• 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 the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), said leading edge shield (32) comprising a lower wing (34) and an extrados wing (36). Each of the vanes (34,36) extends from a height (H) from a lower edge (50) to an upper edge (51) and from the leading edge to a respective trailing edge, and is connected to each other. to one another across the leading edge. At least one fin of the upper fin (36) and the lower fin (34) has a segment (S1) adjacent to the upper edge (51) and extending over at least 10% of the height (H), wherein the trailing edge (42) tilts toward the upper edge (51) such that an angle of intersection (a) between a tangent (t51) at the upper edge (51) and a tangent (t42) at a point any of the rear edge (42) of the fin in said segment (S1) is less than 75 °.
    公开号:FR3045713A1
    申请号:FR1563009
    申请日:2015-12-21
    公开日:2017-06-23
    发明作者:Frederic Jean-Bernard Pouzadoux；Alain Jacques Michel Bassot；Jeremy Guivarc'h；Jean-Louis Romero；Thibault Ruf
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to a leading edge shield for a turbomachine blade. In this context, the term "turbomachine" means any machine in which energy transfer can take place between a fluid flow and at least one blade, such as, for example, a compressor, a pump, a turbine, a helix, or a combination of at least two thereof.
    Such leading edge shields are typically designed to protect the leading edges of rotating vanes or guide vanes against impacts. 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 mainly formed of a blade body made of organic matrix composite, for example polymer, reinforced with fibers. 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 in height and in length on these sections of, respectively, the intrados and the extrados of the blade, and serve mainly to ensure the positioning and the fixation of the shield on the leading edge but also to distribute the force of an impact and dissipate its energy over a larger area of the dawn body. Thus, in case of impact on the leading edge shield, deformation waves will propagate through the shield, including the fins, until fully dissipated. However, in some cases, this propagation can create deformation peaks that can even lead to partial delamination of a fin.
    The present disclosure aims to remedy these drawbacks by proposing a leading edge shield for a turbomachine blade that is more resistant to detachment in the event of an impact.
    In at least one embodiment, this object is achieved by virtue of the fact that, in said leading edge shield, which may be made of metallic material and comprises two fins, each extending over a height of a lower edge at an upper edge and in length of the leading edge to a trailing edge, and connected to each other through the leading edge, at least one of said fins has a segment, adjacent to the upper edge and extending at least 6% of said height, wherein the respective trailing edge slopes towards the upper edge such that an angle of intersection between a tangent to the upper edge and a tangent at any point of the trailing edge in said segment is less than 75 °, or even less than 60 °.
    Such an acute angle has the advantage, compared to a more open angle, or even right, to make it more difficult to detach the fin from the junction between the rear edge and the upper edge in case of impact.
    In order to avoid the concentration of forces, the rear edge may have continuity of tangency over the entire height of the shield, the evolution of the length of the fin being thus gradual and may in particular avoid too pronounced curvatures, corresponding to radii of curvature below a predetermined minimum.
    The present disclosure also relates to a blade extending in height from a blade root to a blade head and comprising a blade body and such a leading edge shield assembled on the blade body, blade body being of anisotropic material, the leading edge shield being of a material having a better resistance to point impacts than the anisotropic material of the blade body.
    In this blade, the anisotropic material may comprise at least one layer, and in particular a layer adjacent to the fin, with a main direction of mechanical resistance substantially parallel to an inner surface of fin adjacent said segment and having an angle with respect to said upper edge substantially greater than a maximum value of said angle of intersection in said segment, to better withstand the bending forces of this blade. This anisotropic material may especially be a composite material reinforced with fibers oriented along at least said main direction. Since it is avoided that the rear edge of the fin is aligned with this main direction near the blade head, it is more difficult to tear the fin from the rear edge which could otherwise be facilitated by the slightest mechanical strength of the anisotropic material of the blade body perpendicular to its main direction.
    The present disclosure also relates to a turbomachine comprising a plurality of such blades, a fan comprising a plurality of such blades and a turbofan engine comprising such a fan.
    BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood and its advantages will appear better on reading the detailed description which follows, of an embodiment shown by way of non-limiting example. The description refers to the accompanying drawings in which: - Figure 1 is a schematic perspective view of a turbofan engine; - Figure 2 is a schematic perspective view of the extrados 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 sectional view of the blade of Figure 2 along the plane III-III.
    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 a central axis X, aerodynamically profiled so as to impulse the air by their rotation and surrounded by a fan casing. 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 addition, the blade 16 comprises a blade body 30 of composite material, in particular fiber-reinforced polymer matrix. These fibers may have at least one particular orientation, thus resulting in at least one main direction of mechanical strength, and therefore an anisotropic nature of the material. More specifically, in order to better withstand the centrifugal forces, as well as the flexural forces on the dawn, this main direction can be that of the height of the blade 16, from the blade root 28 to the blade head 26 .
    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. It is therefore appropriate to protect the leading edge 18 with a leading edge shield 32 integrated with each blade 16. 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 better impact resistance than the composite material of the blade body 30. The leading edge shield 32 is mainly metallic, and more specifically alloy based. titanium, 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.
    As illustrated in particular in FIG. 3, the leading edge shield 32 comprises a lower vane 34, an extrados fin 36, and a thicker central section 38 intended to overlap an edge of the vane body 30 and connecting the vane. intrados fin 34 and fin extrados 36 to the leading edge 18. The intrados and extrados fins 34, 36 ensure the positioning of the shield 32 on the blade body 30, but also the dissipation of the impact energy. The lower and upper fins 34, 36 and each extend in height over a height H from a lower edge 50 to an upper edge 51 and in length from the leading edge 18 to the rear edge 40, 42 corresponding.
    In order to better dissipate the energy of the deformation waves propagating through the shield 32 following an impact, the trailing edge 42 of the extrados fin 36 is not parallel to the leading edge 18 over its entire length, but is inclined near the upper edge 51 so that, over an entire SI segment adjacent to the upper edge 51, the angle of intersection between a tangent t51 at the upper edge 51 and a tangent t42 at any point of the trailing edge 42 is less than 75 °, or even less than 60 °. The segment SI may for example extend over 10% or even 15% of the height H of the shield 30 from the upper edge 51. The inclination of the rear edge 42 towards the leading edge 18 by approaching the upper edge 51 locally reduces the length of the extrados vane 36, which helps to prevent the propagation of local detachment of the shield 32 along the trailing edge 42.
    Since at least a portion of the fibers F of the composite material of the blade body 30 are oriented according to the height of the blade 16, this main direction of the composite material of the blade body 30 has a substantially straight angle β relative to the edge upper 51 of the shield 32 in a plane substantially parallel to an inner surface of the extrados fin 36. More specifically, this angle β can be between 60 ° and 120 °, or between 75 ° and 105 °. More particularly, as illustrated in FIG. 3, fibers F in this orientation can be integrated in a layer, for example of unidirectional fibers or woven in at least two directions, close to or even adjacent to the extrados 24, even if the material composite of the blade body 30 may be covered with a layer of varnish or paint on this surface.
    Thanks to the inclination of the trailing edge 42 of the extrados vane 36 close to the upper edge 51, it can be ensured that the angle of intersection α between the tangent t42 at any point of the trailing edge 42 in the segment SI is substantially less, for example less than 5 ° or even 10 °, or even 15 ° or 25 °, at the angle β, so as to avoid alignment of the rear edge 42 with these fibers F, alignment that would facilitate tearing of the rear edge 42 with one or fragments of this composite material in case of impact.
    Although the present invention has been described with reference to a specific exemplary embodiment, it is obvious that various modifications and changes can be made to this example without departing from the general scope of the invention as defined by the claims. In particular, although in the embodiment described and illustrated only the extrados vane has a rear edge inclined near the upper edge, the invention is also applicable to the intrados fin, or both wings. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    A leading edge shield (32) for a turbomachine blade (16), said leading edge shield (32) having two fins (34,36), each extending over a height (H) of a lower edge (50) at an upper edge (51) and in length of the leading edge at a respective trailing edge (40,42), and connected to each other across the leading edge (18); ), and wherein at least one of said fins (34,36) has a segment (SI), adjacent to the upper edge (51) and extending over at least 6% of the height (H), wherein the rear edge (40,42) tilts toward the upper edge (51) such that an angle of intersection (a) between a tangent (t51) at the upper edge (51) and a tangent (t42) at a point any of the trailing edge in said segment (SI) is less than 75 °.
    [2" id="c-fr-0002]
    The leading edge shield (32) according to claim 1, wherein said angle of intersection (a) is less than 60 °.
    [3" id="c-fr-0003]
    3. Shield (32) according to any one of the preceding claims, made of metallic material.
    [4" id="c-fr-0004]
    A blade (16) extending in height from a blade root to a blade head and comprising a blade body (30) and a leading edge shield (32) according to any one of of the preceding claims, assembled on the blade body (30), the blade joint (30) being of anisotropic material, and the leading edge shield (32) being of a material having better resistance to point impacts as the anisotropic material of the blade body (30).
    [5" id="c-fr-0005]
    The blade (16) according to claim 4, wherein the anisotropic material comprises at least one layer with a main direction of mechanical strength substantially parallel to an inner fin surface adjacent to said segment (SI) and having an angle (β) with respect to said upper edge (51) substantially greater than a maximum value of said intersection angle (a) in said segment (SI).
    [6" id="c-fr-0006]
    The blade (16) according to claim 5, wherein said anisotropic material is a fiber reinforced composite material oriented along at least said main direction.
    [7" id="c-fr-0007]
    A blower (14) comprising a plurality of blades (16) according to any one of claims 4 to 6.
    [8" id="c-fr-0008]
    8. A turbofan engine (10) comprising a blower according to claim 7. *
    类似技术:
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    EP3394399B1|2021-07-07|Blade, associated fan and turbojet engine
    EP1972757B1|2012-07-18|Rotor assembly of a turbomachine fan
    FR2725240A1|1996-04-05|A FIN OF COMPOSITE MATERIAL, ESPECIALLY FOR TURBOMOTORS
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    EP3356651B1|2021-11-10|Blade having a shield at the leading edge and method of manufacturing this blade
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    EP3394398A1|2018-10-31|Leading edge shield
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    FR3041684A1|2017-03-31|DAWN COMPRISING AN ATTACK EDGE SHIELD AND METHOD FOR MANUFACTURING THE DAWN
    EP3394396B1|2019-10-02|Leading edge sheath
    EP3121375A1|2017-01-25|Composite compressor vane of an axial turbomachine
    FR3070427A1|2019-03-01|INSERT FOR FIXING A COMPONENT ON A TURBOMACHINE SUPPORT
    FR3106848A1|2021-08-06|Turbomachinery blade with leading edge shield
    FR3112822A1|2022-01-28|BLADE IN COMPOSITE MATERIAL WITH A SHIELD, AND TURBOMACHINE INCLUDING THE BLADE
    EP3473813A1|2019-04-24|Turbine engine with a rectifier unit
    FR3112821A1|2022-01-28|SHIELD FOR BLADE IN COMPOSITE MATERIAL, BLADE AND TURBOMACHINE COMPRISING THE SHIELD, METHOD FOR MANUFACTURING THE BLADE
    FR3032942A1|2016-08-26|AIRCRAFT PROPULSIVE ASSEMBLY COMPRISING A NON-CARBONATED BLOWER TURBOREACTOR AND A PENSION PYLON
    FR3070428A1|2019-03-01|INSERT FOR FIXING A COMPONENT ON A TURBOMACHINE SUPPORT
    同族专利:
    公开号 | 公开日
    WO2017109408A1|2017-06-29|
    FR3045713B1|2020-09-18|
    CN108474259B|2020-10-09|
    US10619486B2|2020-04-14|
    EP3394399B1|2021-07-07|
    US20190010807A1|2019-01-10|
    EP3394399A1|2018-10-31|
    CN108474259A|2018-08-31|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3892612A|1971-07-02|1975-07-01|Gen Electric|Method for fabricating foreign object damage protection for rotar blades|
    GB2298653A|1995-03-10|1996-09-11|United Technologies Corp|Electroformed sheath|
    EP1032749A1|1997-11-19|2000-09-06|Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh|Rotor with integrated blading|
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    EP2299123A2|2009-09-02|2011-03-23|United Technologies Corporation|Composite airfoil with locally reinforced tip region|
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    GB201507281D0|2015-04-29|2015-06-10|Composite Technology & Applic Ltd|Methods and systems for bonding|GB201814315D0|2018-09-04|2018-10-17|Rolls Royce Plc|Gas turbine engine having optimized fan|
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    JP2021148023A|2020-03-17|2021-09-27|三菱重工業株式会社|Composite material blade, rotary machine, and method for molding composite material blade|
    法律状态:
    2016-12-02| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-23| PLSC| Publication of the preliminary search report|Effective date: 20170623 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1563009A|FR3045713B1|2015-12-21|2015-12-21|ATTACK EDGE SHIELD|FR1563009A| FR3045713B1|2015-12-21|2015-12-21|ATTACK EDGE SHIELD|
    EP16831500.0A| EP3394399B1|2015-12-21|2016-12-21|Blade, associated fan and turbojet engine|
    US16/064,219| US10619486B2|2015-12-21|2016-12-21|Blade, associated fan and turbojet engine|
    PCT/FR2016/053608| WO2017109408A1|2015-12-21|2016-12-21|Blade, associated fan and turbojet engine|
    CN201680079056.8A| CN108474259B|2015-12-21|2016-12-21|Blade, associated fan and turbojet engine|
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