• 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), which comprises a lower vane (34) and an extrados vane (36), each extending in height and length, connected to each other on their height, the lower vane (34) having a greater length than the extrados vane (36) on a first segment (S1) of the shield of leading edge (32), and a length equal to or less than the extrados fin (36) on a second segment (S2) of the leading edge shield (32).
    公开号:FR3045710A1
    申请号:FR1563004
    申请日:2015-12-21
    公开日:2017-06-23
    发明作者:Jeremy Guivarc'h；Alain Jacques Michel Bassot；Gerald Diogo；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. For this reason, the intrados vane typically has, over the entire height of the shield, a greater length than the extrados vane, since the underside of the blade is more exposed to impacts. However, particularly on the rotating blades, this extra length of the intrados vane has the disadvantage of significantly increasing the mass of the shield, as well as its inertia around an axis aligned with the direction of height.
    The present disclosure aims to remedy these drawbacks by proposing a leading edge shield for a turbomachine blade which makes it possible to offer appropriate protection to the underside of this blade with reduced mass and inertia.
    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 metal material and includes an extrados wing and an extrados winglet, each extending in height and in length and connected to each other on their height, the intrados vane has a greater length than the fin extrados on a first segment of the leading edge shield, but a length equal to or less than the fin extrados on a second segment of the leading edge shield.
    Thanks to these provisions, it is possible to reduce the mass and the inertia of the shield when the blade body, intrados side, is less exposed to the impacts and / or less affected by them under said second segment of the shield that under said first segment.
    Said first segment of the shield may extend over at least 60% of the height of the intrados and extrados fins. In order to continue to provide sufficient protection of the underside, in said second segment of the shield the depth of the lower wing may remain equal to or greater than 70% of the depth of the extrados fin, or even 85%.
    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 made of a fiber-reinforced polymer matrix composite material, the leading edge shield being made of a material having better resistance to point impacts than the composite material of the blade body, and the first segment of the the leading edge shield being closer to the blade root than the second segment of the leading edge shield.
    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; FIGS. 2A and 2B are diagrammatic perspective views of the intrados and extrados side, respectively, of a rotating blade of the fan of the turbojet engine of FIG. 1 according to an embodiment of the blade; and FIGS. 3 and 4 are partial sectional views of the blade of FIGS. 2A and 2B along the planes III-III and IV-IV, respectively.
    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 a central axis X, aerodynamically profiled so as to impulse the air by their rotation and surrounded by a fan casing 50. Thus, as illustrated in Figures 2A, 2B, 3 and 4, each blade 16 has a leading edge 18, a trailing edge 20, an intrados 22 , an upper surface 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 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.
    The leading edge shield 32 has a lower vane 34, an upper vane 36, each of which extends in height over a height H of the shield 32 and a thicker central section 38 for overlapping an edge of the body. vane 30 and connecting the lower vane 34 and the extrados vane 36 on this height H. The intrados and extrados fins 34, 36 ensure the positioning of the shield 32 on the vane body 30. The lower and upper fins 34, 36 each have a free edge 40, 42 and each extend in length of the central section 38 to the corresponding free edge 40, 42.
    The relative wind normally having a certain angle of attack with respect to the leading edge 18, the intrados of the blade 16 is more exposed to impacts near the leading edge 18 than the upper surface. For this reason, in the illustrated embodiment, in a first segment SI of the leading edge shield 32 adjacent to the blade root 28, and extending over at least 60%, even 75% of the height H of leading edge shield, the length I of the intrados vane 34, measured from the leading edge 18 to the free edge 40, is greater than the length L of the extrados vane 36, measured from the leading edge 18 to the corresponding free edge 42, as shown in FIG.
    However, thanks to twisting of the vane and / or the casing 50, whose inlet may be narrower than the blower 14, is less exposed to high energy impacts. Thus, the length I of the intrados vane 34 can be reduced to become equal to or less than the length L of the extrados vane 36 in a second segment S2 of the leading edge shield 32, closer to the head of the vane. blade 26 as the blade root 28, as shown in Figure 4. Thus, the mass and especially the inertia of the shield 32 can be reduced without significantly affecting negatively their protection by the same leading edge shield 32 In this second segment S2 of the leading edge shield 32, the length I of the intrados vane 34 may remain equal to or greater than 70% or even 85% of the length L of the extrados fin 36.
    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 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.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Leading edge shield (32) for turbomachine blade (16), said leading edge shield (32) having a lower vane (34) and an extrados vane (36), each extending in height and in length, connected to each other on their height, the lower vane (34) having a greater length than the extrados vane (36) on a first segment (SI) of the leading edge shield (32), and a length equal to or less than the extrados fin (36) on a second segment (S2) of the leading edge shield (32).
    [2" id="c-fr-0002]
    The leading edge shield (32) according to claim 1, wherein said first segment (SI) of the shield (32) extends over at least 60% of the height of the lower and upper fins (34,36). .
    [3" id="c-fr-0003]
    A leading edge shield (32) according to any one of the preceding claims, wherein in said second segment (S2) of the shield the length of the intrados vane (34) remains equal to or greater than 70%, even 85% of the length of the extrados vane.
    [4" id="c-fr-0004]
    4. Shield (32) according to any one of the preceding claims, being made of metallic material.
    [5" id="c-fr-0005]
    A blade (4) extending in height from a blade root (28) to a blade head (26) and comprising a blade body (9) and a leading edge shield (32). ) according to any one of the preceding claims assembled on the blade body (30), the blade body (9) being made of fiber-reinforced polymer matrix composite material, and the leading edge shield ( 32) being made of a material having better resistance to point impacts than the composite material of the blade body (9).
    [6" id="c-fr-0006]
    6. blade (4) according to claim 5, wherein the first segment (SI) of the leading edge shield (32) being closer to the blade root (28) than the second segment (S2) of the shield of leading edge (32).
    [7" id="c-fr-0007]
    7. A turbomachine comprising a plurality of vanes (16) according to any one of claims 5 or 6.
    [8" id="c-fr-0008]
    A blower (14) comprising a plurality of blades (16) according to any one of claims 5 or 6.
    [9" id="c-fr-0009]
    9. A turbofan engine (10) comprising a blower (14) according to claim 8.
    类似技术:
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    同族专利:
    公开号 | 公开日
    RU2018126685A|2020-01-23|
    RU2727825C2|2020-07-24|
    JP6980661B2|2021-12-15|
    CN108474258B|2021-05-28|
    JP2018538481A|2018-12-27|
    CA3009452A1|2017-06-29|
    FR3045710B1|2018-01-26|
    WO2017109404A1|2017-06-29|
    EP3394397A1|2018-10-31|
    BR112018012740A2|2018-12-04|
    US20190024512A1|2019-01-24|
    CN108474258A|2018-08-31|
    RU2018126685A3|2020-05-29|
    EP3394397B1|2019-10-02|
    US10934851B2|2021-03-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2014196987A2|2012-06-21|2014-12-11|United Technologies Corporation|Hybrid metal fan blade|
    WO2014149098A2|2013-03-15|2014-09-25|United Technologies Corporation|Hollow fan blade with extended wing sheath|WO2020169938A1|2019-02-21|2020-08-27|Safran Aircraft Engines|Method for repairing a turbomachine rotor blade|
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    FR2741590B1|1995-11-29|1998-01-30|Eurocopter France|BLADE WITH REINFORCED PROTECTION AGAINST LIGHTNING, FOR ROTOR OF A GIRAVION|
    JPH11182204A|1997-12-15|1999-07-06|Toshiba Corp|Moving blade for turbine|
    FR2867096B1|2004-03-08|2007-04-20|Snecma Moteurs|METHOD FOR MANUFACTURING A REINFORCING LEAK OR RELEASING EDGE FOR A BLOWER BLADE|
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    US7736130B2|2007-07-23|2010-06-15|General Electric Company|Airfoil and method for protecting airfoil leading edge|
    FR2921099B1|2007-09-13|2013-12-06|Snecma|DAMPING DEVICE FOR DRAWINGS OF COMPOSITE MATERIAL|
    EP2072757A1|2007-12-20|2009-06-24|Siemens Aktiengesellschaft|Erosion protection shield for a rotating blade|
    EP2392422B1|2009-01-22|2013-08-21|IHI Corporation|Method of manufacturing member for reinforcing front edge of fan blade|
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    US20120021243A1|2010-07-23|2012-01-26|General Electric Company|Components with bonded edges|
    FR2965202B1|2010-09-28|2012-10-12|Snecma|PROCESS FOR MANUFACTURING A PIECE AND COMPOSITE MASSIVE PART OBTAINED BY THIS METHOD|
    FR2970668B1|2011-01-24|2013-01-18|Snecma|PROCESS FOR MAKING A METAL REINFORCEMENT|
    FR2972124B1|2011-03-01|2014-05-16|Snecma|METHOD FOR PRODUCING A METAL PIECE SUCH AS A TURBOMACHINE BLADE REINFORCEMENT|
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    JP6083112B2|2012-01-30|2017-02-22|株式会社Ihi|Aircraft jet engine fan blades|
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    US9140130B2|2012-03-08|2015-09-22|United Technologies Corporation|Leading edge protection and method of making|
    US10724379B2|2013-03-15|2020-07-28|Raytheon Technologies Corporation|Locally extended leading edge sheath for fan airfoil|
    US10539025B2|2016-02-10|2020-01-21|General Electric Company|Airfoil assembly with leading edge element|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
    FR1563004A|FR3045710B1|2015-12-21|2015-12-21|ATTACK SHIELD|
    FR1563004|2015-12-21|FR1563004A| FR3045710B1|2015-12-21|2015-12-21|ATTACK SHIELD|
    EP16831497.9A| EP3394397B1|2015-12-21|2016-12-21|Leading edge sheath|
    RU2018126685A| RU2727825C2|2015-12-21|2016-12-21|Front edge protective element|
    BR112018012740-0A| BR112018012740A2|2015-12-21|2016-12-21|lead edge shield, shovel, turbomachine, fan, and turbofan|
    CA3009452A| CA3009452A1|2015-12-21|2016-12-21|Leading edge shield|
    JP2018532743A| JP6980661B2|2015-12-21|2016-12-21|Leading edge shield|
    US16/064,473| US10934851B2|2015-12-21|2016-12-21|Leading edge shield|
    PCT/FR2016/053603| WO2017109404A1|2015-12-21|2016-12-21|Leading edge shield|
    CN201680078441.0A| CN108474258B|2015-12-21|2016-12-21|Main edge shield|
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