• 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 nacelle (100) having a longitudinal axis X and comprising: - a frame (101), - two hinged covers (102a-b), each being rotatably mounted in the upper part of the frame (101) around an opening axis parallel to the longitudinal axis X between a closed position and an open position, - a sliding cover (104) which, in the closed position, is located between the free edges (103a-b) of the articulated hoods ( 102a-b), and sliding means arranged to ensure, in the open position, a displacement in rotation about the longitudinal axis X of the sliding cover (104). Such a nacelle thus has hoods whose size in the open position is reduced and whose dimensions are reduced compared to the hoods of the state of the art.
    公开号:FR3036382A1
    申请号:FR1554557
    申请日:2015-05-21
    公开日:2016-11-25
    发明作者:Olivier Pautis；Jerome Colmagro
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an aircraft nacelle comprising two covers mounted to rotate about an axis parallel to the longitudinal axis of the aircraft. nacelle, and an aircraft comprising at least one such nacelle. STATE OF THE PRIOR ART An aircraft comprises at least one nacelle in which is housed a motor, for example of the turbojet type, and which is suspended from a mast fixed under a wing of the aircraft. Conventionally, a nacelle for a turbojet engine is structured in three functional zones: the zone of the air inlet at the front, upstream of the aerodynamic flow, the zone of the fan cowls at the central part, which cover the crankcase of the engine blower, and the area of the thrust reversal system, which covers the turbojet turbine body at the rear, downstream of the aerodynamic flow. The area of the fan cowl of the nacelle comprises two hoods (fan cow in English) arranged on either side of the mast and which can be opened to allow maintenance of the engine. Each hood is articulated on hinges around an opening axis parallel to the longitudinal axis of the nacelle and disposed in the upper part of the hood. Each cover is thus movable between a closed position in which the cover is disposed in the extension of the outer surface of the nacelle so as to cover the fan casing and an open position, in which an operator can access the engine. The lower edges of the covers, which are located in the lower part of the nacelle, are substantially contiguous in the closed position and are held in this closed position by a locking system which keeps the two covers integral. Currently, the dimensions of the nacelle tend to increase, which also implies an increase in the dimensions of the hoods. However, when the 30 hoods are in the open position, it is necessary to maintain a safety distance between the hoods and the wing of the wing under which is installed the nacelle. Maintaining such a safety distance causes a limitation in the opening of the covers and therefore reduced accessibility for the operator. In addition, increasing the diameter of the nacelles tends to reduce the space between the bottom of the nacelles and the ground. Access to the locking system of the covers by the 5 operators is then difficult. In addition, the increase in the dimensions of the covers has repercussions on their manufacturing tolerances, their deformations in flight or on the need to strengthen the hinges. SUMMARY OF THE INVENTION An object of the present invention is to propose an aircraft nacelle which does not have the drawbacks of the prior art and which in particular has a hood rotatably mounted about the longitudinal axis of the nacelle and the hoods of reduced dimensions. For this purpose, is proposed a nacelle having a longitudinal axis X and 15 comprising: - a frame, - two hinged covers, each being rotatably mounted in the upper part of the frame about an axis of opening parallel to the axis longitudinal X between a closed position and an open position, 20 - a sliding cover which, in the closed position, is placed between the free edges of the hinged covers, and - sliding means arranged to ensure, in the open position, a rotational displacement around the longitudinal axis X of the sliding cowl. Such a nacelle thus has hoods whose footprint in the open position is reduced and whose dimensions are reduced compared to the hoods of the state of the art. Advantageously, the sliding means are two circular slide systems integral with the frame and one of which is disposed at the front portion of the sliding cover and the other is disposed at the rear portion of the sliding cover. Advantageously, each circular slide system has a C-shaped groove integral with the frame and one or more blocks integral with the sliding cover and movable in the groove. Advantageously, the nacelle further comprises, for each hinged cover, a locking system provided between the sliding cover and said hinged cover at the free edges of the covers to ensure the locking in the closed position of the sliding cover and the hinged cover between them. Advantageously, the nacelle comprises: an air intake zone at the front, upstream of the aerodynamic flow, an area of the thrust reversal system, at the rear, downstream of the aerodynamic flow. a central zone of fan cowls situated between said air inlet zone and said zone of the thrust reversal system, said two articulated cowls and said sliding cowl being situated in said central zone of fan cowls . The invention also proposes an aircraft comprising a mast under which is fixed a nacelle according to one of the preceding variants.
    [0002] 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 given in relation to the accompanying drawings, among which: FIG. 1 shows a side view of an aircraft having a nacelle according to the invention, FIG. 2 shows in perspective the nacelle according to the invention in the open position, and FIG. 3 shows a sectional view of the nacelle of FIG. 2 by a plane perpendicular to the longitudinal axis of the nacelle. DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows an aircraft 10 which conventionally comprises at least two pods 100, only one of which is seen in FIG. 1 and which is substantially cylindrical in shape. Each nacelle 100 is fixed under a mast 12 of said aircraft 10.
    [0003] In the description which follows, and by convention, X is the longitudinal axis of the aircraft 10 oriented positively in the direction of travel of the aircraft 10 and which is also the longitudinal axis of the nacelle 100. Y the transverse axis of 3036382 4 the aircraft which is horizontal when the aircraft is on the ground, and Z the vertical axis or vertical height when the aircraft is on the ground, these three directions X, Y and Z being orthogonal between they and forming an orthonormal landmark originating from the point O. The terms relating to a position are taken with reference to an aircraft 10 in the position of normal use of advancement as shown in FIG. 1. FIG. 2 shows the nacelle 100 which comprises a frame 101 which is fixed to the mast 12 and which supports the engine. The nacelle 100 has three functional zones: an air intake zone 110 at the front, upstream of the aerodynamic flow through the engine, a zone of the fan cowls at the central part and a zone of the reversal system 10. thrust 112 which covers the turbojet turbine body at the rear, downstream of the aerodynamic flow. In the central zone of the fan cowls, the nacelle 100 comprises cowls which cover the casing of the engine fan. More specifically, it comprises two hinged covers 102a and 102b, each being rotatably mounted on the frame 101 via hinges (302a-b, Fig. 3) around an opening axis parallel to the longitudinal axis X of the nacelle 100 and arranged in the upper part of the frame 101. The two hinged covers 102a-b and the two opening axes are arranged on either side of the mast 12. The two hinged covers 102a-b are arranged between the air intake zone 110 and the zone of the thrust reverser system 112.
    [0004] Each hinged cover 102a-b is thus movable between a closed position (FIG 3) in which the hinged cover 102a-b is disposed in the extension of the outer surface of the nacelle 100, here the envelope of the zone of air inlet 110 and the zone of the thrust reverser system 112, so as to cover the fan casing and an open position (FIG 2), in which the hinged cover 102 a-b is spaced from the chassis 101 and in which an operator can access the interior of the nacelle 100. The nacelle 100 also has a sliding cover 104 also arranged between the air intake zone 110 and the zone of the thrust reversal system 112, in the extension of the outer surface of the nacelle 100. The sliding cover 104 is rotatable on the frame 101 about the longitudinal axis X. To this end, the nacelle 100 has sliding means which are arranged to ensure a rotation in rotat around the longitudinal axis X of the sliding cowl 104 on the periphery of the nacelle 100 between the trailing edge of the air intake zone 110 and the leading edge of the zone of the thrust reverser system 112 when the covers 3036382 5 hinged 102a-b are in the open position. The angular extent of the sliding means determines the amount of displacement of the sliding cover 104. FIG. 3 shows the nacelle 100 when the covers 102a-b and 104 are in the closed position. The two articulated hoods 102a-b then close on the frame 101 and the sliding cowl 104 is positioned between the free edges 103a-b of the hinged covers 102a-b, that is to say here in the lower part of the nacelle 100. The angular extent of each cover 102a-b, 104 is such that in the closed position, the covers 102a-b and 104 are contiguous and completely cover the frame 101. The free edge 103a-b is the edge which is away in the open position and which is on the edge opposite the edge bearing the hinge 302a-b.
    [0005] To move to the open position, the two hinged covers 102a-b are raised and spaced from the frame 101 by rotation around the hinges 302a-b and the sliding cover 104 can then move freely around the frame 101 on one side or the other. Another of the nacelle 100. In the embodiment of the invention shown in FIG. 2, the sliding hood 104 has been moved to the starboard side of the platform 100, but it can likewise move on the port side. Thus, the nacelle 100 has three covers 102a-b and mobile 104 whose dimensions are reduced compared to those of the state of the art which compensates for the effects of enlargement of the nacelle 100. Thus, these covers allow better accessibility inside the nacelle 100, and easier manufacturing.
    [0006] In addition, these panels of reduced dimensions make it possible to limit the deformations in flight, which generate phenomena of scooping. They thus make it possible to reduce the drag and thus the overall consumption of the aircraft. The sliding means take the form of two circular slide systems 114 integral with the chassis 101 and one of which is disposed at the front portion 25 of the hood. sliding member 104 and the other of which is arranged at the rear part of the sliding cover 104. According to a particular embodiment, each circular slide system 114 has for example a C-shaped groove, or a dovetail groove, integral with the frame 101 and one or more pads integral with the sliding cover 104 and movable in the groove. Those skilled in the art can, however, without difficulty imagine other means of sliding. To ensure that the covers 102a-b and 104 are kept in the closed position, and thus the sliding hood 104 and each of the hinged covers 102a-b are locked together in the closed position, the nacelle 100 comprises, for each hinged cowl 102a-b, a locking system 304a-b provided between the sliding cover 104 and said hinged cover 102a-b at the free edges 103a-b of the covers 102a-b and 104. Each locking system 304a-b is represented symbolically on the Fig. 3 and it can take the form of any known locking system. Due to the angular extent of the sliding cover 104, each locking system 304a-b is more easily accessible than in the case of the state of the art. Indeed, each locking system 304a-b is on the side of the nacelle 100 and not under the nacelle. As shown in FIG. 2, the sliding cover 104 can move up to the vicinity of the hinges 302a-b of the hinged covers 102a-b.
    [0007] The particular arrangement described above also allows the opening of an articulated hood 102a-b independently of the opening of the other hinged hood 102b-a.
    权利要求:
    Claims (6)
    [0001]
    CLAIMS1) Nacelle (100) having a longitudinal axis X and comprising: - a frame (101), - two hinged covers (102a-b), each being rotatably mounted at the top of the frame (101) about an axis opening parallel to the longitudinal axis X between a closed position and an open position, - a sliding cover (104) which, in the closed position, is placed between the free edges (103a-b) of the hinged covers (102a-b ), and sliding means arranged to ensure, in the open position, a displacement in rotation about the longitudinal axis X of the sliding cover (104).
    [0002]
    2) nacelle (100) according to claim 1, characterized in that the sliding means are two circular slide systems (114) integral with the frame (101) and one of which is disposed at the front portion of the sliding cover (104) and the other is disposed at the rear portion of the sliding cover (104).
    [0003]
    3) Nacelle (100) according to claim 2, characterized in that each circular slide system (114) has a groove C integral with the frame (101) and one or more blocks integral with the sliding cover (104) and movable in the groove.
    [0004]
    4) nacelle (100) according to one of claims 1 to 3, characterized in that it further comprises, for each hinged cover (102a-b), a locking system (304a-b) provided between the sliding cover (104) and said hinged cover (102a-b) at the free edges (103a-b) of the covers (102a-b, 104) for locking in the closed position of the sliding cover (104) and the hinged cover (102a -b) between them.
    [0005]
    5) Nacelle (100) according to one of claims 1 to 4, characterized in that it comprises: - an air inlet zone (110) at the front, upstream of the aerodynamic flow, - a zone of the reverse thrust system (112), at the rear, downstream of the aerodynamic flow, - a central zone of fan cowls, located between said air intake zone (110) and said zone of the thrust reversal system (112), said two hinged cowlings (102a-b) and said sliding cowl (104) being located in said central zone of fan cowls.
    [0006]
    6) Aircraft comprising a mast (12) under which is fixed a nacelle (100) according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
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    CA2204589C|2003-09-30|Jet turbine engine thrust reverser employing doors fitted with deflector vanes
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    FR2618122A1|1989-01-20|Receptacle for airborne optical sighting system with large deflection in elevation
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    FR3063714A1|2018-09-14|AIRCRAFT NACELLE COMPRISING A ROTARY MONTE HOOD AROUND THE LONGITUDINAL AXIS OF THE NACELLE
    FR3081837A1|2019-12-06|AIRCRAFT TURBOMACHINE ASSEMBLY WITH ARTICULATED HOOD
    EP3620371A1|2020-03-11|Nacelle for an aircraft engine comprising means to prevent the deformation of hinged fan covers
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    WO2020157402A1|2020-08-06|Aircraft
    同族专利:
    公开号 | 公开日
    FR3036382B1|2017-06-16|
    EP3095706A1|2016-11-23|
    US20160340024A1|2016-11-24|
    EP3095706B1|2018-04-18|
    US10144500B2|2018-12-04|
    CN106167099A|2016-11-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2890378A1|2005-09-08|2007-03-09|Airbus France Sas|NACELLE HOOD FOR TURBOJET AND NACELLE COMPRISING AT LEAST ONE SUCH HOOD.|
    US20090272842A1|2008-05-05|2009-11-05|Airbus France|Device to handle and lock a cover of an aircraft nacelle|
    FR2933071A1|2008-06-25|2010-01-01|Snecma|AIRCRAFT PROPELLANT POWER UNIT CAPABILITY NACELLE DEVICE|
    FR3005453A1|2013-05-13|2014-11-14|Airbus Operations Sas|AIRCRAFT TURBOKET AIRCRAFT|FR3063714A1|2017-03-07|2018-09-14|Airbus Operations|AIRCRAFT NACELLE COMPRISING A ROTARY MONTE HOOD AROUND THE LONGITUDINAL AXIS OF THE NACELLE|
    FR3079500A1|2018-03-29|2019-10-04|Airbus Operations|AIRCRAFT NACELLE WITH A ROTATING BLOWER HOOD INTEGRATING AN ACCESS HATCH|GB2182724B|1985-10-08|1988-12-07|Rolls Royce|Gas turbine engine thrust reverser|
    US5259576A|1992-05-18|1993-11-09|Howard D U|External sliding aircraft door|
    US5350136A|1993-05-14|1994-09-27|United Technologies Corporation|Nacelle arrangement|
    FR2901245B1|2006-05-22|2008-12-26|Airbus France Sas|DEVICE FOR JOINING A DOOR OF AN AIRCRAFT NACELLE AND NACELLE EQUIPPED WITH SAID ARTICULATION DEVICE|
    FR2960855A1|2010-06-03|2011-12-09|Aircelle Sa|NACELLE FOR TURBOJETACTOR WITH DEVICE FOR RECOVERING CIRCUMFERENTIAL EFFORTS|
    FR3024435B1|2014-07-31|2016-08-26|Airbus Operations Sas|GUIDED FOLDING BLOWER HOOD, FOR AIRCRAFT ENGINE ASSEMBLY|FR3047973B1|2016-02-23|2018-03-09|Airbus Operations|AIRCRAFT ENGINE ASSEMBLY, COMPRISING A MOTOR ATTACHING DEVICE EQUIPPED WITH STRUCTURAL MOBILE HOOKS CONNECTED TO THE CENTRAL CABIN|
    US10752371B2|2016-09-30|2020-08-25|General Electric Company|Translating nacelle wall for an aircraft tail mounted fan section|
    US10710736B2|2017-10-30|2020-07-14|The Boeing Company|Latch indication system and method for a fan cowl of an air vehicle|
    US11142326B2|2018-07-27|2021-10-12|The Boeing Company|Mechanism for indicating position of a latch mechanism for an aircraft nacelle|
    法律状态:
    2016-05-20| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Search report ready|Effective date: 20161125 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 3 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554557A|FR3036382B1|2015-05-21|2015-05-21|AIRCRAFT NACELLE COMPRISING AT LEAST ONE ROTARY MONTE HOOD AROUND THE LACQUID AXIS OF THE NACELLE|FR1554557A| FR3036382B1|2015-05-21|2015-05-21|AIRCRAFT NACELLE COMPRISING AT LEAST ONE ROTARY MONTE HOOD AROUND THE LACQUID AXIS OF THE NACELLE|
    EP16170227.9A| EP3095706B1|2015-05-21|2016-05-18|Aircraft nacelle comprising at least one cover mounted rotatably about the longitudinal axis of the nacelle|
    US15/160,579| US10144500B2|2015-05-21|2016-05-20|Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle|
    CN201610549743.3A| CN106167099A|2015-05-21|2016-05-20|Aircraft nacelle including two fan guard doors|
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