• 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 aerodynamic fairing comprising at least one subassembly (30a to 30g), each subassembly having a frame (32) oriented transversely to the longitudinal axis (X) of the fairing and a floor portion provided with an inner face (71), through which the floor portion is fixed to the frame. The fairing further comprises side panels (44) fixed to the frame and each extending substantially along the longitudinal axis (X) of the shroud (30) on either side of a plane of symmetry (P) of the fairing . According to the invention, the floor portions (34) of the subassemblies are not mechanically connected to one another via rigid links. Thus, the division of the floor (31) into a distinct portion (34) reduces the longitudinal thermomechanical stresses exerted by the expansion of the floor (31) under the effect of the primary hot flow of the turbojet engine.
    公开号:FR3013679A1
    申请号:FR1361556
    申请日:2013-11-25
    公开日:2015-05-29
    发明作者:Francois Peyruseigt；Thierry Gaches；Delphine Chamaillard；Nicolas Voyer；Mathieu Kaleta
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an aerodynamic fairing of the rear part of an aircraft mast, also referred to in English as "aft pylon fairing" or APF. Such an aerodynamic fairing is known from US 4712750. In this document, the aerodynamic fairing has the shape of a box comprising two side panels assembled together by transverse frames or stiffening transverse internal ribs spaced from each other along the longitudinal axis of the fairing, and a thermal protection floor fixed on the one hand to the side panels and on the other hand transverse inner ribs in contact with which the floor is located. In the position of use, such a fairing is subjected to very high temperatures from the powertrain of the aircraft. These temperatures generate deformations by thermal expansion of the fairing, thus disturbing its aerodynamic qualities. In particular, the thermal protection floor is subjected to a primary flow of the turbine engine of high temperature (of the order of 600 ° C) while the side panels are subjected to a secondary flow of the turbine engine of relatively low temperature (from the order of 150 ° C) relative to that of the primary flow. These temperature differences generate strong thermomechanical stresses on the box, which can eventually deform it. The invention aims to remedy at least partially this disadvantage. The object of the invention is thus an aerodynamic fairing of a turbine engine mast, said fairing having the shape of an open box extending along a longitudinal axis and comprising a first and a second side panel substantially parallel to the longitudinal axis and distributed on either side of a plane of symmetry of said fairing, the aerodynamic fairing comprising at least two subsets arranged consecutively along the longitudinal axis and separated from each other by a interstice, each subassembly comprising a frame oriented transversely to the longitudinal axis and a floor portion extending along the longitudinal axis, each frame having, in the position of use, an upper edge fixed to the mast, a lower edge fixed to an inner face of the floor portion (34) of the subassembly, and a first and a second side edge on which the first and second side panels are respectively fixed. two portions of directly consecutive floors along the longitudinal axis are spaced a distance of between 0.1 mm and 5 cm (these two values being included).
    [0002] Advantageously, a lamella is fixed on the internal face of a floor portion of a first subset, said lamella covering a gap between the first subset and a second subset directly consecutive to the first subset. Advantageously, each side panel is formed of several portions of side panels fixedly attached to each other.
    [0003] Preferably, at least one floor portion comprises a stiffener extending transversely to the longitudinal axis. Other advantages and features of the invention will become apparent in the detailed non-limiting description below. This description will be made with reference to the accompanying drawings in which: - Figure 1 is a schematic side view of a wing provided with an engine mast and an aerodynamic fairing located in the rear portion of the engine mast to protect the wing hot gases ejected by the powertrain; FIG. 2 is a diagrammatic perspective view of the rear aerodynamic fairing according to one embodiment of the invention illustrated in FIG. 1, in which the rear aerodynamic fairing is formed of subassembled rainers; FIG. 3 is a view on a larger scale of a subassembly of FIG. 2 according to an alternative embodiment of the invention; and - Figure 4 is a cross-sectional view along the line IV-IV; aerodynamic fairing shown in Figure 2.
    [0004] Referring to Figure 1, there is shown a powertrain 1 attached to a wing 2 of an aircraft. The powertrain comprises a mast 4 and a turbine engine 6, for example a turbojet engine, attached to the wing 2 via the mast 4. The mast 4 comprises in known manner a rigid structure 8, also called primary structure, allowing to support, by known means, the turbojet engine 6.
    [0005] In addition, the mast 4 comprises secondary structures of the fairing type. Among the secondary structures of the mast 4 are a front aerodynamic structure 24, a rear aerodynamic structure 26, and a rear aerodynamic fairing 30, also called APF or heat shield. 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 turbojet engine 6, this direction being represented schematically by the arrow 7. By convention, it is called X the longitudinal axis of the rear aerodynamic fairing 30. On the other hand, we call Y the axis oriented transversely with respect to the turbojet engine 6 and the rear aerodynamic fairing, and Z the vertical axis or height, these three axes X, Y and Z being orthogonal to each other.
    [0006] As illustrated in FIG. 2, the rear aerodynamic fairing 30 takes the general shape of a box, for example open towards the top, comprising in particular a floor 31 extending along the longitudinal axis X and two spaced lateral panels. and parallel to each other forming the two lateral sides (along the longitudinal axis X) of the box. According to the invention, the rear aerodynamic fairing 30 is formed by at least two consecutive subsets in the longitudinal direction X. In the example illustrated in Figure 2, the rear aerodynamic fairing comprises seven subassemblies 30a to 30g. Each subassembly comprises a floor portion 34 and a frame 32. There are as many separate subassemblies as necessary to form the rear aerodynamic fairing 30 in desired dimensions, the different floor portions 34 succeeding one another according to the invention. X axis form the floor 31 of the box. According to the invention, two consecutive subsets are separated from one another so that a gap 35 (represented by thick lines in FIGS. 2 and 3 for greater visibility, between two floor portions 34 directly consecutive along the longitudinal axis X) having a dimension along the X axis between 0.1 mm and 5 cm (these two values being included).
    [0007] Note that as shown in Figure 2, the rear aerodynamic fairing 30 is not plane in the XZ plane, and has substantially an arrow shape (the tip is facing rearward) in the XY plane. Indeed, the box is shaped so that the rear aerodynamic fairing 30 takes the form of the mast 4 on which it is fixed. The rear aerodynamic fairing 30 is closed by a frame at its front end, and at its rear end it is closed by a floor portion 34 inclined in the YZ plane. Referring to Figure 3, each floor portion 34 is provided with an inner face 71 and an outer face 70 opposite to the inner face 71, the outer face being intended to be matched by the primary flow 36. In order to to withstand the thermal stresses, a floor portion 34 is preferably made of Inconel®, or a titanium alloy. Each frame 32, shown more particularly in Figures 3 and 4, is in the form of a structural panel having four edges and extends in a YZ plane transverse to the box. In the example shown in the figures attached to the present description, the frame 32 has substantially the shape of an isosceles trapezoid in the YZ plane. The two side edges 32b of the frame 32 are intended to each accommodate a side panel 44 as will be described in detail below. The upper edge 32a of some frames 32 (in the case where only certain frames are attached to mast structures), or all frames 32 (in the case where all frames are attached to mast structures), is it is arranged to conform to another structure of the mast 4, on which it is fixed, namely, as in the example illustrated in Figure 1, the rear aerodynamic structure 26 or the rigid structure 8. The lower edge 32c of the frame of a subassembly is attached to the inner face 71 of the floor portion 34 of the same subassembly, for example by splicing. The lower edge 32c of the frame 32 conforms to the floor portion 34 and therefore has, as illustrated in FIG. 4 in a cross section of the rear aerodynamic fairing 30, a curved shape opening outwards with respect to the aerodynamic fairing. 30. In order to withstand thermal stresses, a frame 32 is preferably made of Inconel®, or an equivalent titanium alloy.
    [0008] Referring more particularly to Figures 2 and 4, each side panel 44 of the rear aerodynamic fairing 30 extends substantially in the longitudinal plane XZ and the two side panels 44 are distributed on either side of a plane of symmetry P of the caisson. Each side panel 44 is fixedly mounted to the side edges 32b (located on the same side of the plane P) frames 32 successive. The side panels 44 are fixed to the frames 32 by screwing, possibly completed with a welding. In use, the side panels 44 are designed to be matched externally by the secondary flow 38. The side panels 44 are, for example, made of titanium and have a thickness of the order of 1 mm to 7 mm. In the example shown in Figure 2, the side panels 44 extend, each one piece from the front to the rear of the rear aerodynamic fairing 30. In this configuration, the panels 44 can stiffen the fairing rear aerodynamic 30 since they are attached to each of the frames 32 of the shroud 30. According to the invention, the floor portions 34 of the subassemblies 30a to 30g, are not mechanically connected directly to each other via rigid links. When the turbojet engine 6 is running, the rear aerodynamic fairing 30 provides for the formation of a thermal barrier serving to protect the rigid structure 8, the aerodynamic structure 26 and the wing 2 of the aircraft from the heat released by the primary stream 36, and ensures the formation of a thermal continuity between the output of the turbojet engine 6 and the mast 4.
    [0009] According to the invention, the division of the floor 31 into a distinct portion 34 makes it possible to reduce the longitudinal thermomechanical stresses exerted by the expansion of the floor 31 under the effect of the primary hot flow 36 of the turbojet engine. Indeed, the floor 31 according to the invention has a high mechanical strength, because there is a longitudinal mechanical cut between two consecutive floor portions 34. Each floor portion 34 therefore has a thermal expansion of its own, which contributes to further decrease the thermomechanical stresses that the rear aerodynamic fairing 30 undergoes. The floor 31 being formed by a plurality of portions 34 along its length, the displacement of the portions due to thermal effects are lower and therefore generate lower stresses than in the case of a box formed in one piece.
    [0010] Referring to Figure 3, and in a first variant of the embodiment just described, a floor portion 34 of a subassembly 30a to 30g comprises a stiffener 39 in the form of a profile metal, for example titanium, extending transversely to the floor portion 34. The metal section is fixed, for example by screwing, on the inner face 71 of the floor portion 34 at the gap 35 between two sub -sets. Note that in Figure 3, the frame 32 of a floor portion is attached to the front of the floor portion 34 while the stiffener 39 is located at the rear of the floor portion 34. The stiffener 39 reinforces the portion of the floor 34 which is subjected to significant vibrational stresses when the turbine engine 6 operates. The stiffener 39 also increases the rigidity of the floor portion 34 to better withstand the mechanical stresses. A stiffener 39 also provides vibratory stability to the floor portion 34 to which it is attached. Since a stiffener 39 is connected only to a floor portion 34, it follows the expansion of the latter without causing additional thermomechanical stresses on the rear aerodynamic fairing 30.
    [0011] Preferably, the stiffener 39 extends over the entire width (i.e., the dimension in the YZ plane) of a floor portion 34 and all the floor portions are provided with such a stiffener.
    [0012] In a second variant of the invention, in order to prevent the primary flow 36 of very high temperature from rising and spreading in the interstices 35 between two successive floor portions 34 along the longitudinal axis X, the thermal protection floor 31 is sealed, via lamellae 37 (a lamella is shown in FIG. 3) arranged so as to cover the gap 35 between two consecutive portions of floors 34 along the longitudinal axis X in order to guide the primary air flow 36 along the external face 70 of the floor portions 34. The plate 37 which covers the gap between two consecutive floor portions 34 is for example a flexible metal strip (for example Inconel ()) fixed on the inner face 71 , for example by screwing or welding, to a floor portion (the most forward portion in the example described in Figure 3) and which extends to the other floor portion 34 so as to cover the floor. 'interstic e between the two consecutive floor portions 34. As the strip is not fixed to the other floor portion 34, the free thermal expansion of the two floor portions 34 is therefore not impeded.
    [0013] In the figures accompanying the description above, each frame 32 has been shown as a solid panel. It goes without saying that without departing from the scope of the present invention, a frame 32 may also have a hollow shape so as to reduce the weight of the rear aerodynamic box 30 equipped with such frames.
    权利要求:
    Claims (4)
    [0001]
    REVENDICATIONS1. Aerodynamic fairing (30) of a turbine engine mast (4) (6), said box-shaped fairing extending along a longitudinal axis (X) and comprising first and second panels lateral section (44) substantially parallel to the longitudinal axis (X) and distributed on either side of a plane of symmetry (P) of said fairing, characterized in that the aerodynamic fairing (30) comprises at least two sub-elements. assemblies (30a-g) arranged consecutively along the longitudinal axis (X) and separated from each other by a gap (35), each subassembly comprising a frame (32) oriented transverse to the longitudinal axis and a portion floor (34) extending along the longitudinal axis, each frame (32) having, in use position, an upper edge (32a), a lower edge (32c) attached to an inner face (71) of the floor portion (34) of the subassembly, and first and second side edges (32b) to which the first and the second side panel (44).
    [0002]
    2. Aerodynamic fairing (30) according to claim 1, characterized in that two directly consecutive floor portions along the longitudinal axis (X) are spaced apart by a distance of between 0.1 mm and 5 cm.
    [0003]
    3. Aerodynamic fairing (30) according to any one of claims 1 to 2, characterized in that a plate (37) is fixed on the inner face (71) of a floor portion (34) of a first subassembly (30a), said lamella covering a gap (35) between the first subassembly (30a) and a second subassembly (30b) directly consecutive to the first subassembly.
    [0004]
    4. Aerodynamic fairing (30) according to any one of claims 1 to 3, characterized in that at least one floor portion (34) comprises a stiffener (39) extending transversely to the longitudinal axis (X).
    类似技术:
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    CA2576100A1|2006-08-31|Turbojet pylon for aircraft
    FR3013679A1|2015-05-29|AERODYNAMIC FAIRING DIVIDED IN SUBPARTS
    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
    FR2873986A1|2006-02-10|AIRCRAFT ENGINE ASSEMBLY
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    FR3000721A1|2014-07-11|AIRCRAFT PROPULSIVE ASSEMBLY COMPRISING AERODYNAMIC AERODYNAMIC REAR FITTING FOR SIDE WALLS FOR THE INJECTION OF FRESH AIR ALONG A THERMAL PROTECTION FLOOR
    FR2960519A1|2011-12-02|Aerodynamic fairing i.e. rear lower aerodynamic fairing, for hooking device i.e. hooking strut, of turbo-jet engine in aircraft, has stiffener including pressed flange extending along stiffener direction
    FR3021029A1|2015-11-20|AERODYNAMIC CARENAGE
    FR2966803A1|2012-05-04|Sealing joint for use between rear secondary structure and aft pylon fairing of e.g. turbojet engine mounting structure of aircraft, has junction zone with section shrunk with respect to connection zone section to permit folding of joint
    同族专利:
    公开号 | 公开日
    US20150144732A1|2015-05-28|
    US9469409B2|2016-10-18|
    FR3013679B1|2015-11-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4712750A|1986-05-02|1987-12-15|The Boeing Company|Temperature control device for jet engine nacelle associated structure|
    FR2960519A1|2010-05-31|2011-12-02|Airbus Operations Sas|Aerodynamic fairing i.e. rear lower aerodynamic fairing, for hooking device i.e. hooking strut, of turbo-jet engine in aircraft, has stiffener including pressed flange extending along stiffener direction|
    EP2597039A1|2011-11-22|2013-05-29|Airbus Operations |Aerodynamic aft fairing of aircraft engine pylon|
    FR2891803B1|2005-10-07|2007-11-30|Airbus France Sas|RIGID STRUCTURE FOR AN AIRCRAFT ENGINE HANDLING MACHINE, AND MATT COMPRISING SUCH A STRUCTURE|
    FR2913665B1|2007-03-16|2009-06-05|Airbus France Sa|LOWER REAR AERODYNAMIC FAIRING FOR AN AIRCRAFT ENGINE CLAMPING DEVICE|
    FR2921342B1|2007-09-20|2010-03-12|Airbus France|LOWER REAR AERODYNAMIC FAIRING FOR AN AIRCRAFT ENGINE CLAMPING DEVICE|
    FR2960522B1|2010-05-27|2012-06-29|Airbus Operations Sas|METHOD FOR MANUFACTURING BY SUPERPLASTIC FORMING AND BY LAUNDRYING A RIB FOR AERODYNAMIC FITTING OF AN AIRCRAFT ENGINE HITCHING MAT|
    FR2988688B1|2012-03-27|2014-05-09|Airbus Operations Sas|REAR AERODYNAMIC FAIRING HAVING IMPROVED TEMPERATURE FOR AN AIRCRAFT PROPULSION ASSEMBLY|JP6419437B2|2014-02-28|2018-11-07|三菱航空機株式会社|Aircraft engine pylon and aircraft|
    US10144525B2|2015-09-24|2018-12-04|Embraer S.A.|Aircraft engine pylon to wing mounting assembly|
    US9868539B2|2015-09-24|2018-01-16|Embraer S.A.|Aircraft engine pylon to wing mounting assembly|
    US10899463B2|2017-05-16|2021-01-26|Rohr, Inc.|Segmented pylon for an aircraft propulsion system|
    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 3 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-19| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1361556A|FR3013679B1|2013-11-25|2013-11-25|AERODYNAMIC FAIRING DIVIDED IN SUBPARTS|FR1361556A| FR3013679B1|2013-11-25|2013-11-25|AERODYNAMIC FAIRING DIVIDED IN SUBPARTS|
    US14/501,910| US9469409B2|2013-11-25|2014-09-30|Aerodynamic fairing divided into sub-portions|
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