• 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:
    A blade (16) comprising a blade body (30) of fiber-reinforced organic matrix composite material and a leading edge shield (32) of a material having better resistance to point impacts than the composite material of the dawn body. The leading edge shield (32) is assembled on the blade body (30) and the blade (16) has a securing reinforcement (46) adhered to the leading edge shield (32) and on the dawn body (16). The invention also relates to a turbojet comprising a fan comprising such blades and a method of manufacturing such a blade.
    公开号:FR3041684A1
    申请号:FR1559132
    申请日:2015-09-28
    公开日:2017-03-31
    发明作者:Matthieu Arnaud Gimat；Jeremy Guivarc'h；Gilles Pierre-Marie Notarianni；Frederic Jean-Bernard Pouzadoux；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 be separated 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 leading edge shield being assembled on the blade body, the blade having a securing reinforcement glued to the leading edge shield and the blade body.
    During shocks on the leading edge shield, the presence of the fastening reinforcement reduces the risk of detachment of the shield, especially near the free edges of the leading edge shield. Indeed, the fastening reinforcement being bonded to both the leading edge shield and the blade body, at least a portion of the free edge of the leading edge shield is covered by the fastening reinforcement if although the effort required to take off the leading edge shield of the dawn body is more important. Also, the risks of dawn damage are reduced.
    Furthermore, during a shock, if the fastening reinforcement is damaged, it can be replaced without having to replace the leading edge shield andyou dawn.
    [0008] The leading edge shield may be made of titanium-based alloy.
    This material has a very good resistance to punctual impacts.
    By titanium-based alloy is meant 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 securing reinforcement may comprise fibers oriented preferably perpendicularly to a free edge of the leading edge shield.
    The orientation of the fibers is parallel to the main forces to which the free edges of the leading edge shields are subjected during their detachment, so that the reinforcing effect of the reinforcing reinforcement is maximized. A fastening reinforcement of this type is of low cost and is readily available. It can also be easily positioned and stuck on dawn.
    The securing reinforcement may comprise unidirectional fibers, woven fibers and / or nonwoven fibers distributed uniformly. These fibers are, for example, glass fibers or carbon fibers.
    The securing reinforcement may comprise a stack of layers of fibers, each layer may comprise fibers of a composition different from the other layers and each layer may have a fiber orientation different from the other layers.
    The composition of the securing reinforcement may not be uniform over its entire surface.
    It is therefore understood that although fibers may have different orientations, the orientation of the fibers is predominantly perpendicular to a free edge of the leading edge shield.
    The blade comprises a blade head and a blade root and the leading edge shield may comprise a projecting portion and a recessed portion, the recessed portion being disposed between the blade head and the protruding portion and the securing reinforcement may be glued to the recessed portion.
    The hollow portion of the blade is disposed more towards the blade head than the projecting portion. It has been found that the leading edge shield detachments generally take place in the recessed portion of the leading edge shield at the head of the blade.
    The blade may comprise an upper surface, a lower surface and at least two reinforcing reinforcements, a first bonding reinforcement being bonded to the intrados and a second bonding reinforcement being bonded to the upper surface.
    This reinforces the free edge of the intrados and extrados side of the blade.
    Furthermore, especially when the blade comprises several reinforcing reinforcements, each fastening reinforcement may have a shape different from the other reinforcing reinforcements and / or comprise fibers of a different composition and orientation of the other reinforcements. bonding and / or being formed by one or more layers of stacked fibers, these layers may comprise fibers of a composition different from the other layers and each layer may have a fiber orientation different from the other layers.
    The blade may comprise an upper surface and a lower surface and wherein the reinforcing reinforcement comprises a first portion bonded to the lower surface and a second portion bonded to the upper surface, the first portion and the second portion are interconnected. by an intermediate party.
    It sticks a single fastening reinforcement on the blade that covers both the free edges of the leading edge shield on the underside and the extrados side.
    The intermediate portion can be glued to the leading edge shield.
    The intermediate portion may be glued on a trailing edge of the blade.
    The intermediate portion can be glued to a blade head.
    The invention also relates to a turbojet comprising a fan comprising a plurality of blades as defined above and a method of manufacturing a blade as defined above.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features 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; FIG. 3 is a diagrammatic perspective view of the extrados side of the blade of FIG. 3; FIGS. 4, 5A, 5B and 5C are diagrammatic perspective views of reinforcing reinforcement; - Figures 6 and 7 are schematic perspective views respectively of the intrados side and the extrados side of a blade according to a second embodiment of the blade; - Figures 8, 9 and 10 are schematic perspective views of a blade respectively according to a third, fourth and fifth embodiment of the blade.
    DETAILED DESCRIPTION OF THE INVENTION [0030] 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 a fiber-reinforced polymer matrix, it is therefore advisable to protect the leading edge 18 with a leading edge shield 32 integrated into 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 resistance to punctual impacts 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 ™. Inconel is later referred to as an alloy based on iron alloyed 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 wing 36. The intrados and extrados fins 34, 36 ensure the positioning of the shield 32 on the blade body 30. The lower and upper fins 34, 36 each have a free edge 40 and may have identical lengths or one of the fins 34, 36 may be longer than the other.
    Furthermore, the shield 32 has a projecting portion 42 and a recessed portion 44. The projecting portion 44 is disposed between the blade head 26 and the projecting portion 42. It is therefore understood that the part in FIG. protrusion 42 of the shield 32 is disposed between the recessed portion 44 and the blade root 28. Thus, starting from the blade root to the blade head, the blade root 28 is successively protrusion 42, recessed portion 44 and blade head 26.
    In the embodiment of Figures 2 and 3, the blade 16 comprises a first bonding reinforcement 46 adhered to the lower surface 22 and a second fastening reinforcement 48 bonded to the extrados 24. Each reinforcement 46 , 48 is bonded to both the blade body 30 and the leading edge shield 32. Each securing reinforcement 46, 48 thus covers a portion of each free edge 40 of the leading edge shield 32 respectively on the intrados 22 and the extrados 24.
    The fastening reinforcement 46 is bonded to the recessed portion 44 and thus covers the portion of the free edge 40 of the leading edge shield 32 located at the right of this recessed portion 44. In Figure 2, reinforcement 46 is glued close to the blade head 26. It is glued between 0.6 of the total height H of the blade 16, measured starting from the blade root 28, and the total height H of the blade 16.
    The reinforcing reinforcements 46, 48 may comprise fibers. For example, as shown in FIG. 4, the fibers 50 can all be oriented in the same direction, which is then referred to as directional solid fibers. The fibers 50 are here shown partially immersed in a matrix 52 to show their orientation. It is understood that in the fastening reinforcement, the fibers 50 are completely immersed in the matrix 52, so-called impregnated folds. Generally, the matrix 52 comprises compounds for sticking the fibers on a support, in this case on the blade 16.
    The fibers 50 are preferably oriented perpendicular to the free edge 40 of the leading edge shield 32. In fact, this direction, represented by the double arrow R, and the direction in which the tearing forces of the edge shield. of attack are maximal.
    The securing reinforcement may also comprise woven fibers. Figures 5A, 5B and 5C show different examples of woven fibers. The fibers 50 may be immersed in a matrix or provided in the form of non-impregnated sheets or rolls.
    The reinforcing reinforcement may also comprise nonwoven fibers, for example fibers 50 distributed uniformly within a matrix 52.
    Thus, the method of manufacturing the blade 16 comprises a step of assembling the leading edge shield 32 on the blade body 30, for example by gluing. This step is followed by a step of bonding or reinforcing ribs 46, 48 on the blade 16. Each reinforcing reinforcement 46, 48 being glued on both the blade body 30 and on the edge shield. attack 32.
    Typically, when the matrix 52 comprises a thermosetting glue, the blade on which is positioned the fastening reinforcement is disposed in an autoclave to ensure the bonding of the fastening reinforcement on the blade.
    When the fibers are in their non-impregnated form, they are cut to the desired dimensions, disposed on the blade 16 and impregnated with glue. The blade 16 then undergoes a treatment, for example a heating step in an autoclave, to ensure the bonding of the fastening reinforcement on the blade.
    The bonding step may be preceded by a step of preparing the contiguous surfaces, that is to say the surfaces of the blade body 30 and / or the leading edge shield 32.
    In what follows, the elements common to the various embodiments are identified by the same reference numerals.
    Figures 6 and 7 show a second embodiment of the blade 16 in which the securing reinforcement 46 has a first portion 54 bonded to the intrados 22 and a second portion 56 bonded to the extrados 24. The first portion 54 and the second portion 56 are interconnected by an intermediate portion 58. In Figures 6 and 7, the intermediate portion 58 is bonded to the leading edge shield 32. The fastening reinforcement 46 covers the shield of leading edge 32 over the entire height of the fastening reinforcement 46.
    FIG. 8 represents a third embodiment of the blade 16 in which the intermediate portion 58 of the securing reinforcement 46 is bonded to the trailing edge 20 of the blade 16.
    9 shows a fourth embodiment of the blade 16 in which the fastening reinforcement 46 comprises two intermediate parts 58 one glued to the leading edge shield 32 and the other glued on the edge 20 of the dawn 16. The fastening reinforcement 46 thus covers the entire surface of the blade 46 over the height of the fastening reinforcement 46.
    Note that the blade 16 of Figure 9 has a different shape of the blades of the previous figures. However, the blade 16 of FIG. 9 also includes a projecting portion 42 and a recessed portion 44. The projecting portion 44 is disposed between the blade head 26 and the projecting portion 42. It will therefore be understood that the protruding portion 42 of the shield 32 is disposed between the recessed portion 44 and the blade root 28. Thus, starting from the blade root to the blade head, successively the blade root 28, the projecting portion 42, recessed portion 44 and blade head 26.
    FIG. 10 represents a fifth embodiment of the blade 16 in which the intermediate portion 58 is glued to the blade head 26. In FIG. 10, the fibers are preferably oriented perpendicularly to the free edge 40 of the shield Leading edge 32. Alternatively, the fibers could be oriented preferably perpendicularly to the free edge of the leading edge shield at the blade head, that is to say that the orientation of the fibers of the fastening reinforcement would be parallel to the free edge 40 of the leading edge shield 32.
    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, the securing reinforcement may comprise several layers of fibers stacked on each other, each layer may comprise fibers of a composition different from the other layers and each layer may have a fiber orientation different from the other layers. The composition of the securing reinforcement may not be uniform over its entire surface. Moreover, especially when the blade comprises several reinforcing reinforcements, each reinforcing reinforcement may have a shape different from the other reinforcing reinforcements and / or comprise fibers of a different composition and orientation of the other reinforcing reinforcements and and / or being formed by one or more layers of stacked fibers, these layers possibly comprising fibers of a composition different from the other layers and each layer being able to have a fiber orientation different from the other layers.
    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 of the blade body, the leading edge shield (32) being assembled on the blade body (30), characterized in that the blade (16) comprises a securing reinforcement (46, 48) glued on the leading edge shield (32) and the blade body (30).
    [2" id="c-fr-0002]
    2. blade (16) according to the preceding claim, wherein the securing reinforcement (46, 48) comprises fibers oriented preferably perpendicular to a free edge (40) of the leading edge shield (32).
    [3" id="c-fr-0003]
    The blade (16) according to any one of the preceding claims, wherein the blade comprises a blade head (26) and a blade root (28), the leading edge shield (32) comprising a protruding portion (42) and a recessed portion (44), the recessed portion (44) being disposed between the blade head (26) and the projecting portion (42) and the securing reinforcement (46, 48) being adhered to the recessed portion (44).
    [4" id="c-fr-0004]
    4. blade (16) according to any one of claims 1 to 3, wherein the blade (16) comprises an extrados (24), a lower surface (22) and at least two reinforcing fasteners, a first reinforcing fastening (46) being glued on the intrados (22) and a second securing reinforcement (48) being glued on the upper surface (24).
    [5" id="c-fr-0005]
    5. blade (16) according to any one of claims 1 to 3, wherein the blade (16) comprises an upper surface (24) and a lower surface (22) and wherein the fastening reinforcement (46) comprises a first part (54) glued to the pressure surface (22) and a second part (56) glued to the upper surface (24), the first part (54) and the second part (56) are interconnected by an intermediate part ( 58).
    [6" id="c-fr-0006]
    The blade (16) of claim 5 wherein the intermediate portion (58) is bonded to the leading edge shield (32).
    [7" id="c-fr-0007]
    7. blade (16) according to claim 5 or 6, wherein the intermediate portion (58) is bonded to a trailing edge (20) of the blade (16).
    [8" id="c-fr-0008]
    8. blade (16) according to any one of claims 5 to 7, wherein the intermediate portion (58) is bonded to a blade head (26).
    [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 blade body (30) and the leading edge shield (32); and - bonding the fastening reinforcement (46,48) on the blade (16).
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3356651B1|2021-11-10|Blade having a shield at the leading edge and method of manufacturing this blade
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    EP2199544B1|2016-03-30|Assembly of guide vanes
    EP2715145B1|2019-07-31|Method for reinforcing a mechanical component
    CA3009226A1|2017-06-29|Leading edge shield
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    FR3112821A1|2022-01-28|SHIELD FOR BLADE IN COMPOSITE MATERIAL, BLADE AND TURBOMACHINE COMPRISING THE SHIELD, METHOD FOR MANUFACTURING THE BLADE
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    FR3106848A1|2021-08-06|Turbomachinery blade with leading edge shield
    EP3473813A1|2019-04-24|Turbine engine with a rectifier unit
    FR3108664A1|2021-10-01|Fan rotor with upstream center of gravity vanes
    同族专利:
    公开号 | 公开日
    EP3356650B1|2021-11-10|
    US20180274374A1|2018-09-27|
    WO2017055727A1|2017-04-06|
    CN108026778B|2021-08-17|
    US11105210B2|2021-08-31|
    CN108026778A|2018-05-11|
    EP3356650A1|2018-08-08|
    FR3041684B1|2021-12-10|
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    JP6421078B2|2015-05-28|2018-11-07|エムエイチアイ ヴェスタス オフショア ウィンド エー／エス|Wind turbine blade and wind power generator, and method for manufacturing or modifying wind turbine blade|
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    FR3085417B1|2018-08-29|2020-12-04|Safran Aircraft Engines|DAWN INCLUDING A STRUCTURE IN COMPOSITE MATERIAL AND ASSOCIATED MANUFACTURING PROCESS|
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    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
    FR1559132A|FR3041684B1|2015-09-28|2015-09-28|DAWN INCLUDING AN ATTACK EDGE SHIELD AND PROCESS FOR MANUFACTURING THE DAWN|FR1559132A| FR3041684B1|2015-09-28|2015-09-28|DAWN INCLUDING AN ATTACK EDGE SHIELD AND PROCESS FOR MANUFACTURING THE DAWN|
    PCT/FR2016/052444| WO2017055727A1|2015-09-28|2016-09-27|Vane comprising a leading-edge shield and method for producing said vane|
    US15/763,404| US11105210B2|2015-09-28|2016-09-27|Blade comprising a leading edge shield and method for producing the blade|
    EP16787491.6A| EP3356650B1|2015-09-28|2016-09-27|Blade havind a shield at the leading edge and process of fabricating this blade|
    CN201680056339.0A| CN108026778B|2015-09-28|2016-09-27|Blade comprising a leading edge guard and method of producing the same|
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