• 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 invention relates to a device (36) for attaching a downstream end of an air inlet (14) to a fan casing (30) of a nacelle (10) of a turbojet engine (12). the air inlet (14) having an acoustic shell (28) radially delimited by an inner skin (32) and an outer skin (34) enclosing an acoustic panel (70), the device (36) ) having a first flange (38) which is integral with the housing (30), and a second L-shaped flange (40) which comprises a base (48) adapted to be connected to the ferrule (28), and a flange ( 50) intended to be connected to the second flange (38), characterized in that it comprises an outgrowth (56) extending longitudinally from an upstream section (58) integral with the outer skin (34) of the ferrule ( 28), to a flared downstream section (60) which delimits a space (62) radial with the ferrule (28) and which is adapted to be fixed on the base (48) of the second br L-shaped design (40) by fastening means (61) without altering the outer skin (34) of the shell (28).
    公开号:FR3026134A1
    申请号:FR1458829
    申请日:2014-09-18
    公开日:2016-03-25
    发明作者:Bertrand Desjoyeaux；Simon Verger；Sylvain Sentis
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to an air intake of an aircraft turbojet engine nacelle. More specifically, the invention relates to a particular form of the structure of the air inlet for its attachment to a nacelle fan casing 5 along a radial interface surface. An aircraft is driven by several turbojet engines each housed in a nacelle housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped. A turbojet engine nacelle generally has a substantially tubular structure which extends along a longitudinal axis from upstream to downstream, depending on the direction of flow of the airflow. The nacelle comprises an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section surrounding the combustion chamber of the turbojet engine, intended to channel the secondary air stream and possibly including means thrust reverser, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine. The air inlet comprises in particular an annular inlet lip 20 forming a leading edge which is adapted to allow optimum capture of the air necessary for the supply of the blower and the internal compressors of the turbojet engine. Downstream of the lip, an acoustic downstream structure properly channels the air to the vanes of the blower. This downstream structure of the air inlet comprises in particular an annular duct, the structure of which is particularly adapted to attenuate the noise emitted by the turbojet engine, also called the acoustic air inlet shell. For this purpose the shell is mainly composed of an acoustic sandwich structure comprising, an acoustically permeable skin also forming an inner skin of the air duct, an impervious outer skin, and a honeycomb core of predetermined height connecting the two skins, this core being generally of honeycomb type, the assembly constituting an acoustic damper. The ferrule is assembled in its downstream part with the blower housing according to a clamping plane by means of a device comprising fasteners connecting vis-à-vis the flange of the air intake ferrule and the housing.
    [0002] For safety reasons in case of loss of a blade of the blower, the clamping plane must be positioned upstream of the blade of the plane of the blower. In addition, it is desirable to attenuate the noise emitted by the engine 5 upstream and downstream of the clamping plane and to maximize the surface of the acoustically effective internal vein, and in particular the acoustic surface of the inlet ferrule air. For this purpose, the document FR-A-2767560 describes and represents a device comprising a first L-shaped flange integral with the fan casing 10 and a second L-shaped flange whose axial base is riveted to the outer skin of the shell and of which one radial flange is attached to the first flange. This type of device has the disadvantage of having to bind the inner skin and the outer skin of the ferrule to associate them in one with the attachment zone of the second L-shaped flange. Moreover, the interlocking of a upstream portion of the housing in the shell is difficult to achieve and may cause vibration instability of the upstream portion of the housing which is cantilevered. It also increases the risk of damage to the end of the parts during the interlocking. Also known is FR-A-2869360 which proposes a second L-shaped flange attached to the outer skin of the ferrule, this type of device has the disadvantage of perforating the outer skin. The quality of the fixation is difficult to verify and the acoustic cavity between the outer skin and inner skin is impaired reducing the efficiency of the area. This document also proposes an L-flange directly glued or made to the back of the outer skin of the ferrule, however this device has the risk of punching the cellular material connecting the inner skin and the outer skin during the mechanical deformations induced by the operation. of the turbojet. There is also known a device described and shown in the document FR-A-2959726 which comprises a first flange which is integral with the housing and a second flange which is integral with the ferrule. This device provides advantages by proposing an L-flange bonded to the ferrule and which is offset to the back of the outer skin of the ferrule which avoids impacting the acoustic treatment of said ferrule, but is difficult and expensive to achieve.
    [0003] The present invention aims in particular to solve these disadvantages and relates for this purpose to a device for fixing a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle, the air inlet comprising an acoustic ferrule having an annular shape which extends axially from upstream to downstream along a longitudinal axis and which is delimited radially by an internal skin and an external skin trapping an acoustic panel, the device comprising a first flange which is secured to the housing, and a second L-shaped flange which comprises a base adapted to be connected to the shell, and a flange adapted to be connected to the second flange, characterized in that it comprises a protrusion which s' extends longitudinally from an integral upstream section of the outer skin of the ferrule, to a flared upstream section which delimits a radial space with the ferrule and which is adapted é to be fixed on the base of the second L-shaped flange by fixing means without altering the outer skin of the ferrule. The device according to the invention is of simple design and offers a reliable and costly solution for fixing a ferrule on a fan casing. In addition, the invention makes it possible not to alter and maintain the integrity of the acoustic structure of the ferrule formed by the outer skin, the inner skin and the acoustic panel of the ferrule. Preferably, the protuberance has the shape of an annular ring which extends around the axis of the ferrule. In addition, the acoustic panel of the ferrule extends longitudinally continuously from upstream to downstream at least to the downstream portion of the protrusion. The ring and the second flange can each be made of a separate material which is chosen to best meet the mechanical stress and imposed weight requirements. Preferably, the second flange is made of metallic material. This type of material offers an elastic resistance greater than a composite material, thus allowing to absorb significant forces without breaking.
    [0004] According to a preferred embodiment, the second flange is made of a plurality of independent parts which are arranged in a ring around the axis of the ferrule. In addition, the crown is made of composite material.
    [0005] This type of material offers a weight / strength compromise adapted to the mechanical stresses subjected to the crown. Advantageously, the ring has a wavy shape that draws an alternation of valleys and bumps distributed around the axis of the shell, said bumps each forming a radial extra thickness designed to promote the attachment of the second L-shaped flange. The acoustic panel extends longitudinally downstream beyond the plane of the second L-shaped flange. The design of the device according to the invention makes it possible not to perforate the acoustic panel by means of fixing, thus preserving all the performances of sound absorption of the panel. In addition, the device comprises a wedge which is interposed radially between the outer skin of the ferrule and the flared downstream portion of the crown. Finally, the fastening means comprise a plurality of metal links which connect the flared downstream portion of the ring to the base 20 of the second L-shaped flange. Other characteristics and advantages of the invention will become apparent on reading the description. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is a schematic view in longitudinal section, which illustrates an aircraft turbojet engine nacelle; - Figure 2 is a schematic longitudinal sectional view, which illustrates a device for fixing the air intake ring on a fan casing of the nacelle of Figure 1, according to the invention; Figure 3 is a perspective detail view, which illustrates the first flange and the second flange of the device of Figure 2; - Figure 4 is a detail view broken away in perspective, which illustrates the first flange and the second flange of the device of Figure 2 according to an alternative embodiment; FIG. 5 is a detail view broken away in perspective, which illustrates the connecting ring of the second flange on the ferrule of the device of FIG. 2; FIG. 6 is a detail view in cross-section, which illustrates the connecting ring of the second flange on the ferrule of the device of FIG. 2. To clarify the description and the claims, the terminology will be adopted in a nonlimiting manner. longitudinal, vertical and transverse with reference to the trihedron L, V, T indicated in the figures, whose axis L is parallel to the axis A of the nacelle. In addition, the terms "upper", "lower" and "lower" in reference to the upper and lower portions of FIG. 2, respectively, will be used in a nonlimiting manner, and the terms "inside" and "outside" in reference to FIG. inside of the nacelle and outside the nacelle respectively. Note also that in the present patent application, the terms "upstream" and "downstream" must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet, that is to say from left to right according to Figure 1. For different embodiments, the same references may be used for identical elements or ensuring the same function, for the sake of simplification of the description . FIG. 1 shows a nacelle 10 of turbojet engine 12 which has a tubular structure and which extends along a longitudinal axis A from upstream to downstream in the direction of flow of the air flow, from the left towards the right according to FIG. 1. The nacelle 10 comprises an air inlet 14 arranged upstream of the turbojet engine 12, a median section 16 intended to surround a fan 18 of the turbojet engine 12, a downstream section 20 intended to surround the combustion chamber the turbojet engine 12 and optionally incorporating thrust reverser means (not shown), and an exhaust nozzle 22. The air inlet 14 comprises in particular an annular inlet lip 24 forming a leading edge, and an acoustic tubular downstream tubular structure 28 on which the lip 24 is attached to channel the air towards the blades of the fan 18. The acoustic shell 28 is extended longitudinally by a fan casing 30 to guide the air flow. As can be seen in FIG. 2, the ferrule 28 has an annular shape of axis A, which extends axially from upstream to downstream along the longitudinal axis A of the nacelle 10 and which is delimited. radially by an inner skin 32 and an outer skin 34 which traps a cellular acoustic panel 70. The inner skin 32 is acoustically permeable and is, for example, comprised of a perforated skin allowing the sound waves to pass through it. Conversely, the outer skin is waterproof and acoustically impermeable. Also, the acoustic panel 70 is preferably a cellular material keeping the inner skin 32 and the outer skin 34 at a distance, the acoustic panel 70 forming a cavity designed to absorb and dampen the sound waves. The nacelle 10 is equipped with a device 36 for attaching the air inlet 14 to the fan casing 30, more particularly for fixing the acoustic shell 28 to the casing 30. For this purpose, the device 36 of fixing comprises a first metal flange 38 which is fixed on an upstream end of the casing 30, and a second L-shaped metal flange 40 which is fixed on a downstream end of the shell 28. The first flange 38 has a base 42 of annular shape which extends generally axially along the longitudinal axis A of the nacelle 10 and which is fixed on the housing 30 by a mechanical connection means (not shown) as a set of screws and nuts for example, or by any other means of attachment. In addition, the first flange 38 has an annular flange 44 projecting radially outwardly from the base 42 and defining a first radial clamping face 46 arranged facing the second flange 40. Similarly, the second flange 38 flange 40 has a base 30 of annular shape which extends generally axially along the longitudinal axis A of the nacelle 10 and an annular flange 50. The flange 50 of the second flange 40 projects radially outwardly from the associated base 48, the flange 50 delimiting a second radial flange face 52 intended to cooperate with the first complementary flange face 46 of the first flange 38. .
    [0006] For this purpose, the second clamping face 52 and the first clamping face 46 are contiguous along a radial clamping plane P, and they each delimit a series of holes for the passage of fastening means, such as a set of screws and bolts. nuts 54 for example, or any other means of attachment.
    [0007] Preferably, the second flange 40 is made of metal alloy, and preferably of aluminum alloy or titanium. These alloys have high strengths and elongations before rupture which are particularly suitable for producing this type of flange which must withstand large deformations imposed by the casing 30 in extreme cases of failure of a blade of the blower. According to an alternative embodiment, the second flange 40 may be made of composites among discontinuous and continuous fiber thermocompression technologies, or RTM molding of fibrous textures. The fibers are preferably selected from carbon fibers, glass fibers, and matrices from thermosetting epoxy polymers and thermoplastics from the Polyaryletherketone family. Also, to reduce flatness defects to the right of the clamping plane P, the flange 50 of the second flange 40 and the flange 44 of the first flange 38 can be machined. According to a preferred embodiment shown in FIG. 3, the second flange 40 is made of a plurality of sector-shaped portions 55 which are independent and identical and which are arranged in a ring around the axis of the ferrule 28. According to the example shown in FIG. 3, each part 55 delimits three holes which are uniformly distributed around the axis A and which are provided for the passage of the fastening means on the first flange 38. According to another example embodiment shown in Figure 4, the second flange 40 is made in one piece in the form of a ring. In addition, without limitation, the second flange 40 may be made of a plurality of parts which are mechanically interconnected by means of reported links. According to another aspect of the invention, the device 36 comprises an annular annular protrusion 56 which extends around the axis A of the nacelle 10 and which extends longitudinally from an upstream section 58 integral with the outer skin 34 of the shell 28, to a downstream section 60 which is adapted to be fixed on the base 48 of the second flange 40 L by fastening means 61. Note that the ring 56 is independent of the second flange 40.
    [0008] The downstream section 60 of the ring 56 has a generally frustoconical flared shape of increasing radial section in an axial direction from upstream to downstream, this flared shape allowing the downstream section 60 to delimit a radial space 62, or cavity, with the outer skin 34 of ferrule 28.
    [0009] In addition, the ring 56 is made of composite material. According to a preferred embodiment, the ring 56 is made of a succession of fabric skins which are pre-impregnated with a binder, such as resin. According to a preferred embodiment, the ring 56 is made at the same time as the outer skin 34 of the shell 28, by a stack of layers of fabric and / or fibers that can be part of the constitution of the outer skin 34. The layers of fabrics and / or fibers are impregnated with resin and solidified by polymerization. Also, the skins of the crown 56 may be made by the process of placing fibers pre-impregnated with binder or draping of pre-impregnated sheets of binder. The ring 56 can also be made by injection molding, for example by a resin injection process in a fiber preform 25 arranged in a mold, this type of process is known by the acronym RTM for "resin transfer molding". . After its manufacture, the ring 56 can be glued or co-cured with the fiber layers of the outer skin 34 of the ferrule 28. Without limitation, the crown can be made by any other type of manufacturing process. composite material part. To constitute the radial space 62 formed between the downstream portion 60 of the ring 56 and the outer skin 34 of the shell 28, an extractable tooling element (not shown) can be inserted for draping and polymerization of the assembly. . The downstream section 60 of the ring 56, which is radially offset from the acoustic shell 28, has the advantage of not altering the geometric shape of the acoustic assembly formed by the outer skin 34, the inner skin 32 and the panel. acoustic 70 of the ferrule 28 which then extends axially downstream continuously beyond the ring 56 and can extend to the clamping plane P, and possibly even beyond inside the housing of According to an alternative embodiment of the invention, the device 36 comprises a wedge 64 of triangular section, shown in FIG. 4, which is interposed radially between the outer skin 34 of the ferrule 28 and the downstream section 60 flush with the crown 56.
    [0010] The wedge 64 is for example made of composite material and in particular makes it possible to avoid or limit the deformation of the downstream section 60 of the ring 56, the wedge 64 possibly having the shape of a closed or open ring or formed of several angular sectors. . With reference to FIG. 2, the fixing means 61 of the downstream section 60 of the ring 56 on the base 48 of the second flange 40 comprise a plurality of metal links, such as a set of screws and nuts and / or a set of rivets for example. These fastening means are not shown in FIGS. 3 to 5. The base 48 of the second flange 40 delimits a series of holes 65 for the passage of the fastening means 61. In order to ensure a reliable fastening of the ring gear 56 on the second flange 40, the holes 65 are distributed in two rows, staggered as shown in Figure 4 or vis-à-vis as shown in Figure 3. In addition, the downstream section 60 of the ring 56 can be machined if 25 necessary to promote cooperation between the downstream section 60 of the ring 56 and the base 48 of the second flange 40 associated. According to a preferred embodiment of the invention illustrated in FIGS. 5 and 6, the downstream section 60 of the ring 56 has an undulating shape which draws an alternation of recesses 66 and bumps 68 distributed around the axis A of the ferrule 28. The bumps 68 each form a radial extra thickness designed to promote the fixing of the ring 56 on the second flange 40 by the fastening means 61, as can be seen in FIG. 6. Finally, with reference to FIG. the acoustic panel 70 extends longitudinally beyond the plane P of the second flange 40 in L.
    [0011] By way of non-limiting example, the acoustic panel 70 may extend only to the clamping plane P, the casing 30 then comprising an additional acoustic panel arranged in the extension. Advantageously, the fixing device 36 according to the invention is lightweight, of simple, robust and reliable design, and it makes it possible to connect the ferrule 28 to the casing 30 without perforating the acoustic panel 70, thus preserving all its absorption capacities. noise.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Device (36) for fixing a downstream end of an air inlet (14) on a fan casing (30) (18) of a nacelle (10) of an aircraft turbojet (12), l air inlet (14) having an acoustic ferrule (28) having an annular shape which extends axially from upstream to downstream along a longitudinal axis (A) and which is delimited radially by an inner skin (32) and a outer skin (34) enclosing an acoustic panel (70), the device (36) having a first flange (38) which is integral with the housing (30), and a second L-shaped flange (40) which comprises a base ( 48) adapted to be connected to the shell (28), and a flange (50) adapted to be connected to the second flange (38), characterized in that it comprises a protuberance (56) extending longitudinally from a upstream section (58) secured to the outer skin (34) of the shell (28), to a flared downstream section (60) which delimits a space (62) radial with the ferrule (28) and which is adapted to be fixed on the base (48) of the second flange (40) L by fastening means (61) without altering the outer skin (34) of the shell (28).
    [0002]
    2. Device (36) according to claim 1, characterized in that the protrusion (56) has the shape of an annular ring which extends around the axis (A) of the ferrule (28).
    [0003]
    3. Device (36) according to any one of the preceding claims, characterized in that the acoustic panel (70) of the ferrule (28) extends longitudinally continuously from upstream to downstream at least up to 25 downstream (60) of the outgrowth (56).
    [0004]
    4. Device (36) according to any one of the preceding claims, characterized in that the second flange (40) is made of metallic material.
    [0005]
    5. Device (36) according to any one of the preceding claims, characterized in that the second flange (40) is made of a plurality of independent portions (55) which are arranged in a ring around the axis (A). of the ferrule (28).
    [0006]
    6. Device (36) according to any one of the preceding claims, characterized in that the protrusion (56) is made of composite material.
    [0007]
    7. Device (36) according to any one of the preceding claims, characterized in that the protrusion (56) has an undulating shape which draws an alternation of recesses (66) and bumps (68) distributed around the axis (A) the ferrule (28), said bosses (68) each forming a radial extra thickness designed to promote the attachment of the second flange (40) L on the protrusion (56).
    [0008]
    8. Device (36) according to any one of the preceding claims, characterized in that the acoustic panel (70) extends longitudinally downstream beyond the plane of the second flange (40) L.
    [0009]
    9. Device (36) according to any one of the preceding claims, characterized in that it comprises a wedge (64) which is interposed radially between the outer skin (34) of the ferrule (28) and the downstream section ( 60) flared out of the protrusion (56).
    [0010]
    10. Device (36) according to any one of the preceding claims, characterized in that the fastening means (61) comprise a plurality of metal links which connect the downstream section (60) flared out of the protrusion (56) on the base (48) of the second flange (40). 20
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3026134B1|2019-07-19|DEVICE FOR FIXING AN AIR INLET ON A BLOWER HOUSING OF AN AIRCRAFT TURBOJET AIRCRAFT
    EP1591643A1|2005-11-02|Noise reduction assembly for flight gas turbine
    FR2767560A1|1999-02-26|NOISE REDUCTION ASSEMBLY FOR AN AIRCRAFT TURBOREACTOR
    WO2008043903A2|2008-04-17|Bypass turbojet engine nacelle
    FR2956876A1|2011-09-02|STRUCTURAL AND AERODYNAMIC MODULE OF A TURBOMACHINE CASING AND CARTER STRUCTURE COMPRISING A PLURALITY OF SUCH A MODULE
    FR3036136B1|2019-07-12|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOREACTOR COMPRISING A COMPOSITE DISCHARGE DUCT
    FR2907098A1|2008-04-18|Nacelle for sheltering e.g. two-flow turbojet, has rear section with external structure rigidly connected to part for supporting turbojet, and attachment unit joining nacelle to pylon that is intended to be connected to fixed structure
    FR2925118A1|2009-06-19|ABRADABLE SUPPORT PANEL IN A TURBOMACHINE
    FR3026122A1|2016-03-25|ACOUSTIC TREATMENT PANEL
    EP2811121A1|2014-12-10|Composite casing for axial turbomachine compressor with metal flange
    FR2976974A1|2012-12-28|DEVICE FOR ASSEMBLING ACOUSTIC PANELS OF A TURBOMACHINE NACELLE
    FR2956875A1|2011-09-02|Blade for use in casing of turbomachine of double flow airplane, has two plates made of draped composite material, where one of plates forms lower surface of blade and other plate forms upper surface of blade
    FR3011271A1|2015-04-03|DEVICE FOR CONNECTING A FIXED PART OF A TURBOMACHINE AND A DISTRIBUTOR FOOT OF A TURBOMACHINE TURBINE
    WO2011144836A2|2011-11-24|Aerodynamic element for an aircraft nacelle
    FR3013393A1|2015-05-22|
    EP2714517B1|2017-08-02|Assembly for an aircraft nacelle
    WO2011138571A1|2011-11-10|Unit for an aircraft thruster
    FR3058762A1|2018-05-18|ACOUSTICAL ATTENUATION PANEL COMPRISING A FRONT SKIN AND A CENTRAL STRUCTURE
    FR2995026B1|2019-06-07|FRONT FRAME FOR A DEVIATION GRID REVERSING INVERTER STRUCTURE
    FR3016159A1|2015-07-10|AIRCRAFT TURBO BURNER BOAT COMPRISING AN INCREASED RIGIDITY AIR INTAKE ASSEMBLY
    FR3075759A1|2019-06-28|ANTERIOR PLATFORM PART OF A PROPELLANT AIRCRAFT COMPRISING A SHOCKING ELEMENT
    EP3215358B1|2018-01-31|Method of repairing a perforated skin of a panel using a doubler
    FR3029831A1|2016-06-17|PROCESS FOR THE REPAIR OF AN ACOUSTIC PANEL OF COMPOSITE MATERIAL
    WO2019105610A1|2019-06-06|Assembly for axial turbomachine, associated axial turbomachine, assembly method and sealing joint
    FR3031360A1|2016-07-08|PROPULSIVE ASSEMBLY FOR AIRCRAFT
    同族专利:
    公开号 | 公开日
    FR3026134B1|2019-07-19|
    CN106715267A|2017-05-24|
    US10415472B2|2019-09-17|
    WO2016042271A1|2016-03-24|
    US20170184023A1|2017-06-29|
    EP3194749A1|2017-07-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2767560A1|1997-08-19|1999-02-26|Aerospatiale|NOISE REDUCTION ASSEMBLY FOR AN AIRCRAFT TURBOREACTOR|
    WO2012175850A1|2011-06-24|2012-12-27|Safran|Turbomachine casing acoustic panels fitted with improved attachment devices|
    FR2988778A1|2012-03-29|2013-10-04|Aircelle Sa|AIR INTAKE STRUCTURE OF LAMINAR TYPE TURBOREACTOR NACELLE AIRCRAFT|US20160251085A1|2014-09-18|2016-09-01|The Boeing Company|Method of attaching nacelle structure to minimize fatigue loading|
    FR3087827A1|2018-10-25|2020-05-01|Safran Aircraft Engines|BLOWER HOUSING OF COMPOSITE MATERIAL INCLUDING METAL FLANGES|GB2010434B|1977-12-16|1982-06-30|Rolls Royce|Flanged joint structure for composite materials|
    FR2840647B1|2002-06-05|2004-10-29|Airbus France|DEVICE FOR CONNECTING TWO TUBULAR PIECES OF AIRCRAFT TURBOREACTOR|
    FR2869360B1|2004-04-27|2006-07-14|Airbus France Sas|NOISE REDUCING ASSEMBLY FOR AIRCRAFT TURBOJET ENGINE|
    FR2898870B1|2006-03-24|2008-05-23|Aircelle Sa|AIR INLET VIROLET STRUCTURE|
    FR2936223B1|2008-09-23|2010-09-17|Airbus France|DEVICE FOR CONNECTING AN AIR INLET AND A MOTORIZATION OF AN AIRCRAFT NACELLE|
    FR2959726B1|2010-05-07|2013-05-31|Aircelle Sa|ASSEMBLY FOR PROPULSIVE AIRCRAFT SYSTEM|
    FR2966127B1|2010-10-15|2013-06-14|Airbus Operations Sas|AIRCRAFT NACELLE INCORPORATING AT LEAST ONE RADIAL PITCH BETWEEN TWO CONDUITS|
    US9151181B2|2012-06-19|2015-10-06|United Technologies Corporation|Metallic rails on composite fan case|FR3033839B1|2015-03-16|2018-09-28|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A BLOWER HOUSING EQUIPPED WITH AN ACOUSTIC COATING INTEGRATING A BLOWER HOUSING STIFFENER|
    WO2017074407A1|2015-10-30|2017-05-04|Siemens Energy, Inc.|System and method for attaching a non-metal component to a metal component|
    US10589869B2|2018-07-25|2020-03-17|General Electric Company|Nacelle inlet lip fuse structure|
    CN109606708A|2018-12-03|2019-04-12|江西洪都航空工业集团有限责任公司|A kind of small size inlet structure preparation method|
    FR3097902A1|2019-06-27|2021-01-01|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE WITH AT LEAST PARTLY COMPOSITE ENCLOSURE|
    法律状态:
    2015-09-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-25| PLSC| Search report ready|Effective date: 20160325 |
    2016-08-10| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-24| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2018-09-07| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458829A|FR3026134B1|2014-09-18|2014-09-18|DEVICE FOR FIXING AN AIR INLET ON A BLOWER HOUSING OF AN AIRCRAFT TURBOJET AIRCRAFT|
    FR1458829|2014-09-18|FR1458829A| FR3026134B1|2014-09-18|2014-09-18|DEVICE FOR FIXING AN AIR INLET ON A BLOWER HOUSING OF AN AIRCRAFT TURBOJET AIRCRAFT|
    CN201580050534.8A| CN106715267A|2014-09-18|2015-09-17|Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle|
    EP15788468.5A| EP3194749A1|2014-09-18|2015-09-17|Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle|
    PCT/FR2015/052495| WO2016042271A1|2014-09-18|2015-09-17|Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle|
    US15/459,014| US10415472B2|2014-09-18|2017-03-15|Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle|
    [返回顶部]