• 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 an air intake structure (350) for an aircraft nacelle (104) (100), said air intake structure (350) comprising: - an air inlet lip (158) having a U-shaped section open towards the rear and providing for the sharing of air between an inner face (152) and an outer face (154) and having a stopping point (250), - a panel acoustic device (162) attached to the rear of the air intake lip (158) on the inside face side (152) at a first assembly point (10a), - an outer panel (113) ) attached to the rear of the air inlet lip (158) on the outer face side (154) at a second connection point (20a), - a front reinforcement frame (160) placed inside the air inlet lip (158) and attached to the air inlet lip (158), on the inner side (152) side at a first attachment point (30a) and on the side of the outer face (154) at a level of two th fixing point (40a), the air inlet structure (350) being such that the length of the rope between said stopping point (250) and each fixing point (30a, 40a) is between 1 1/3 and 1/6 of the total rope between the stopping point (250) and the joining point (10a, 20a) on the same side. The position of the front reinforcing frame allows a heat dissipation between the junction of the front reinforcing frame and the air inlet lip and the acoustic panel and the outer panel which are no longer impacted by any temperature increases. .
    公开号:FR3060651A1
    申请号:FR1662815
    申请日:2016-12-20
    公开日:2018-06-22
    发明作者:Alain Porte；Patrick Oberle；Gregory ALBET；Eric Haramburu；Vincent BILLEROT；Frederic Piard；Franck Oundjan
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    Holder (s): AIRBUS OPERATIONS Simplified joint-stock company, AIRBUS Simplified joint-stock company.
    Extension request (s)
    Agent (s): LE GUEN & ASSOCIES Professional civil society.
    AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE.
    FR 3 060 651 - A1 (5 /) The invention relates to an air intake structure (350) for an aircraft nacelle (104) (100), said air intake structure (350) comprising :
    - an air intake lip (158) with a U-shaped section open towards the rear and ensuring the sharing of air between an inner face (152) and an outer face (154) and having a point d 'stop (250),
    - an acoustic panel (162) fixed to the rear of the air intake lip (158) on the side of the interior face (152) at a first assembly point (10a),
    - an external panel (113) fixed to the rear of the air intake lip (158) on the side of the external face (154) at a second connection point (20a),
    - a front reinforcement frame (160) placed inside the air intake lip (158) and fixed to the air intake lip (158), on the side of the interior face (152) at a first fixing point (30a) and on the side of the external face (154) at a second fixing point (40a), the air intake structure (350) being such that the length of the rope between said stopping point (250) and each fixing point (30a, 40a) is between 1/3 and 1/6 of the total rope between the stopping point (250) and the point d 'assembly (10a, 20a) located on the same side.
    The position of the front reinforcement frame allows heat to be dissipated between the junction of the front reinforcement frame and the air intake lip and the acoustic panel and the exterior panel which are no longer affected by any temperature increases .

    i
    AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE
    TECHNICAL AREA
    The present invention relates to an air intake structure for an aircraft nacelle, an aircraft nacelle comprising such an air intake structure, as well as an aircraft comprising at least one such nacelle.
    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.
    On the side of the inner face, the front reinforcement frame is fixed, on the one hand, to the air intake lip for example by means of rivets, and, on the other hand, to the acoustic panel at the level of its front part, for example by means of rivets.
    On the side of the exterior face, the front reinforcement frame is fixed, on the one hand, to the air intake lip for example by means of rivets, and, on the other hand, to the exterior panel by the with rivets.
    The volume at the front between the air intake lip and the reinforcement frame is supplied with hot gas from the engine. This hot gas then heats the air intake lip to prevent the formation of frost.
    Aircraft engines tend to exhibit increasing dilution rates, which results in a sharp increase in the temperature of the hot gas from the engine.
    If the air intake lip and the front reinforcement frame which are made of aluminum alloy can withstand relatively high temperatures, this is not the case of the acoustic panel and the exterior panel which are made of composite materials .
    In the long term, the temperature of the hot gas could thus reach values incompatible with the composite materials constituting the acoustic panel and the exterior panel.
    STATEMENT OF THE INVENTION
    An object of the present invention is to provide an air intake structure which allows better evacuation of heat at the level of the air intake lip.
    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 and having a stop point,
    - an acoustic panel fixed to the rear of the air intake lip on the side of the interior face at the level of a first assembly point,
    - an exterior panel fixed to the rear of the air intake lip on the side of the exterior face at a second assembly point,
    - a front reinforcement frame placed inside the air intake lip and fixed to the air intake lip, on the side of the interior face at a first attachment point and on the side of the external face at a second fixing point, the air intake structure being such that the length of the cord between said stopping point and each fixing point is between 1/3 and 1 / 6 of the total rope between the breakpoint and the assembly point on the same side.
    The position of the front reinforcement frame allows heat to be dissipated between the junction of the front reinforcement frame and the air intake lip and the acoustic panel and the exterior panel which are no longer affected by any temperature increases .
    According to a particular embodiment, the attachment to the first attachment point and the attachment to the second attachment point are provided by rivets.
    According to a particular embodiment, the attachment to the first attachment point and the attachment to the second attachment point are provided by welding.
    According to a particular embodiment, the attachment to the first attachment point and the attachment to the second attachment point are ensured by the fact that the air intake lip and the front reinforcement frame constitute a single piece produced in a single piece. and mono-material.
    Advantageously, the air intake lip and the front reinforcement frame are made of titanium alloy.
    Advantageously, the length of the cord on the air intake lip between the stopping point and the attachment point of the inner face is 170 to 320 mm, the length of the cord on the intake lip d between the stop point and the fixing point of the external face is 150 to 250 mm, the length of the cord on the air intake lip between the fixing point of the internal face and the first assembly point of the interior face is between 20 and 80 mm, and the length of the cord on the air intake lip between the attachment point of the exterior face and the second assembly point of the face outside is between 15 and 80 mm.
    The invention also provides a nacelle for an aircraft engine, said nacelle having an air intake structure according to one of the preceding variants, a supply pipe which takes hot gas from the engine and injects it in a volume between the air intake lip and the front reinforcement frame, a control unit, a pressure sensor intended to measure the pressure in the supply line and a single valve mounted on the supply line and provided for alternately taking an open position in which it lets hot gas pass through the supply line, or a closed position in which it does not let hot gas pass through the supply line, where the position of the valve is controlled by the control unit based on the pressure information that the control unit receives from the pressure sensor.
    The invention also provides an aircraft comprising at least one nacelle according to the previous variant.
    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 schematic sectional representation of a nacelle according to the invention, FIG. 3 is a sectional view of an air intake structure according to a first embodiment of the invention, and FIG. 4 is a sectional view of an air intake structure according to a second embodiment of the invention.
    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 inside which the motor 202 is housed. The nacelle 104 takes an annular shape and the air intake structure 150 comprises an inner face 152 and an outer face 154 in contact with the air exterior, while the interior face 152 delimits a vein 156 which constitutes the fan channel.
    In the blower channel 156 is housed a blower 204.
    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 113.
    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 113 extends rearward the air intake lip 158 on the side of the outer face 154 and thus forms part of the outer face 154.
    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 front reinforcement frame 160 has in section the shape of a U open towards the rear and it is placed inside 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.
    The air intake structure 150 comprises, between the air intake lip 158 and the front reinforcement frame 160, a volume 206.
    The nacelle 104 also has a supply line 208 which takes hot gas from the engine 202, in particular in the high pressure section of the engine 202, and injects it into the volume 206 by passing through the front reinforcement frame 160.
    To regulate the quantity of hot gas injected into the volume 206, the nacelle 104 comprises a control unit 214, a pressure sensor 210 provided for measuring the pressure in the supply line 208 and a single valve 212 mounted on the line d 'supply 208 and designed to alternately take an open position in which it lets hot gas pass through the supply line 208, or a closed position in which it does not let hot gas pass through the supply line 208. The position of the valve 212 is controlled by the control unit 214 according to the pressure information that the control unit 214 receives from the pressure sensor 210. The control unit 214 takes for example the form of a processor.
    Fig. 3 shows an air intake structure 350 according to a first embodiment of the invention and FIG. 4 shows an air intake structure 450 according to a second embodiment of the invention.
    On the side of the inner face 152, the rear of the air intake lip 158 is fixed to the front part of the acoustic panel 162 at a first assembly point 10a, 10b, for example by the intermediary of rivets symbolized by a mixed line 302, 402.
    On the side of the external face 154, the rear of the air intake lip 158 is fixed to the front part of the external panel 113 at a second assembly point 20a, 20b, for example by the intermediate rivets symbolized by a mixed line 304, 404.
    On the side of the inner face 152, the front reinforcement frame 160 is fixed inside the air intake lip 158 at a first fixing point 30a, 30b.
    On the side of the outer face 154, the front reinforcement frame 160 is fixed to the air intake lip 158 at a second fixing point 40a, 40b.
    Relative to the stop point 250 of the air intake lip 158, i.e. the point where the air speed is zero, i.e. the point of the lip air inlet 158 furthest forward, the length of the cord between said stopping point 250 and each fixing point 30a-b, 40a-b is between 1/3 and 1/6 of the total cord between the stopping point 250 and the assembly point 10a-b, 20a-b situated on the same side, that is to say on the side of the internal face 152 or on the side of the external face 154.
    Such a positioning of the front reinforcement frame 160 makes it possible to move the heat source away, that is to say the volume 206 filled with hot gas, from the acoustic panel 162 and from the exterior panel 113.
    The part of the air intake lip 158 between the fixing points 30a-b, 40a-b and the assembly points 10a-b, 20a-b constitutes a radiator which dissipates the heat and the acoustic panel 162 and the outer panel 113 is no longer impacted by any temperature increases.
    In the embodiment of FIG. 3, the attachment to the first attachment point 30a is provided by rivets symbolized by a mixed line 306, and the attachment to the second attachment point 40a is provided by rivets symbolized by a mixed line 308.
    In the embodiment of FIG. 4, the attachment to the first attachment point 30b is provided by welding, and the attachment to the second attachment point 40b is provided by welding. The first attachment point 30b and the second attachment point 40b constitute weld zones.
    In the embodiment of FIG. 4, the air intake lip 158 and the front reinforcement frame 160 may constitute a single piece produced in a single piece and single material, for example by 3D printing. The first attachment point 30b and the second attachment point 40b constitute monobloc and mono-material zones.
    Depending on the temperature of the hot gas, the air intake lip 158 and the front reinforcement frame 160 can be made of different materials, such as, for example, aluminum alloy.
    So that the air intake lip 158 and the front reinforcement frame 160 withstand very high temperatures, they are advantageously made of titanium alloy.
    According to a particular embodiment:
    - the length of the cord on the air intake lip 158 between the stop point 250 and the fixing point 30a-b of the inner face 152 is from 170 to 320 mm,
    - the length of the cord on the air intake lip 158 between the stop point 250 and the fixing point 40a-b of the outer face 154 is 150 to 250 mm,
    - the length of the cord on the air intake lip 158 between the fixing point
    30a-b of the inner face 152 and the first assembly point lOa-b of the inner face 152 is between 20 and 80 mm depending on the drop in temperature to be achieved,
    - the length of the cord on the air intake lip 158 between the fixing point
    40a-b of the outer face 154 and the second assembly point 20a-b of the outer face 154 is between 15 and 80 mm depending on the drop in temperature to be achieved.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1) Air intake structure (150, 350, 450) for an aircraft nacelle (104) (100), said air intake structure (150, 350, 450) comprising:
    - an air intake lip (158) with a U-shaped section open towards the rear and
    5 ensuring the sharing of air between an inner face (152) and an outer face (154) and having a stop point (250),
    - an acoustic panel (162) fixed to the rear of the air intake lip (158) on the side of the interior face (152) at the level of a first assembly point (10a-b),
    - an outer panel (113) fixed to the rear of the air intake lip (158) on the side
    10 of the outer face (154) at a second assembly point (20a-b),
    - a front reinforcement frame (160) placed inside the air intake lip (158) and fixed to the air intake lip (158), on the side of the interior face (152) at a first fixing point (30a-b) and on the side of the external face (154) at a second fixing point (40a-b),
    The air intake structure (150, 350, 450) being such that the length of the cord between said stop point (250) and each fixing point (30a-b, 40a-b) is between 1/3 and 1/6 of the total rope between the stopping point (250) and the joining point (10a-b, 20a-b) located on the same side.
    [2" id="c-fr-0002]
    2) Air intake structure (350) according to claim 1, characterized in that the
    20 fixing to the first fixing point (30a) and fixing to the second fixing point (40a) are ensured by rivets.
    [3" id="c-fr-0003]
    3) Air intake structure (450) according to claim 1, characterized in that the attachment to the first attachment point (30b) and the attachment to the second attachment point (40b) are provided by welding.
    25
    [4" id="c-fr-0004]
    4) Air intake structure (450) according to claim 1, characterized in that the fixing at the first fixing point (30b) and the fixing at the second fixing point (40b) are ensured by the fact that the lip air inlet (158) and the front reinforcement frame (160) constitute a single piece made in a single piece and single material.
    [5" id="c-fr-0005]
    5) Air intake structure (150, 350, 450) according to one of claims 1 to 4, characterized in that the air intake lip (158) and the front reinforcement frame (160) are made of titanium alloy.
    [6" id="c-fr-0006]
    6) Air intake structure (150, 350, 450) according to one of claims 1 to 5, 5 characterized in that:
    - the length of the cord on the air intake lip (158) between the stop point (250) and the fixing point (30a-b) of the inner face (152) is 170 to 320 mm ,
    - the length of the cord on the air intake lip (158) between the stop point (250) and the fixing point (40a-b) of the outer face (154) is 150 to 250 mm ,
    10 - the length of the cord on the air intake lip (158) between the fixing point (30a-b) of the interior face (152) and the first assembly point (10a-b) of the inner face (152) is between 20 and 80 mm,
    - the length of the cord on the air intake lip (158) between the fixing point (40a-b) of the external face (154) and the second assembly point (20a-b) of the face
    15 outer (154) is between 15 and 80 mm.
    [7" id="c-fr-0007]
    7) nacelle (104) for an aircraft engine (100), said nacelle (104) having an air intake structure (150, 350, 450) according to one of claims 1 to 6, a pipe d feed (208) which takes hot gas from the engine (202) and injects it into a volume (206) between the air intake lip (158) and the front reinforcement frame (160),
    20 a control unit (214), a pressure sensor (210) provided for measuring the pressure in the supply line (208) and a single valve (212) mounted on the supply line (208) and provided for alternately take an open position in which it lets hot gas pass through the supply line (208), or a closed position in which it does not let hot gas pass through the line
    25 supply (208), where the position of the valve (212) is controlled by the control unit (214) based on the pressure information that the control unit (214) receives from the pressure sensor (210 ).
    [8" id="c-fr-0008]
    8) Aircraft (100) comprising at least one nacelle (104) according to the preceding claim.
    PL. 1/2
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3060651A1|2018-06-22|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE
    EP0853192A1|1998-07-15|Thrust reverser with optimized cascade actuator position
    EP0898063A1|1999-02-24|Noise reducing attachment for a turbofan engine
    CA2564508A1|2006-02-16|Cooling device for the primary nozzle of a dual-flow turbojet engine
    CA2681931C|2015-09-15|Air intake arrangement for a vehicle, in particular an aircraft
    CA2732351A1|2010-02-04|Assembly of components connected by a device that maintains the integrity of the surface of one of the components
    EP2393712A1|2011-12-14|Suspension assembly for an aircraft turbojet engine
    EP2543864A2|2013-01-09|Aircraft propulsion assembly with a heat shield for thermal protection of a rear aerodynamic fairing of a pylon and a cooling method for the heat shield
    FR2890696A1|2007-03-16|TURBOMOTEUR WITH ATTENUATED JET NOISE
    FR2651020A1|1991-02-22|EXHAUST TUBE WITH INTEGRAL TRANSITION AND CONVERGENT SECTION
    EP3640139A1|2020-04-22|Aircraft engine nacelle equipped with an ice protection system
    FR2920137A1|2009-02-27|FIXING A STRUCTURE OF A TURBOJET NACELLE BY A REINFORCED KNIFE / GRIP BRIDGE
    CA2695626C|2015-03-31|Turboshaft engine with reduced noise emission for aircraft
    CA2991740A1|2017-01-26|Turbine engine exhaust casing with improved lifetime
    CA2866531A1|2013-09-26|Aircraft turbojet engine exhaust cone
    FR2990928A1|2013-11-29|Nacelle for gas turbine engine that is utilized for aircraft, has transverse partition arranged to be fixed with upstream support, and reinforcement element connecting transverse partition to downstream support
    EP3361071A1|2018-08-15|Air intake structure for an aircraft nacelle
    FR2964415A1|2012-03-09|HYPERSTATIC MOTOR SUSPENSION TRELLIS
    WO2019081864A1|2019-05-02|Propulsion unit for aircraft
    WO2007036520A2|2007-04-05|Engine mounting structure for an aircraft engine
    FR3011584A1|2015-04-10|EXTENSION OF INTERMEDIATE CASING
    EP3581781B1|2021-07-28|Propulsion system of an aircraft comprising a fixed interior structure having an evacuation slot
    FR2757570A1|1998-06-26|Thrust reverser for aircraft gas turbine engine
    EP3617490A1|2020-03-04|Air bleeding scoop for an aircraft
    FR2984280A1|2013-06-21|AIR INTAKE STRUCTURE FOR TURBOREACTOR NACELLE
    同族专利:
    公开号 | 公开日
    US10836503B2|2020-11-17|
    FR3060651B1|2020-11-06|
    US20180201387A1|2018-07-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4817756A|1985-08-26|1989-04-04|Aeronautic Development Corp. Ltd.|Quiet nacelle system and hush kit|
    EP1715160A1|2005-04-22|2006-10-25|Rohr, Inc.|Aircraft engine nacelle inlet having electrical ice protection system|
    FR2887518A1|2005-06-22|2006-12-29|Airbus France Sas|Jet aircraft engine nacelle has air intake de-icing and anti-icing system created by resistive heating elements embedded in electrical insulating material|
    WO2009136062A2|2008-04-10|2009-11-12|Airbus France|Acoustic treatment panel with integral connecting reinforcement|
    EP2366624A1|2010-03-18|2011-09-21|Airbus Opérations SAS|De-icing system comprising detection means for detecting an air leak in the hot air supply|
    FR3016159A1|2014-01-03|2015-07-10|Airbus Operations Sas|AIRCRAFT TURBO BURNER BOAT COMPRISING AN INCREASED RIGIDITY AIR INTAKE ASSEMBLY|FR3092871A1|2019-02-15|2020-08-21|Airbus Operations|PROCESS FOR ASSEMBLING AN AIR INLET OF A TURBOREACTOR of an aeroneF|US5683062A|1995-02-27|1997-11-04|General Electric Company|Aircraft anti-insect system|
    FR2813581B1|2000-09-06|2002-11-29|Aerospatiale Matra Airbus|AIR INTAKE COVER FOR REACTION ENGINE PROVIDED WITH DEFROSTING MEANS|
    US7588212B2|2003-07-08|2009-09-15|Rohr Inc.|Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip|
    US20100199629A1|2005-06-22|2010-08-12|Airbus France|Systeme d'anti givrage et de degivrage de nacelle de moteur d'aeronef a tapis resistif|
    US7923668B2|2006-02-24|2011-04-12|Rohr, Inc.|Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein|
    WO2010086560A2|2009-02-02|2010-08-05|Airbus Operations Sas|Aircraft nacelle including an optimised acoustic processing system|
    FR2954280B1|2009-12-18|2012-03-23|Airbus Operations Sas|AIR INTAKE OF AN AIRCRAFT NACELLE COMPRISING AN OPTIMIZED GEL TREATMENT|
    FR2954282B1|2009-12-22|2012-02-17|Airbus Operations Sas|NACELLE INCORPORATING A JUNCTION ELEMENT BETWEEN A LIP AND AN ACOUSTICAL ATTENUATION PANEL|
    US9534505B2|2012-07-23|2017-01-03|United Technologies Corporation|Integrated nacelle inlet and metallic fan containment case|
    FR3009278B1|2013-07-30|2016-12-23|Airbus Operations Sas|METHOD FOR REGULATING THE DEFROSTING OF AN AIRCRAFT ATTACHMENT EDGE AND DEVICE FOR IMPLEMENTING IT|
    US9764847B2|2013-10-18|2017-09-19|The Boeing Company|Anti-icing system for aircraft|
    US10837362B2|2016-10-12|2020-11-17|General Electric Company|Inlet cowl for a turbine engine|FR3060650B1|2016-12-20|2019-05-31|Airbus Operations|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE|
    US10870491B2|2017-07-20|2020-12-22|The Boeing Company|Eductor driven anti-ice system|
    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
    FR1662815|2016-12-20|
    FR1662815A|FR3060651B1|2016-12-20|2016-12-20|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE|FR1662815A| FR3060651B1|2016-12-20|2016-12-20|AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE|
    US15/847,207| US10836503B2|2016-12-20|2017-12-19|Air intake structure for an aircraft nacelle|
    [返回顶部]