• 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:
    In order to reduce the risks of opening the mobile platform covers, the invention provides a nacelle (11) for an aircraft engine assembly (1) comprising a fixed nacelle structure (42) and at least one movable cowl ( 38) articulated on the fixed structure (42), the cover (38) being hinged at its front end (38a) on the fixed structure so that when closing the movable cover, a rear end (38b) of the cover moves backwards and radially inwards.
    公开号:FR3033545A1
    申请号:FR1552046
    申请日:2015-03-12
    公开日:2016-09-16
    发明作者:Olivier Pautis；Jerome Colmagro
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to an aircraft engine assembly, comprising a turbomachine and a nacelle arranged around the turbomachine. DESCRIPTION OF THE PREFERRED EMBODIMENT The invention relates more specifically to the implementation of movable nacelle hoods allowing access to the equipment of the engine assembly, for carrying out maintenance operations. The invention is preferably applicable to turbomachines comprising a pair of non-careened contrarotating propellers, these turbomachines being also called "Open Rotor", or "CROR" (English "Contra Rotative Open Rotor"). Even more preferentially, the invention applies to Open Rotor turbomachines of "Pusher" type configuration, in which the receiver is arranged backwards relative to the gas generator. The application of the invention to the more traditional turbojet engines and turboprop engines is also envisaged, without departing from the scope of the invention. STATE OF THE PRIOR ART On aircraft, each turbine engine is usually surrounded by a nacelle, having a substantially aerodynamic function. The nacelle is conventionally equipped with movable covers allowing, when in the open position, access to equipment arranged around a casing of the turbomachine. Access to this equipment allows for ground maintenance operations.
    [0002] The movable covers are usually articulated along axes substantially parallel to the longitudinal axis of the turbomachine. They are thus articulated at their upper end, and their free end is equipped with locking means in the closed position. When opening a nacelle cover, its free end departs radially from the longitudinal axis of the turbomachine, while during closure of the cover, its free end approaches radially to the same longitudinal axis. . This conventional solution gives overall satisfaction. Nevertheless, it may be judicious to improve it, in particular so as to reduce the risks of opening the hoods in flight, under the effect of external aerodynamic loads applied to these hoods. This need is even more pronounced when the turbomachine is of the Open Rotor type and Pusher configuration, that is to say with the receiver arranged at the rear. Indeed, in case of opening of a mobile cowl in flight, it is likely to detach and therefore come to impact the blades of the contrarotative propellers 10 further back. This risk of deterioration of the blades also exists vis-à-vis debris may become detached from the motor assembly, following the opening of the movable covers. SUMMARY OF THE INVENTION It is therefore an object of the invention to provide an aircraft assembly which at least partially overcomes the above-mentioned problems encountered in the prior art solutions. For this purpose, the subject of the invention is a nacelle for an aircraft engine assembly comprising a fixed nacelle structure and at least one movable nacelle cowl articulated on said fixed structure, said movable cowl being hinged at its front end. on the fixed structure so that when closing the movable cover, a rear end of this cover moves backwards and radially inwards. The implementation of the movable nacelle hood breaks with conventional solutions, and limits the risk of opening the hood in flight. Indeed, thanks to the articulation of the movable cowl at its front end, external aerodynamic loads applying to this cowling advantageously tend to force it in its closed position. In addition, the reduction of the risk of opening the cover reduces the risk of detachment of the hood, as well as a reduction in the risk of flying debris may become detached from the engine assembly, following the opening of the hood. a mobile bonnet of nacelle. This advantage is particularly interesting for turbomachines of the Open Rotor type and Pusher configuration, because it reduces the risk of damage to the blades of the counter-rotating propellers not keeled. Nevertheless, the invention applies to all types of aircraft turbomachines such as turbojets and turboprops, without departing from the scope of the invention. The invention preferably has at least one of the following optional features, taken singly or in combination. The nacelle comprises a number of movable covers between two and four, said movable covers being distributed around a longitudinal axis of the nacelle 10 and succeeding one another in a circumferential direction of the nacelle, each of said movable covers being articulated at its front end. on the fixed structure so that when closing the movable cover, a rear end of this cover moves backwards and radially inwards. Said movable cowl is articulated at its front end along a hinge axis 15 forming a transverse plane of the nacelle. Nevertheless, the hinge axis could be inclined relative to this transverse plane, without departing from the scope of the invention. Preferably, the hinge axis is oriented substantially tangentially to the nacelle.
    [0003] Said moving cowl has an axial length of between 30 and 90% of the total axial length of the nacelle. The invention also relates to a motor assembly for an aircraft comprising a turbomachine and a nacelle as described above, arranged around said turbomachine.
    [0004] Preferably, the turbomachine comprises a gas generator as well as a receiver with a pair of counter-rotating non-careened propellers, said receiver being preferably arranged rearwardly with respect to said gas generator. Preferably, said movable cowl covers at least a portion of said gas generator.
    [0005] The invention finally relates to an aircraft comprising at least one such engine assembly, said assembly being preferably reported in the rear part of the fuselage. Alternatively, it can be attached to a wing of the aircraft or a more advanced portion of its fuselage, without departing from the scope of the invention.
    [0006] Other advantages and features of the invention will become apparent from the detailed non-limiting description below. BRIEF DESCRIPTION OF THE DRAWINGS This description will be made with reference to the appended drawings among which; FIG. 1 represents a schematic perspective view of an aircraft comprising motor assemblies according to the invention; FIG. 2 represents a perspective view of an engine assembly according to a first preferred embodiment of the invention; Figure 3 is a longitudinal sectional view of the motor assembly shown in Figure 2; - Figure 4 is a view similar to that of Figure 2, with the movable covers of the nacelle shown in the open position; FIG. 4a shows a cross-sectional view of the motor assembly taken along the line IVa-IVa of FIG. 3; FIG. 5 is a view similar to that of FIG. 4, with the assembly being according to a second preferred embodiment of the invention; and - Figure 5a shows a cross sectional view of the motor assembly, according to the second preferred embodiment. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS Referring firstly to FIG. 1, there is shown an aircraft 100 comprising one or more engine units 1 according to the invention. More specifically, the aircraft comprises two sets 1 each reported in the rear part of a fuselage 102 of this aircraft. The fixing of each engine assembly 1 on the fuselage 102 is carried out in a conventional manner, using an attachment pole 104 or EMS (Engine Mounting Structure). Each engine assembly 1 comprises a turbomachine 10 and a nacelle 11 surrounding a portion of the turbomachine.
    [0007] As will be described with reference to FIGS. 2 and 3, the turbine engine 10 is of the Open Rotor type in Pusher mode, that is to say that it comprises a gas generator and a doublet receiver. non-keeled counter-rotating propellers, this receiver being arranged backward with respect to the gas generator. Throughout the following description, by convention, the direction X 10 corresponds to the longitudinal direction of the motor assembly 1, which is also comparable to the longitudinal direction of the turbomachine 10 and this set 1. This direction X is parallel to a longitudinal axis 5 of the turbomachine 10. On the other hand, the direction Y corresponds to the direction transversely oriented relative to the motor assembly 1 and also comparable to the transverse direction of the turbomachine 10, 15 while the direction Z corresponds to the vertical direction or height. These three directions X, Y and Z are orthogonal to each other and form a direct trihedron. On the other hand, the terms "front" and "rear" are to be considered in relation to a direction of advancement of the aircraft encountered following the thrust exerted by the turbomachines 10, this advancement direction being represented schematically by the boom 19. Overall, the turbomachine 10 comprises from front to rear a low pressure compressor 10, a high pressure compressor 12, a combustion chamber 14, a high pressure turbine 16 and a low pressure turbine 18. The compressor Low pressure 10 and the low pressure turbine 18 are connected by a low pressure shaft 20, while the high pressure compressor 12 and the high pressure turbine 16 are connected by a high pressure shaft 22 to form together a gas generator 24. All these elements are surrounded by a motor housing 26 centered on the axis 5. Downstream of the low-pressure turbine 18, there is provided a receiver 30 of the type with a pair of counter-rotating propellers, namely, a front propeller 32 and a rear propeller 3033545 6 34. Although this has not been shown, the propellers are driven by a power-free turbine or by an epicyclic gearbox. At the front of the receiver 30, the turbomachine 10 is surrounded by the nacelle 11 which comprises an air inlet 36, extended towards the rear by mobile covers 38 whose implantation is specific to the invention. More generally, the nacelle 11 comprises a fixed structure 42 of which the air inlet 36 is part. The fixed structure 42 also comprises a support 40 for air inlet 36, connecting the latter to the engine casing 26, at the right or in the vicinity of the low-pressure compressor 10. This support 40 takes for example the form of an annular structure centered on the axis 5, this structure being able to be a so-called "strong frame" frame. The movable hoods 38 have the particularity of being articulated at their front end 38a on the fixed structure 42, for example on the annular structure 40. The articulation is effected by means of conventional hinges 46, or by means of similar elements. Each moving cowl 38 extends here from the air inlet 36 to the receiver 30, that is to say over an axial length "La" of between 30 and 90% of the total axial length "Lt" of the nacelle, and more preferably close to 70% of this total axial length. Each cover 38 thus covers the gas generator 24, but also preferably all the elements of the turbomachine contained in the casing 26. The movable covers 38 can thus extend downstream to the receiver 30, or although one or more fixed covers provide the aerodynamic junction between the movable covers 38 and the same receiver 30, in the direction X. In other words, the movable covers 38 extend, in the direction X X, the entrance air 36 to the receiver 30 over the entire aerodynamic surface between these two elements 36, 30, that is to say over the entire axial length and over the entire circumference of this aerodynamic surface. Alternatively, the movable hoods 38 extend, in the direction X, from the air inlet 36 to the receiver 30 but only on a portion of the aerodynamic surface 30 between these two elements 36, 30. that is, they extend over part of the length and / or part of the circumference of this aerodynamic surface. The additional surface not formed by the movable covers 38 is then provided by fixed covers positioned between the movable covers 38 and the structure of the receiver 30 to ensure aerodynamic continuity in the X direction, or between two movable covers 38 for ensure aerodynamic continuity in the circumferential direction. In addition, rather than providing only one annular row of movable covers 38, it could for example be provided two rows of annular succession in the direction X. In other words, it amounts to segmenting the movable covers 10 in the direction X. An annular space 50 is defined between the crankcase 26 and the inner surface of the movable hoods 38. This space 50 is dedicated to housing equipment, shown schematically at the reference 52 in Figure 3. The opening the covers 38 provides access to these equipment, for performing maintenance operations on the ground. Apart from the maintenance operations, each movable cowl 38 is closed via its rear end 38b, by means of locking means 39, for example intended to cooperate with the rear part of the crankcase 26. Here again, these locking means 39 are conventional and will not be further described. Referring to Figures 3, 4 and 4a, it is noted that in this first preferred embodiment, there are provided two movable covers 38, each extending over an angular sector of about 180 °. The two hoods 38 in the form of half-shells are arranged to form an upper cover and a lower cover, the interface between them forming part of a median plane XY of the assembly 1. It is noted that even if not provided in the described embodiment, the stationary structure of the nacelle could comprise support members extending longitudinally towards the receiver 30, and on which the hoods 38 could rest in the closed position. Each movable cover 38 is articulated at its front end 38a, so that when closed, a rear end 38b of this cover moves rearwardly and radially inwards. To do this, it is preferably done in 3033545 8 so that the hinge axis 60 of each cover 38 is inscribed in the transverse sectional plane of Figure 4a, with a tangential orientation to the nacelle. In this preferred configuration, to move from the open position of Figure 4 to the closed position of Figure 3 and vice versa, each movable cowl 38 moves in a longitudinal plane XZ. Other directions of displacement could of course be envisaged, in particular non-longitudinal directions, but always so as to ensure that during closure, the rear end 38b of the cover moves backwards and radially towards the inside. This makes it possible to ensure that the external aerodynamic loads applied to the hood force the latter towards its closed position, thus reducing the risks of opening and detachment in flight. In the second embodiment shown in FIGS. 5 and 5a, the only change lies in the number of movable covers 38 in the annular row, these covers being here four in number, each extending over an angular sector of the order of 90 °. In this configuration, to move from the open position of Figure 5 to the closed position of Figure 5a and vice versa, each movable cowl 38 moves in a longitudinal plane corresponding to a median plane of the cowl concerned. Other embodiments may be envisaged with a different number of mobile covers, for example eight covers. Of course, various modifications can be made by those skilled in the art to the engine assemblies 1 for aircraft which have just been described, by way of non-limiting examples only. In particular, the invention can be applied to other types of aircraft turbomachines such as turbojet turbofan engines, also called "turbofan". In this case, the hoods concerned are preferably the fan cowls, arranged axially between the air inlet and the thrust reverser covers 25. 30
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Nacelle (11) for an aircraft engine assembly (1) comprising a fixed nacelle structure (42) and at least one movable nacelle cover (38) hinged to said fixed structure (42), characterized in that said hood mobile (38) is articulated at its front end (38a) on the fixed structure so that when closing the movable cowl, a rear end (38b) of this cowl moves backwards and radially inwards .
    [0002]
    2. Nacelle according to claim 1, characterized in that it comprises a number of movable covers (38) between two and four, said movable covers being distributed around a longitudinal axis (5) of the nacelle and succeeding each other. a circumferential direction of the nacelle, and in that each of said movable hoods (38) is articulated at its front end (38a) on the fixed structure (42) so that when closing the movable hood, a rear end ( 38b) of this hood moves backwards and radially inwards.
    [0003]
    3. Nacelle according to claim 1 or claim 2, characterized in that said movable cowl (38) is articulated at its front end (38a) along a hinge axis (60) forming a transverse plane of the nacelle .
    [0004]
    4. Nacelle according to any one of the preceding claims, characterized in that said movable cowl (38) is articulated at its front end (38a) along a hinge axis (60) oriented substantially tangentially to the nacelle.
    [0005]
    5. Nacelle according to any one of the preceding claims, characterized in that said movable cowl (38) has an axial length (La) of between 30 and 90% of the total axial length (Lt) of the nacelle. 3033545 10
    [0006]
    6. Engine assembly (1) for aircraft comprising a turbomachine (10) and a nacelle (11) according to any one of the preceding claims, arranged around said turbomachine (10). 5
    [0007]
    7. Engine assembly according to the preceding claim, characterized in that the turbomachine (10) comprises a gas generator (24) and a receiver (30) doublet non-keeled contrarotating propellers, said receiver (30) being preferably arranged rearwardly with respect to said gas generator (24). 10
    [0008]
    8. Engine assembly according to the preceding claim, characterized in that said movable cowl (38) covers at least a portion of said gas generator (24).
    [0009]
    9. Aircraft (100) comprising at least one engine assembly (1) according to any one of claims 6 to 8.
    [0010]
    10. Aircraft according to claim 9, characterized in that the engine assembly (1) is attached to the rear part of a fuselage of the aircraft. 15 20
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    引用文献:
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    法律状态:
    2016-03-21| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-16| PLSC| Publication of the preliminary search report|Effective date: 20160916 |
    2017-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552046|2015-03-12|
    FR1552046A|FR3033545B1|2015-03-12|2015-03-12|NACELLE FOR AIRCRAFT ENGINE ASSEMBLY COMPRISING AT LEAST ONE ARTICULATED NACELLE COVER AT ITS FRONT END|FR1552046A| FR3033545B1|2015-03-12|2015-03-12|NACELLE FOR AIRCRAFT ENGINE ASSEMBLY COMPRISING AT LEAST ONE ARTICULATED NACELLE COVER AT ITS FRONT END|
    US15/067,854| US10232930B2|2015-03-12|2016-03-11|Nacelle for an aircraft engine assembly comprising at least one jointed nacelle cowling at its front end|
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