strength of the front part of the nacelle and helps to preserve its shape and sizing.
    The acoustic panel forms the interior envelope of the nacelle, behind the air intake lip, on the side of the blower channel. The acoustic panel therefore forms part of the interior face. The acoustic panel has a structure capable of attenuating noise and is of the sandwich composite type.
    It can happen that the air intake lip is subjected to shocks which can damage it.
    The repair of the air intake lip then consists in cutting the part of the air intake lip which is around the damaged area, in conforming a plate so that it takes the shape of the cut part, then fix the plate with fishplates.
    The ribs are placed inside the air intake lip straddling the shaped plate and the skin of the air intake lip remaining in place. Each splint is then fixed by screwing or riveting from the outside.
    To ensure that the screw or rivet heads are flush with the exterior surface of the skin of the air intake lip, it is necessary to make a countersink in the skin of the air intake lip from the outside. . The depth of the counterbore is conventionally on the order of 1.3 mm and the thickness of the skin of the air intake lip must therefore be greater and is conventionally between 1.6 mm and 2 mm.
    Although such a repair procedure gives satisfactory results, it is necessary to provide a relatively large thickness of skin all along the leading edge of the air intake lip, which is disadvantageous from the point of view weight and therefore fuel consumption.
    STATEMENT OF THE INVENTION
    An object of the present invention is to provide an air intake structure which makes it possible to have a reduced skin thickness while facilitating repairs.
    To this end, an air intake structure is proposed for an aircraft nacelle, said air intake structure comprising:
    - an air inlet lip with U-shaped section open towards the rear and ensuring the sharing of air between an inner face and an outer face,
    - a front reinforcement frame placed inside the air intake lip and integral with the air intake lip at an interior junction zone on the side of the interior face and a outer junction zone on the side of the outer face, the front part of the air intake lip having a plurality of sectors angularly distributed along the leading edge of the air intake lip, two neighboring sectors being separated by an intermediate part having an extra thickness, each sector having a first edge, a second edge, an inner edge and an outer edge, each edge of each sector having an excess thickness compared to the rest of the sector, the entry lip d air between the inner junction area and the extra thickness of the inner edge, an inner allowance, between the outer junction zone and the allowance of said outer edge, an outer allowance e, the extra thickness of the internal edge extending the internal excess thickness, the excess thickness of the external edge extending the external excess thickness, the additional thickness of the first edge extending the additional thickness of the intermediate part in contact, and the additional thickness of the second edge extending the additional thickness of the intermediate part in contact, the extended excess thicknesses being monobloc and mono-material and forming a single excess thickness.
    Thus, the air intake lip has a lighter structure.
    Advantageously, for each sector, the air intake structure comprises a predefined cutting line, identifiable from the outside and passing through the middle of each of said only extra thicknesses.
    The invention also provides a nacelle for an aircraft engine, said nacelle having an air intake structure according to one of the preceding variants.
    The invention also provides an aircraft comprising at least one nacelle according to the previous variant.
    The invention also provides a method of repairing an air intake structure according to a previous variant, said repair method comprising:
    - a cutting step during which an impacted sector is cut along the cutting line,
    a setting-up step during which a replacement sector identical to the cut sector is put in place of the cut sector, and
    - a fixing step during which the replacement sector is fixed by fishplates fixed by screwing or riveting from the outside at the extra thicknesses.
    Advantageously, the implementation step includes:
    - a pre-positioning sub-step during which a template showing the traces of the holes to be made is put in place around the replacement sector and the air intake lip,
    - a drilling sub-step during which holes are drilled at the appropriate locations defined by the template, and
    - a sub-step of installation during which screws or rivets are put in place in the holes thus produced.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
    Fig. 1 is a side view of an aircraft having an air intake structure according to the invention, FIG. 2 is a perspective view of an air intake structure under repair, and FIGS. 3 to 5 show side and sectional views of an air intake structure according to the invention during various repair stages.
    DETAILED DESCRIPTION OF EMBODIMENTS
    Fig. 1 shows an aircraft 100 which has a wing 102 and under the wing 102, a nacelle 104 according to the invention in which an engine is housed.
    The front of nacelle 104 has an air intake structure 150 according to the invention.
    Fig. 2 shows the nacelle 104 seen from the front. The nacelle 104 takes an annular shape and the air intake structure 150 comprises an internal face 152 and an external face 154 in contact with the outside air, while the internal face 152 defines a vein which constitutes the blower channel in which a blower is housed.
    Fig. 3 shows a section through the air intake structure 150.
    The air intake structure 150 includes, among other things, an air intake lip 158, an acoustic panel 162, a front reinforcement frame 160 and an exterior panel 164.
    The air intake lip 158 has in section the shape of a U open towards the rear, forms the outer envelope of the front part of the air intake structure 150 and ensures the sharing of the air between the inner face 152 and the outer face 154.
    The outer panel 164 extends rearward the air intake lip 158 on the side of the outer face 154 and thus constitutes a part of the outer face 154. The outer panel 164 is fixed to the intake lip of air 158 by means of rivets symbolized by a dashed line 302.
    The acoustic panel 162 extends rearward the air intake lip 158 on the side of the interior face 152, that is to say on the side of the blower channel 156, and thus constitutes part of the interior face. 152. The acoustic panel 162 is fixed to the air intake lip 158 by means of rivets symbolized by a dashed line 304.
    The front reinforcement frame 160 has in section the shape of a U open towards the rear and it is placed inside and is integral with the air intake lip 158. The front reinforcement frame 160 ensures the mechanical strength of the front part of the nacelle 104 and helps to preserve its shape and sizing.
    In the embodiment of the invention presented here, the front reinforcement frame 160 is in one piece with the air intake lip 158, but it could constitute a separate element fixed inside the intake lip d 158 through rivets.
    The front reinforcement frame 160 is integral with the air intake lip 158 at an internal junction zone 306 on the side of the internal face 152 and an external junction zone 308 on the side of the external face 154.
    The front part of the air intake lip 158, that is to say that which is in front of the front reinforcement frame 160, has a plurality of sectors 120 which are angularly distributed along the leading edge of the air intake lip 158.
    Each sector 120 is materialized by a line, here in dashed lines, which represents a cutting line 126 of the sector 120 predefined and identifiable from the outside. The cutting line 126 is said to be predefined when it is already drawn.
    Two neighboring sectors 120 are separated by an intermediate portion 124 which has a U-shaped section open towards the rear.
    Each sector 120 also has a U-shaped section open towards the rear.
    Each sector 120 thus has four edges, namely:
    - a first edge 128a,
    - a second edge 128b,
    - an inner edge 130a and
    - an outer edge 130b.
    The first and second edges 128a-b take the form of a U open towards the rear, and the inner edge 130a and the outer edge 130b generally take the form of an arc of a circle.
    Each edge 128a-b, 130a-b of each sector 120 has an extra thickness 5 122a-b relative to the rest of the sector 120, that is to say that the rest of the sector 120, between the extra thicknesses 122a-b, has reduced thickness compared to extra thicknesses
    122a-b.
    The air inlet lip 158 has, between the inner junction area 306 and the inner edge 130a, and more precisely the extra thickness 122a of said inner edge 130a, an inner extra thickness 132a.
    The air inlet lip 158 has, between the external junction zone 308 and the external edge 130b, and more precisely the additional thickness 122b of said external edge 130b, an external additional thickness 132b.
    Each intermediate part 124 also has an additional thickness.
    Thus, when the sector 120 is in position, the excess thickness 122a of the internal edge
    130a extends the internal allowance 132a, the allowance 122b of the external edge 130b extends the external allowance 132b, the allowance of the first edge 128a extends the allowance of the intermediate part 124 in contact, and the allowance of the second edge 128b extends the allowance of the part intermediate 124 in contact.
    During the manufacture of the air intake lip 158, the excess thicknesses which are extended are monobloc and mono-material and form a single additional thickness, and the cutting line 126 passes through the middle of this single additional thickness.
    The reduced thickness is for example of the order of 1 mm, while the extra thicknesses 122a-b, 132a-b are for example of the order of 1.6 mm to 2mm.
    Thus, the air intake lip 158 has a lighter structure than in the state of the art, since only the extra thicknesses are thickened.
    If there is an impact on a sector 120, it is then easy to cut the impacted sector by following the cutting line 126, separating the excess thicknesses which extend. Fig. 4 shows the air intake lip 158 for which a sector 120 has been cut. The cutting is done for example by positioning a predefined clipping tool using existing fixing holes outside the impact area.
    Of course, depending on the size of the impact, it is possible that several consecutive 120 sectors will be impacted. In this case, all of the sectors 120 which are impacted are cut along the cutting lines 126, and the intermediate parts 124 which are also impacted are also cut by extending the cutting lines 126.
    Fig. 5 shows the air intake lip 158 for which a replacement sector 520 has been put in place to replace the cut sector 120.
    The replacement sector 520 takes the same shape as the cut sector 120 and also has a first edge, a second edge, an inner edge 530a and an outer edge 530b, and each edge 130a-b has an extra thickness 522a-b relative to the rest of replacement area 520.
    When the replacement sector 520 is put in place, the additional thickness 522a of the internal edge 530a extends the internal additional thickness 132a, the additional thickness 522b of the external edge 530b extends the external additional thickness 132b, the additional thickness of the first edge extends the additional thickness of the intermediate portion 124 in contact, and the extra thickness of the second edge extends the extra thickness of the intermediate part 124 in contact.
    The replacement sector 520 is then fixed by fishplates 550 arranged inside the air intake lip 158 and fixed by screwing or riveting from the outside at the level of the extra thicknesses thus placed in the extension of one another. .
    The presence of the extra thickness allows the countersinking from the outside in order to hide the heads of screws or rivets.
    A method of repairing the air intake structure 150 thus consists of:
    a cutting step during which an impacted sector 120 is cut along the cutting line 126,
    a setting-up step during which a replacement sector 520 identical to the cut sector 120 is put in place of the cut sector 120, and
    - A fixing step during which the replacement sector 520 is fixed by fishplates 550 fixed by screwing or riveting from the outside at the extra thicknesses.
    As mentioned above, when several neighboring sectors 120 are impacted, the cutting step also consists in cutting the intermediate parts 124 between said sectors 120, and the setting up step consists in putting back a replacement sector which is identical to the assembly consisting of said sectors 120 cut out with the intermediate parts 124 cut out.
    The advantage of such an architecture is to be able to prepare for each sector 120 or more sectors 120 included, the intermediate parts 124, a spare part of shapes programmed in advance, in order to cover all the cases of possible repairs on the whole. from the surface of the lips. This avoids having to conform a plate as described in the state of the art, having to define and validate case by case repair concepts and sizes not known in advance. The external appearance of the entry lip of air 158 thus repaired is then a function of the size of the impact, very close to or identical to that of the new air intake lip 158.
    The positioning step includes a pre-positioning sub-step, a drilling sub-step, and a sub-step for installing screws or rivets.
    The pre-positioning sub-step consists of placing around a replacement sector 520 and the air intake lip 158 a template having the traces of the holes to be made. The template takes, for example, the form of a flexible sheet, of the tracing type, on which the positions of the holes to be drilled are materialized.
    The drilling sub-step consists of drilling the holes at the appropriate locations defined by the template. The drilling sub-step is carried out for example by positioning a predefined drilling tool, using existing fixing holes outside the impact zone.
    The implementation sub-step consists of installing the screws or rivets in the holes thus made.
    Each sector 120 extends between 10 ° and 30 ° around the axis of the nacelle 104, or between 12 to 36 sectors 120 by air intake, while each intermediate portion 124 extends between 0 and 2 ° around of the axis of the nacelle 104.
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1) Air intake structure (150) for an aircraft nacelle (104) (100), said air intake structure (150) comprising:
    - an air inlet lip (158) with a U-shaped section open towards the rear and 5 ensuring the sharing of air between an internal face (152) and an external face (154),
    - a front reinforcement frame (160) placed inside the air intake lip (158) and integral with the air intake lip (158) at an interior junction zone ( 306) on the side of the inner face (152) and an outer junction zone (308) on the side of the outer face (154),
    10 the front part of the air intake lip (158) having a plurality of sectors (120) angularly distributed along the leading edge of the air intake lip (158), two sectors (120 ) neighbors being separated by an intermediate part (124) having an extra thickness, each sector (120) having a first edge (128a), a second edge
    15 (128b), an inner edge (130a) and an outer edge (130b), each edge (128a-b, 130ab) of each sector (120) having an extra thickness (122a-b) relative to the rest of the sector (120 ), the air intake lip (158) having, between the interior junction zone (306) and the allowance (122a) of the interior edge (130a), an interior allowance (132a), between
    The outer junction zone (308) and the allowance (122b) of said outer edge (130b), an outer allowance (132b), the allowance (122a) of the inner edge (130a) extending the interior allowance (132a), the allowance (122b) of the outer edge (130b) extending the outer allowance (132b), the allowance of the first edge (128a) extending the
    25 extra thickness of the intermediate part (124) in contact, and the extra thickness of the second edge (128b) extending the extra thickness of the intermediate part (124) in contact, the extra thicknesses being monobloc and mono-material and forming a single extra thickness.
    [2" id="c-fr-0002]
    2) Air intake structure (150) according to claim 1, characterized in that, for each sector (120), it comprises a predefined cutting line (126), locatable from the outside and passing through the middle of each of said sole excess thicknesses.
    ίο
    [3" id="c-fr-0003]
    3) Nacelle (104) for an aircraft engine (100), said nacelle (104) having an air intake structure (150) according to one of claims 1 or 2.
    [4" id="c-fr-0004]
    4) Aircraft (100) comprising at least one nacelle (104) according to the preceding claim.
    5
    [5" id="c-fr-0005]
    5) Method for repairing an air intake structure (150) according to claim
    2, said repair process comprising:
    a cutting step during which an impacted sector (120) is cut along the cutting line (126),
    a setting-up step during which a replacement sector (520) identical to the cut sector (120) is put in place of the cut sector (120), and
    - A fixing step during which the replacement sector (520) is fixed by fishplates (550) fixed by screwing or riveting from the outside at the extra thicknesses.
    [6" id="c-fr-0006]
    6) Repair method according to claim 5, characterized in that the installation step comprises:
    a pre-positioning sub-step during which a template showing the traces of the holes to be made is put in place around the replacement sector (520) and the air intake lip (158),
    a drilling sub-step during which holes are drilled at the appropriate locations defined by the template, and
    - a sub-step of installation during which screws or rivets are put in place in the holes thus produced.
    PL. 1/3
    PL. 2/3
    PL. 3/3
    152
    158
    154
    302,164 t
    162
    104
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    US10676203B2|2020-06-09|
    FR3060650B1|2019-05-31|
    CN108202870A|2018-06-26|
    引用文献:
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    EP2194233A2|2008-12-05|2010-06-09|Rolls-Royce Deutschland Ltd & Co KG|Flow splitter for a fan engine|
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    FR3060651B1|2016-12-20|2020-11-06|Airbus Operations Sas|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE|
    US11125157B2|2017-09-22|2021-09-21|The Boeing Company|Advanced inlet design|FR3067955B1|2017-06-23|2019-09-06|Safran Aircraft Engines|METHOD FOR POSITIONING A HOLLOW PIECE|
    US11085373B2|2019-01-31|2021-08-10|Rolls-Royce North American Technologies Inc.|Gas turbine engine with mount for interchangeable inlets|
    FR3102080A1|2019-10-18|2021-04-23|Safran Nacelles|Repair process for an air inlet lip|
    法律状态:
    2017-12-21| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-22| PLSC| Publication of the preliminary search report|Effective date: 20180622 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1662817A|FR3060650B1|2016-12-20|2016-12-20|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE|
    FR1662817|2016-12-20|FR1662817A| FR3060650B1|2016-12-20|2016-12-20|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE|
    US15/834,605| US10676203B2|2016-12-20|2017-12-07|Air input structure for an aircraft nacelle|
    CN201711387468.0A| CN108202870B|2016-12-20|2017-12-20|Air inlet structure of aircraft nacelle, repairing method thereof, nacelle and aircraft|
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