• 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 blade (16) comprising a blade body (30) made of an organic matrix composite material and a leading edge shroud (32) made of a material having better resistance to point impacts than the composite material of the dawn body. The blade (16) includes a blade tip (26). The leading edge shield (32) is assembled on the blade body (30) and comprises an intrados fin (34) and an extrados fin (36). The intrados fin (34) comprises an intrados flap and the extrados fin (36) comprises an extrados flap, the intrados flap and the extrados flap are folded over one another and secured to each other by so as to form a partial covering (48) of the blade tip (26). The invention also relates to a turbojet engine comprising a fan comprising such blades as well as a method for manufacturing such a blade.
    公开号:FR3041683A1
    申请号:FR1559127
    申请日:2015-09-28
    公开日:2017-03-31
    发明作者:Gilles Pierre-Marie Notarianni；Jeremy Guivarc'h；Frederic Jean-Bernard Pouzadoux；Dominique Raulin；Thibault Ruf
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION [0001] The present invention relates to a composite material blade having a leading edge shield. Such leading edge shields are typically designed to protect the leading edges of rotating vanes or guide vanes against impact and erosion. In this context, the term "blades" refers to both the fan blades and the air propeller blades. In order to limit their weight, these blades are typically made of organic matrix composite, for example fiber-reinforced polymer. Although these materials have generally very favorable mechanical properties, in particular with respect to their mass, they have a certain sensitivity to point impacts. Shields, typically made of highly resistant metallic material, such as titanium alloys, are therefore normally installed on the leading edges of such blades, in order to protect them against these impacts. These shields normally take the form of a thin intrados fin and a thin extrados fin joined by a thicker section overlapping the leading edge, the set conforming to the shape of the dawn on the leading edge and adjacent sections of the intrados and the extrados. The intrados and extrados fins extend over these sections of, respectively, the intrados and the extrados of the blade, and serve mainly to ensure the positioning and fixing of the shield on the leading edge.
    In order to improve the aerodynamic performance of the blades, their leading edges are increasingly complex shapes, which complicates the manufacture of shields to marry these shapes and the fastening of the shield on the blade.
    Furthermore, during impacts on a blade, the shield can separate at least partially from the leading edge of the composite blade and cause an alteration of aerodynamic performance related to the degradation of the aerodynamics of the aircraft. dawn accompanied by an imbalance in the case of a partial loss of the shield. In addition, if a portion of the shield is torn off, the leading edge of the blade is no longer protected over its entire height, the composite at the leading edge of the dawn exposed is subjected to the aggressions of the external environment. The resulting profile is usually irregular, which also causes a loss of aerodynamics. It must then repair the dawn and / or replace it.
    OBJECT AND SUMMARY OF THE INVENTION [0004] The present invention aims at remedying at least part of these disadvantages.
    For this purpose, the subject of the invention is a blade comprising a blade body made of fiber-reinforced organic matrix composite material and a leading edge shield made of a material having better resistance to point impacts than the composite material of the blade body, the blade having a blade head, the leading edge shield being assembled on the blade body and having a lower vane and an extrados vane, the lower vane having a flap intrados and extrados wing having an upper flap, the flap intrados and the flap extrados being folded over one another and secured to each other so as to form a partial overlap of the dawn head .
    During shocks on the leading edge shield, the presence of intrados and extrados flaps that extend the lower and upper fins reduces the risk of detachment of the shield, especially near the free edges of the edge shield. attack at the head of dawn, where these detachments are most frequently observed. In fact, the intrados and extrados flaps are not reported, glued or welded on the intrados and extrados fins, they are therefore not separable from the intrados and extrados fins. These flaps intrados and extrados came from material respectively with the fins intrados and extrados so that to take off the leading edge shield of the blade body, it is necessary to dissociate the fins intrados and extrados of the blade body and also to dissociate the flap intrados of the flap extrados. The effort required to take off the leading edge shield of the blade body is therefore more important. Also, the risks of dawn damage are reduced.
    The leading edge shield may be made of titanium-based alloy.
    This material has a very good resistance to punctual impacts.
    Titanium-based alloy is understood to mean alloys whose mass content of titanium is predominant. It is understood that titanium is the element whose mass content in the alloy is the highest. The titanium-based alloy has, for example, a mass content of at least 50% titanium, preferably at least 70% titanium, more preferably at least 80% titanium.
    The leading edge shield may also be steel or metal alloy commonly referred to by the trademark Inconel ™. This is later referred to as a nickel-based alloy with nickel and chromium.
    The lower flap and the upper flap can be secured to one another by gluing or welding.
    These two techniques are simple to achieve and ensure a good bonding of the flap intrados with the flap extrados.
    The flap intrados can be folded over the flap extrados.
    In a turbojet fan, the blades are rotated in a housing arranged around the blades. A fixed point of the casing will first pass the intrados of the dawn and then the extrados. Also, the flap intrados being folded over the flap extrados, when contact between the blade head and the housing, the risk that the flap intrados is disengaged from the flap extrados is reduced. This provision of the flaps intrados and extrados therefore reduces the risk of opening the flap intrados during an involuntary contact with the housing.
    The flap intrados or flap extrados can be secured to the blade head.
    The flap disposed between the blade head and the other flap is secured to the blade head also, for example by gluing. It is thus possible to better secure the flaps intrados and extrados with the blade head.
    The lower vane and the extrados vane each have a free edge, one of the lower fins or extrados may be longer than the other and the flap of the longer vane may comprise a cutout starting from free edge of the longest blade towards the free edge of the shortest blade.
    This cutting of the longest blade makes it possible to make a transition, at the blade head, between the free edge of the longest blade and the free edge of the shortest blade on the head of the blade. 'dawn.
    At least a portion of the blank may comprise a radius of curvature.
    The radius of curvature of the cut minimizes the concentration of local stresses may be present along the cut when the cut has sudden changes in direction. Cutting is not just a straight line between the free edge of the longest blade and the free edge of the shorter blade on the blade head. The cut may have a radius of curvature that changes along the cut. Also, the cutout may have a first portion which runs along the edge formed by the blade head and a second rectilinear portion joining the free edge of the shortest blade, these two parts being connected by a portion having a radius of weak curvature with respect to the other two parts, that is to say a part with strong curvature. The cutout may also have a rectilinear portion and a portion having a radius of curvature. The part having the large radius of curvature may be preceded and / or followed by straight portions or portions having a small radius of curvature.
    The flap of the shortest blade may comprise a blank extending from the free edge of the shortest blade to the free edge of the longer blade.
    The flan of the shortest blade makes it possible to make a transition between the free edge of the longest blade and the free edge of the shortest blade on the blade head. The shape of the blank may correspond to the shape of the cut of the longest blade so that the partial overlap of the blade head has a constant thickness over its entire surface, the thickness of the partial covering being equal to the sum of the thickness of the upper flap and the thickness of the intrados flap. Moreover, thanks to this blank, it increases the contact area between the flap intrados and the flap extrados. It is therefore possible to increase the fastening surface of the intrados and extrados flaps.
    The blade body may comprise, at the top of the blade, a housing for receiving the flap intrados and / or the flap extrados.
    Thus, the surface of the blade head is flat and the blade does not have extra thickness at the blade head due to the folding of the flap intrados and flap extrados.
    The invention also relates to a turbojet engine comprising a fan comprising a plurality of blades as defined above.
    The invention also relates to a method of manufacturing a blade as defined above comprising the following steps: - assembly of the leading edge shield on the blade body; - folding of the flap extrados on the blade head; - folding of the flap intrados on the flap extrados; - Securing the upper flap and flap intrados by gluing or welding.
    The upper flap can be glued to the blade head.
    BRIEF DESCRIPTION OF THE DRAWINGS Other characteristics and advantages of the invention will emerge from the following description of embodiments of the invention, given by way of non-limiting examples, with reference to the appended figures, in which: Figure 1 is a schematic perspective view of a turbofan engine; - Figure 2 is a schematic perspective view of the intrados side of a rotating blade of the fan of the turbojet engine of Figure 1 according to a first embodiment of the blade; - Figure 3 is a partial schematic perspective view of the blade of Figure 2 before folding the flaps; - Figure 4 is a partial schematic perspective view of a rotating blade according to a second embodiment of the blade; - Figures 5 to 7 are partial sectional views of the blade of Figure 4 respectively along the plane V-V, VI-VI and VII-VII; - Figures 8A and 8B are partial schematic views of a rotating blade according to a third embodiment of the blade; - Figures 9 and 10 are partial schematic views of a rotating blade according to a fourth and a fifth embodiment of the blade.
    DETAILED DESCRIPTION OF THE INVENTION FIG. 1 illustrates a turbofan engine 10 comprising a gas generator group 12 and a fan 14. This fan 14 comprises a plurality of rotating vanes 16 arranged radially about an axis. central X, and aerodynamically profiled so as to impulse the air by their rotation. Thus, as illustrated in FIGS. 2 and 3, each blade 16 has a leading edge 18, a trailing edge 20, a lower surface 22, an extrados 24, a blade head 26 and a blade root 28.
    In normal operation, the relative wind is substantially oriented towards the leading edge 18 of each blade 16. Thus, this leading edge 18 is particularly exposed to impacts. In particular when the blade 16 comprises a blade body 30 made of a composite material, in particular an organic matrix material, for example a fiber-reinforced polymer, it is therefore advisable to protect the leading edge 18 with an edge shield. 32 attack integrated at each dawn. In other words, the leading edge shield 32 is assembled on the blade body 30.
    The leading edge shield 32 is made of a material having a better impact resistant point than the composite material of the blade body 30. The leading edge shield 32 is mainly metallic, and more specifically in titanium-based alloy, such as TA6V (T-6AI-4V). The leading edge shield 32 could also be steel or metal alloy commonly referred to by the trademark Inconel ™. This is later referred to as a nickel-based alloy with nickel and chromium.
    The leading edge shield 32 comprises a lower wing 34, an upper wing 36 and a thicker central section 38, intended to overlap an edge of the blade body 30 and connecting the lower wing 34 and the extrados vane 36. The intrados and extrados fins 34, 36 ensure the positioning of the shield 32 on the blade body 30. The intrados and extrados fins 34, 36 each have a free edge 40, 42 and have, in FIG. identical lengths.
    Furthermore, the intrados vane 34 has a flap intrados 44 and the extrados fin 36 has an extrados flap 46. The flap intrados 44 and the flap 46 extrados come from material with the fin 34 respectively fins and fin extrados 36.
    In Figure 2, the intrados flaps 44 and extrados 46 are shown folded over one another so as to form a partial overlap 48 of the blade head 26. In addition, the flap intrados 44 is secured with the upper flap 46, for example by gluing by welding.
    The manufacturing process of the blade 16 comprises a first step of assembling the leading edge shield 32 on the blade body 30, as shown in FIG. 3. The method also comprises a folding step. the upper flap 46 on the blade head 26 and a folding step of the flap intrados 44 on the upper flap 46, the upper flap 46 and the flap intrados 44 being secured to one another by gluing or welding.
    The manufacturing process of the blade 16 may also comprise a step during which the flap disposed between the blade head 26 and the other flap is also secured to the blade head 26, for example by bonding. In this case, the upper flap 46 can be glued to the blade head 26.
    The blade 16 can also be manufactured, after assembly of the leading edge shield 32 on the blade body 30 by first folding the flap intrados 44 on the blade head 26 and then folding the upper flap 46 on the flap intrados 44. When one folds first the flap intrados 44 on the blade head 26, we can consider sticking the flap intrados 44 on the blade head 26. The flap intrados 44 and the upper flap 46 are secured by gluing or welding.
    In the following, the elements common to the various embodiments are identified by the same reference numerals.
    Figures 4 to 7 show a second embodiment of the blade 16 in which the intrados vane 34 is longer than the extrados vane 36, see in particular Figure 5.
    Furthermore, in the embodiment of Figures 4 to 7, the flap intrados 44 is folded over the upper flap 46. The flap intrados 44 and the upper flap 46 are secured to one another by gluing or by welding. They form a partial overlap 48 of the blade head 26. The upper flap 46 can be glued to the blade head 26.
    The flap intrados 44 further comprises a cutout 52 from the free edge 40 of the intrados vane 34 to the free edge 42 of the extrados vane 42 when the flap intrados 44 and the flap 46 are extrados folded one on the other on the dawn head 26.
    In the embodiment of Figures 4 to 7, the blade body 30 comprises, at the blade head 26, a housing 54 for receiving the flap intrados 44 and the flap 46 extrados so that the head of blade 26 has a smooth surface and does not have extra thickness to the right partial recovery 48 of the blade head 26.
    Figures 8A and 8B show a third embodiment of the blade 16 in which, the intrados vane 34 is longer than the extrados vane 36, the lower flap 44 being folded over the upper flap 46. The flap intrados 44 has a cutout 52 from the free edge 40 of the intrados vane 34 to the free edge 42 of the extrados vane 42 when the flap intrados 44 and the upper flap 46 are folded one on the other on the blade head 26. In addition, the upper flap 46 has a blank 56 extending from the free edge 42 of the extrados vane 36 towards the free edge 40 of the intrados vane 34 when the lower flap 44 and the upper flap 46 are folded one over the other on the dawn head 26.
    In the embodiment of Figures 8A and 8B, the cutout 52 is curved, that is to say that the cutout 52 comprises at least one radius of curvature. The radius of curvature can evolve along the cutout 52 of the free edge 40 of the intrados vane 34 towards the free edge 42 of the extrados vane 36 or be constant.
    Furthermore, the blade body 30 does not have a receiving housing flaps intrados 44 and extrados 46 so that the flaps intrados 44 and extrados 46 form extra thickness of the blade head 26 on the partial recovery 48 of the dawn head 26.
    FIG. 9 shows an embodiment of the blade 16 similar to the embodiment of FIGS. 8A and 8B but which differs in that the cutout 52 has a first portion 58 starting from the free edge 40 of the vane. 34 and which runs along the edge of the blade head 26, and a second straight portion 62 joining the free edge 42 of the extrados fin 36, the first portion 58 and the second straight portion 62 being interconnected by a third portion 60 having a small radius of curvature with respect to the other portions 58, 62, i.e. the third portion 60 has a strong curvature with respect to the other portions of the cutout 52.
    FIG. 10 represents an embodiment of the blade 16, in which the extrados vane 36 is longer than the intrados vane 34.
    Although the present invention has been described with reference to specific embodiments, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In addition, individual features of the various embodiments mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    In particular, a cutout 52 having a portion having a radius of curvature may be combined with a housing for receiving the flaps intrados and extrados. The receiving housing may receive only one of the two flaps. The receiving housing can receive the two flaps in a portion of the receiving housing and receive only one flap in the other part of the receiving housing, for example when the flap of the shorter blade does not have any blank.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A blade (16) comprising a blade body (30) made of a fiber-reinforced organic matrix composite material and a leading edge shield (32) of a material having better impact resistance than the composite material the blade body (16) comprising a blade head (26), the leading edge shield (32) being assembled on the blade body (30) and having a lower blade (34). ) and an extrados vane (36), characterized in that the intrados vane (34) has a lower flap (44) and in that the upper vane (36) has an upper flap (46), the lower flap ( 44) and the upper flap (46) being folded over one another and secured to each other so as to form a partial overlap (48) of the blade head (26).
    [2" id="c-fr-0002]
    2. blade (16) according to claim 1, wherein the lower flap (44) and the upper flap (46) are secured to one another by gluing or welding.
    [3" id="c-fr-0003]
    3. blade (16) according to claim 1 or 2, wherein the intrados flap (44) is folded over the upper flap (46).
    [4" id="c-fr-0004]
    4. blade (16) according to any one of the preceding claims, wherein the flap intrados (44) or the upper flap (46) is secured to the blade head (26).
    [5" id="c-fr-0005]
    5. blade (16) according to any one of the preceding claims, wherein the vane fin (34) and the extrados vane (36) each comprise a free edge (40, 42), one of the fins intrados or extrados (34, 36) being longer than the other and the flap of the longer blade having a cutout (52) extending from the free edge of the longer blade to the free edge of the blade. short.
    [6" id="c-fr-0006]
    6. blade (16) according to the preceding claim, wherein at least a portion of the blank (52) has a radius of curvature.
    [7" id="c-fr-0007]
    The blade (16) according to claim 5 or 6, wherein the flap of the shortest blade has a blank (56) extending from the free edge of the shortest blade to the free edge of the blade. longer.
    [8" id="c-fr-0008]
    8. blade (16) according to any preceding claim, wherein the blade body (30) comprises, at the blade head (26), a housing (54) for receiving the flap intrados (44) and / or the upper flap (46).
    [9" id="c-fr-0009]
    9. Turbojet engine (10) comprising a fan (14) having a plurality of vanes (16) according to any one of the preceding claims.
    [10" id="c-fr-0010]
    10. A method of manufacturing a blade (16) according to any one of claims 1 to 8, comprising the steps of: - assembly of the leading edge shield (32) on the blade body (30); - Folding the upper flap (46) on the blade head (26); folding of the intrados flap (44) on the upper flap (46); - Securing the upper flap (46) and the flap intrados (44) by gluing or welding.
    类似技术:
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    同族专利:
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    CN111231369A|2020-02-18|2020-06-05|中材科技风电叶片股份有限公司|Protective shell, preparation method thereof and manufacturing method of wind power blade|
    法律状态:
    2016-09-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-31| PLSC| Publication of the preliminary search report|Effective date: 20170331 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559127A|FR3041683B1|2015-09-28|2015-09-28|DAWN INCLUDING A FOLDED ATTACK EDGE SHIELD AND PROCESS FOR MANUFACTURING THE DAWN|FR1559127A| FR3041683B1|2015-09-28|2015-09-28|DAWN INCLUDING A FOLDED ATTACK EDGE SHIELD AND PROCESS FOR MANUFACTURING THE DAWN|
    EP16790634.6A| EP3356651B1|2015-09-28|2016-09-27|Blade having a shield at the leading edge and method of manufacturing this blade|
    RU2018114902A| RU2730201C2|2015-09-28|2016-09-27|Blade, vane manufacturing method and turbojet engine containing such blade|
    BR112018006148-4A| BR112018006148B1|2015-09-28|2016-09-27|BLADE, TURBOJET, AND METHOD FOR MAKING A BLADE|
    PCT/FR2016/052443| WO2017055726A1|2015-09-28|2016-09-27|Blade comprising a leading edge shield and method of manufacturing the blade|
    US15/763,703| US10883374B2|2015-09-28|2016-09-27|Blade comprising a folded leading edge shield and method of manufacturing the blade|
    CN201680056305.1A| CN108026777B|2015-09-28|2016-09-27|Blade including a folded leading edge guard and method of making the same|
    JP2018515979A| JP6810136B2|2015-09-28|2016-09-27|A blade with a folded front edge shield and a method of manufacturing the blade.|
    CA2999360A| CA2999360A1|2015-09-28|2016-09-27|Blade comprising a leading edge shield and method of manufacturing the blade|
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