• 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 rotor blade (10) for an aircraft turbomachine, this blade having an axis (A) of rotation once secured to a rotor and a stacking axis (X) and having a blade (16) extending between an inner platform (19) and an outer platform (20) which carries at least one protruding wiper (31, 32), said blade having a lower surface (16a) and an upper surface (16b) and said outer platform having lateral lower edges (22) and extrados (21), located respectively on the side of said intrados (16a) and extrados (16b), and configured to cooperate in complementarity with complementary lateral edges (21, 22) of adjacent blades, these lateral edges each comprising an anti-wear coating (36), characterized in that the anti-wear coating of the intrados lateral edge extends on a wall (40a) of a first wall (40) which is substantially rectilinear, and on a wall (42a). ) a second wall (42) extending at least partly in said wiper (31) and is inclined with respect to said first wall in a direction substantially parallel to a transverse axis (Z) of extension of the wiper.
    公开号:FR3077600A1
    申请号:FR1851070
    申请日:2018-02-08
    公开日:2019-08-09
    发明作者:Marc-Etienne Loisel Bruno；Aline Marie Deflandre Stephanie；Jacques Delcoigne Eric；Denis Daniel Limousin Franck；Nicole Person Laetitia
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Aircraft turbomachine dawn
    TECHNICAL FIELD The present invention relates to the general field of the manufacture of rotor blades for an aircraft turbomachine.
    STATE OF THE ART [0002] Conventionally, an axial turbine of a turbomachine consists of a succession of axial stages (along the axis of circulation of gas flows) arranged in series. Each stage comprises a movable impeller with blades forming a rotor and a bladed distributor forming a stator. The movable wheel is rotated opposite the corresponding distributor.
    In the present application, the upstream and downstream are defined with respect to the normal direction of flow of the air flows (from upstream to downstream) through the turbomachine. The axis of the turbomachine is the axis of rotation of the main rotor of the turbomachine. The axial direction corresponds to the direction of the axis of the turbomachine, and a radial direction is a direction perpendicular to the axis of the turbomachine and intersecting this axis. Likewise, an axial plane is a plane containing the axis of the turbomachine, and a radial plane is a plane perpendicular to this axis. The interior and exterior adjectives are used with reference to a radial direction so that the interior part of an element is, in a radial direction, closer to the axis of the turbomachine than the exterior part of the same element. The stacking axis of a blade is the axis perpendicular to the axis of the turbomachine, which passes through the center of gravity of the innermost section of the blade of the blade (ie, the most close to the axis of the turbomachine). Typically, a turbomachine blade comprises a blade extending along the stacking axis of the blade, between the proximal and distal (i.e., inner and outer) ends of the blade.
    The movable wheel conventionally consists of an annular disc centered on the axis of rotation of the wheel, on which are fixed a plurality of vanes.
    An example of a blade is shown in Figure 1. A blade of this type is described in patent document FR-B1-2 985 759. This blade 10 comprises a blade 16 extending along the axis d stack X of the blade, between the proximal 10A and distal 10B ends of the blade 10. At its proximal end 10A, the blade comprises a platform 19 and a foot 12 by which it is fixed to the disc (not shown) . At its distal end 10B, the blade 10 has a heel
    14. When several blades 10 are fixed on the disc, their heels 14 are arranged edge to edge so as to form a circumferential crown delimiting a surface of revolution around the axis A of rotation of the wheel. The function of this ring is in particular to delimit the external surface of the flow stream of the gas flows circulating between the blades 16 and to limit gas leaks at the level of the distal end 10B of the blades 10.
    The heel 14 comprises a platform 20 externally delimiting the flow stream of the gas flowing between the blades 16, and having opposite lateral edges 21, 22. The platform 20 comprises an upstream part 24 called “upstream spoiler” and a downstream part 28 called “downstream spoiler”. The heel 14 also includes upstream 31 and downstream 32 sealing wipers extending radially outward from the external face of the platform 20. These wipers have a general circumferential or transverse orientation relative to the axis of wheel rotation. Each of the side edges 21, 22 of the platform has, between the upstream wipers 31 and downstream 32, a profile substantially in "Z".
    When several blades 10 are fixed on the disc, the upstream 31 and downstream 32 wipers are arranged edge to edge so as to form a rotary ring of axis A, this ring being contained substantially in a radial plane. The function of such a ring is in particular to limit the clearance existing between the blades 10 and a casing (not shown) which surrounds the blades 10 in order to limit the gas leaks at this location. This casing carries an abradable annular coating which can cooperate by friction with the wipers of the blades in order to limit these leaks by labyrinth effect.
    In order to dampen the vibrations to which the blades 10 are subjected in operation, the blades 10 are mounted on their disc with a torsional stress around their stacking axis X. The geometry of the heels 14 is such that each blade 10 is put in torsional stress by pressing on the neighboring blades 10 mainly along the lateral faces 34 of the upstream wiper 31, within the framework of the blade geometry shown. The lateral faces 34 therefore define the inter-blade contact surfaces and are the site of significant friction during the operation of the turbomachine. To be protected against wear, the side faces 34 are provided with a coating or insert made of friction-resistant material. It may, for example, be a material sold under the brand name Stellite®. This anti-wear coating 36 is better visible in FIG. 2.
    Conventionally, this anti-wear coating 36 is deposited on the side faces 34 by welding, for example by drop welding, involving the creation of an electric arc for the melting of the material. This is often a manual operation, the Stellite® type alloy being in the form of a liquid drop during deposition.
    The Stellite® alloy is a steel alloy with a high content of chromium (Cr) and cobalt (Co). It can also contain a small amount of tungsten (W) or molybdenum (Mo) and a small amount of carbon (C). The Stellite® alloy is not forgeable and must either be cast or fixed by welding on an object of which it forms a part or into which it is inserted.
    We noticed the appearance of cracks after depositing the drop of Stellite® on blades, which induces the scrapping of these blades.
    The present invention provides a simple, effective and economical solution to this problem.
    PRESENTATION OF THE INVENTION The present invention provides a rotor blade for an aircraft turbomachine, this blade having an axis of rotation once secured to a rotor and a stacking axis and comprising a blade extending between an internal platform and an external platform which carries at least one protruding wiper, said blade comprising a lower surface and an upper surface and said external platform comprising lower and upper side edges, respectively located on the side of said lower surface and upper surface, and configured for cooperate by complementarity, and in particular by interlocking, with complementary lateral edges of adjacent blades, these lateral edges each comprising an anti-wear coating, characterized in that the anti-wear coating of the lateral edge situated on the side of said lower surface s' extends over a wall of a first low wall which is substantially straight and over a wall of a second low wall which extends less partially in said wiper and is inclined relative to said first wall in a direction substantially parallel to a transverse axis of elongation of the wiper.
    The anti-wear coating is thus deposited on low walls which stiffen the blade and limit the risk of the appearance of cracks during this deposit. These walls make it possible to thicken the areas of application of the anti-wear coating as needed, and thus ensure better heat dissipation during deposition, thereby reducing the risk of cracks forming.
    Furthermore, the shape of the walls is adapted on the one hand to limit their size and that of the coating, and to prevent the latter from coming into contact with the abradable coating mentioned above extending around the wheel and in which the heel wipers are intended to form annular grooves in operation. In the case where the wipers are inclined relative to a plane perpendicular to the axis of rotation of the wheel, and where the walls of each blade are aligned (and therefore not inclined relative to each other), the second low wall could overflow beyond the wiper and generate unwanted contact with the abradable coating, thus resulting in a widening of the corresponding groove and a risk of increased gas leaks in this area.
    The dawn according to the invention may include one or more of the characteristics below, taken in isolation from one another or in combination with each other:
    said first wall has a substantially constant thickness E1,
    said second wall has a thickness E2 less than E1,
    - the anti-wear coating of the lateral edge located on the side of said upper surface extends over a wall of a third low wall, this third low wall having a thickness E3 similar to E1,
    - each wall thickness is measured in a direction substantially perpendicular to a surface forming the wall, or in a direction substantially perpendicular to a median longitudinal plane or an axis of extension of the corresponding wall,
    - said wall of said second wall extends over 20 to 50% of the height of the wiper in which it extends, measured along the stacking axis,
    - said wiper comprises two opposite longitudinal ends, one of which comprises at least partially said wall of said second wall, and the other of which includes an additional thickness in a direction perpendicular to said axis of elongation,
    said wiper is inclined relative to a plane perpendicular to said axis of rotation,
    - the dawn comprises two projecting wipers and said first low wall is located between these wipers, and
    - Said second low wall has a first end connected to one end of said first low wall and a second free end situated to the right of said lower side edge.
    The present invention also relates to a rotor wheel for an aircraft turbomachine, comprising a disc carrying at its periphery an annular row of vanes as described above.
    The present invention also relates to an aircraft turbomachine, comprising at least one blade or a wheel as described above.
    BRIEF DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings in which:
    FIG. 1 is a schematic perspective view of a turbine wheel vane for an aircraft turbomachine,
    FIG. 2 is a diagrammatic view on a larger scale of part of another turbine wheel blade for an aircraft turbomachine,
    FIG. 3 is a schematic side view of a rotor blade according to the invention,
    - Figure 4 is a schematic top view of the blade of Figure 3,
    - Figures 5 and 6 are detail views of Figure 4, Figure 6 illustrating one of the features of the invention as opposed to Figure 5 which therefore does not illustrate the invention, and
    - Figure 7 is a schematic top view of the blade of Figure 3, with a cross section.
    DETAILED DESCRIPTION OF AN EMBODIMENT [0021] The invention applies to a blade 10 of a moving wheel as described above with reference to FIGS. 1 and 2.
    The blade 10 comprises at least one blade 16 which extends between two platforms, respectively internal 19 and external 20. The internal platform 19 is connected to the radially internal end of the blade and the external platform 20 is connected at the radially outer end of the blade and comprises coatings 36 of anti-wear material.
    Figures 3, 4, 6 and 7 illustrate an embodiment of the invention.
    According to the invention, the anti-wear coating 36 of the side edge 22 located on the underside 16a of the blade 16 extends over a wall 40a of a first wall 40 which is located between the wipers 31 , 32, and on a wall 42a of a second low wall which extends at least in part into the wiper 31. The low walls 40, 42 form an integral part of the platform 20. As can be seen in FIG. 3, the wall 42a extends over approximately 20 to 50% of the height of the wiper 31, measured along the stacking axis X.
    The first wall 40 is substantially straight and has a downstream end connected to a boss 44 projecting from the outside face of the platform 20. This boss has a general shape in blade profile and forms an extension of the blade 16 radially outward from the platform 20.
    The second wall 42 is substantially straight and at its downstream end connected to the upstream end of the first wall 40. This second wall 42 is inclined relative to the first wall 40 in a direction substantially parallel to a transverse axis Z d ' elongation of the wiper 31. In other words, the second wall 42 is substantially parallel to the wiper 31 and the first wall 40 is inclined relative to the wiper 31 and to the second wall 42.
    Figure 7 is a cross-sectional view of the blade, the cutting plane passing substantially through the walls 40, 42 and the boss 44, and being substantially parallel to the plane of the platform 20. Figure 7 shows the thicknesses E1, E2 of the walls 40, 42 as well as their angle of inclination a, which is for example between 120 and 150 °. In other words, the second wall 42 forms a substantially zero angle with the wiper 31 or the Z axis, and the first wall 40 is inclined relative to the wiper 31 or the Z axis by an angle between 30 and 60 ° .
    A This angle is also visible in Figure 6 which illustrates walls 40, 42 inclined relative to each other, as opposed to Figure 5 which shows aligned walls. In the latter case, and as explained in the foregoing, the low wall 42 may extend beyond the wiper and the anti-wear coating which it wears is capable of widening the groove 46 formed in the abradable coating which surrounds the blade, due to the rotation of the disc carrying this blade.
    The groove 46 is here partially represented by a hatched area whose dimensions are a function of the maximum dimensions of the wiper 31. In the example shown, the wiper 31 comprises a longitudinal end situated on the side of the lower surface 16a and in which extends the wall 42, and an opposite longitudinal end which is located on the side of the upper surface of the blade. This last end is thickened in a direction perpendicular to the axis of elongation of the wiper and has a general shape called elephant's foot. This thickened end defines the largest thickness of the wiper and therefore the thickness of the groove 46. This groove is annular and therefore intended to extend all around the wheel carrying the blade.
    In the example shown, the walls 40, 42 define therebetween and with a lug 48 present on the wall 40a of the wall 40, a first recess 50 intended to receive the anti-wear coating 36.
    On the upper surface of the blade 16, the anti-wear coating is located on a wall 52a of a third wall 52 which has a general orientation substantially parallel to the wall 40. The wall 52 has a thickness E3. The wall 52 defines with two lugs 54, 56 present at opposite ends of the wall 52a, a second recess 58 intended to receive the anti-wear coating 36.
    The thickness of a wall is measured in a direction substantially perpendicular to a surface forming the wall or to a median longitudinal plane or an axis of elongation of this wall. The thickness of the wall 42 can be measured in a direction substantially perpendicular to the axis Z. The extension axes of the walls 40, 42 and 52 are respectively designated by the references 40b, 42b and 52b in FIG. 7.
    The thicknesses E1, E2 and E3 are for example between 1 and 3mm. The thickness E2 of the low wall 42 is preferably less than that E1 of the low wall 40. The thickness E1 is for example of the order of 2mm and the thickness E2 is for example of the order of 1.5mm. The thickness E3 is preferably similar to the thickness E1, and is for example of the order of 2mm. These thicknesses ensure good mechanical strength and avoid the formation of cracks when depositing the stellite.
    Dawn can be made as follows. It is first made gross foundry. The recesses 50, 58 are then filled with the anti-wear coatings 36, for example by depositing the molten Stellite® material, which are located on the walls of the walls. The blade can then undergo a machining operation 5 to bring it to the desired ribs. During this last operation, the coverings 36 can be machined, as well as the lugs and walls which delimit the recesses for receiving these coverings.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. rotor blade (10) for an aircraft turbomachine, this blade having an axis (A) of rotation once secured to a rotor and a stacking axis (X) and comprising a blade (16) s' extending between an internal platform (19) and an external platform (20) which carries at least one protruding wiper (31, 32), said blade comprising a lower surface (16a) and an upper surface (16b) and said external platform comprising edges lateral intrados (22) and extrados (21), located respectively on the side of said intrados (16a) and extrados (16b), and configured to cooperate by complementarity with lateral edges (21,22) complementary to adjacent blades, these lateral edges each comprising an anti-wear coating (36), characterized in that the anti-wear coating on the lower side edge extends over a wall (40a) of a first low wall (40) which is substantially straight, and over a wall (42a) of a second low wall (42) which extends at least in part da ns said wiper (31) and is inclined relative to said first wall in a direction substantially parallel to a transverse axis (Z) of elongation of the wiper.
    [2" id="c-fr-0002]
    2. Dawn (10) according to the preceding claim, wherein said first wall (40) has a substantially constant thickness E1.
    [3" id="c-fr-0003]
    3. Dawn (10) according to the preceding claim, wherein said second wall (42) has a thickness E2 less than E1.
    [4" id="c-fr-0004]
    4. Dawn (10) according to claim 2 or 3, wherein the anti-wear coating (36) of the lateral edge located on the side of said upper surface extends over a wall (52) of a third wall (52), third wall having a thickness E3 similar to E1.
    [5" id="c-fr-0005]
    5. Dawn (10) according to one of the preceding claims, in which said wall (42a) of said second wall (42) extends over 20 to 50% of the height of the wiper (31) in which it extends , measured along the stacking axis (X) ·
    [6" id="c-fr-0006]
    6. Dawn (10) according to one of the preceding claims, in which said wiper (31) comprises two opposite longitudinal ends, one of which at least partly comprises said wall (42a) of said second wall (42), and the other of which includes an allowance in a direction perpendicular to said axis of elongation (X).
    [7" id="c-fr-0007]
    7. Dawn (10) according to one of the preceding claims, wherein said wiper (31) is inclined relative to a plane perpendicular to said axis of rotation (A).
    [8" id="c-fr-0008]
    8. Dawn (10) according to one of the preceding claims, wherein said second wall (42) has a first end connected to one end of said first wall (40) and a second free end located to the right of said lower side edge.
    [9" id="c-fr-0009]
    9. Rotor wheel for an aircraft turbomachine, comprising a disc carrying at its periphery an annular row of blades (10) according to one of the preceding claims.
    [10" id="c-fr-0010]
    10. Aircraft turbomachine, comprising at least one blade (10) according to one of claims 1 to 8 or a wheel according to claim 9.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2951397B1|2019-03-06|Turbomachine rotor blade
    EP2805020B1|2016-04-06|Turbomachine rotor blade and corresponding turbomachine
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    CA2652679C|2016-05-10|Blades for turbomachine impeller, with a groove for cooling
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    WO2013001240A1|2013-01-03|Labyrinth seal for gas turbine engine turbine
    EP3749838A1|2020-12-16|Vane for an aircraft turbine engine
    FR3079847A1|2019-10-11|METHOD FOR MANUFACTURING A METALLIC AIRBORNE ELEMENT OF AN AIRCRAFT TURBOMACHINE
    FR2965843A1|2012-04-13|ROTOR FOR TURBOMACHINE
    FR3107079A1|2021-08-13|AIRCRAFT TURBOMACHINE DAWN
    FR3077601A1|2019-08-09|AIRCRAFT TURBINE TURBINE
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    FR3079848A1|2019-10-11|METHOD FOR DEPOSITING ANTI-WEAR MATERIAL ON A TANK ELEMENT FOR AN AIRCRAFT TURBOMACHINE
    FR3045709A1|2017-06-23|AUBE DE SOUFFLANTE
    FR3084399A1|2020-01-31|MOBILE VANE FOR A WHEEL OF A TURBOMACHINE
    FR3090032A1|2020-06-19|BLADE FOR TURBOMACHINE WHEEL
    FR3011035A1|2015-03-27|EXHAUST CASE COMPRISING A FLUID EVACUATION DEVICE, AND TURBOMACHINE
    FR3101107A1|2021-03-26|DAWN FOR AN AIRCRAFT TURBOMACHINE
    FR3074813A1|2019-06-14|METHOD FOR DEPOSITING ANTI-WEAR MATERIAL ON A TANK ELEMENT FOR AN AIRCRAFT TURBOMACHINE
    FR3067625A1|2018-12-21|METHOD FOR MANUFACTURING A ROTOR BLADE FOR AN AIRCRAFT TURBOMACHINE
    同族专利:
    公开号 | 公开日
    US20200408099A1|2020-12-31|
    FR3077600B1|2020-03-06|
    EP3749838A1|2020-12-16|
    WO2019154734A1|2019-08-15|
    CN111742115A|2020-10-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2985759A1|2012-01-17|2013-07-19|Snecma|MOBILE AUB OF TURBOMACHINE|
    US20150369058A1|2013-02-01|2015-12-24|Snecma|Turbomachine rotor blade|
    EP3006673A1|2014-10-07|2016-04-13|Siemens Aktiengesellschaft|Method for and arrangement for measuring shrouded blade interlock wear|WO2021156559A1|2020-02-07|2021-08-12|Safran Aircraft Engines|Vane for an aircraft turbine engine|
    EP3865665A1|2020-02-11|2021-08-18|MTU Aero Engines AG|Blade for a turbomachine with a shroud|
    法律状态:
    2019-01-23| PLFP| Fee payment|Year of fee payment: 2 |
    2019-08-09| PLSC| Publication of the preliminary search report|Effective date: 20190809 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 3 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 4 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1851070|2018-02-08|
    FR1851070A|FR3077600B1|2018-02-08|2018-02-08|DAWN OF AIRCRAFT TURBOMACHINE|FR1851070A| FR3077600B1|2018-02-08|2018-02-08|DAWN OF AIRCRAFT TURBOMACHINE|
    PCT/EP2019/052521| WO2019154734A1|2018-02-08|2019-02-01|Vane for an aircraft turbine engine|
    US16/968,515| US20200408099A1|2018-02-08|2019-02-01|Vane for an aircraft turbomachine|
    CN201980014194.1A| CN111742115A|2018-02-08|2019-02-01|Blade for an aircraft turbine engine|
    EP19702278.3A| EP3749838A1|2018-02-08|2019-02-01|Vane for an aircraft turbine engine|
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