• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    Part comprising a wall which comprises a first zone (541), a second zone (542), and a transition zone (54t) located between the first zone (541) and the second zone (542), a network of riblets being formed on the first zone (541), the second zone (542), and also on the transition zone (54t), so as to reduce the drag of the room during the circulation of a flow of air along the said wall; the height, width, and spacing of the riblets formed on the transition zone (54t) moving along said transition zone (54t) so as to pass the height, width, and spacing of the formed riblets on the first zone at a first end of the transition zone, at the height, the width, and the spacing of the riblets formed on the second zone (542) at a second end of the transition zone (54t); the transition zone (54t) comprising a central portion on which the riblets comprise on the one hand the height and the width which are respectively equal to the height and the width of the riblets on the first zone (541), and secondly a spacing equal to the spacing of the riblets of the second zone (542).
    公开号:FR3053074A1
    申请号:FR1656025
    申请日:2016-06-28
    公开日:2017-12-29
    发明作者:William Henri Joseph Riera；Jerome Jean-Yves Talbotec；Julien Roger Marcel Marty
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Field of the invention
    The present invention relates to a part of a turbomachine for an aircraft which is adapted to reduce the drag of said piece created by the passage of an air flow along said part.
    More particularly, the invention relates to a blade of the turbomachine comprising riblets, or a wall of the turbomachine defining an air flow vein inside said turbomachine which comprises riblets.
    State of the art
    In order to reduce the drag of the vanes of a rectifier of a secondary flow of an aircraft turbomachine, it is known to form a network of riblets on the underside and / or the extrados of the vanes of said secondary flow rectifier.
    The riblets are ribs extending along the axis of the turbomachine on the underside and the upper surface of the blades, so that said ribs are oriented parallel to the direction of the air flow.
    The riblets can have various forms. The riblets may for example have a triangular shape, or a square shape, in a section normal to the axis of the turbomachine.
    The riblets generally have a height and a width of the order of 1 to 100 pm. In addition, two neighboring riblets may be spaced from a distance of 0 to 50 μm.
    According to a first known solution, the riblets have a shape that is constant along the intrados and extrados. The shape of a riblet also includes the width and height of said riblet.
    This first known solution offers the advantage of facilitating the manufacture of the riblets on the blades.
    Because of the shape of the blade profiles, the flow velocity of the air flow along the upper surface and the lower surface of the vanes is not constant.
    However, for a given form, the reduction of the drag by riblets depends on the speed of the flow of air flowing along the wall on which said riblets are formed.
    In other words, some forms of riblets can effectively reduce drag when the flow velocity of the airflow is low, while other forms of riblets can effectively reduce drag when the flow velocity of the flow of air is low. air is high.
    Thus, such a first solution does not effectively reduce blade drag.
    In order to take into account the variation of the velocity of the flow of air along the extrados and the intrados, a second known solution consists in separating the intrados and / or the extrados in at least two zones, a first zone being located near the leading edge of the dawn while a second zone is located near the trailing edge, and forming different shaped riblets on the first zone and the second zone . The shape of the riblets on the first zone and the second zone is constant.
    A transition zone is located between the first and second zones to allow the shape of the riblets to evolve between the shape of the riblets on the first zone and the shape of the riblets on the second zone.
    Such a second solution offers the advantage of being able to adapt the shape of the riblets along the wall of the blades according to the flow velocity of the air flow.
    However, because of the variation in the shape of the riblets, the second known solution greatly complicates the manufacture of the riblets.
    In particular, manufacturing is made more complex because of the transition zone on which the shape of the riblets evolves.
    Thus, none of the known solutions makes it possible both to reduce drag effectively, and at the same time to simplify the method of manufacturing the riblets.
    General presentation of the invention
    An object of the invention is to propose a solution that makes it possible both to effectively reduce the drag created by the circulation of an air flow against a wall by adapting locally the shape of the riblets formed on said wall to the speed flow of air flow, and both to have a method of manufacturing riblets on said wall which is simple to implement. For this purpose, there is provided a part of a turbomachine for an aircraft comprising a wall which comprises a first zone, a second zone, and a transition zone located between the first zone and the second zone, a network of riblets being formed. on the first zone, the second zone, and also on the transition zone, so as to reduce the drag of the room during the circulation of an air flow along said wall; the riblets comprising a vertex, a height, a width, and a distance which corresponds to the distance between the vertices of neighboring riblets; the height, the width, and the spacing of the riblets formed on the first zone being constant on the first zone; the height, the width, and the spacing of the riblets formed on the second zone being constant on the second zone; the ratio between the spacing and the height of the riblets formed on the first zone being equal to the ratio between the spacing and the height of the riblets formed on the second zone; the height, the width, and the spacing of the riblets formed on the transition zone evolving along said transition zone so as to pass from the height, the width, and the spacing of the riblets formed on the first zone to a first end of the transition zone, at the height, the width, and the spacing of the riblets formed on the second zone at a second end of the transition zone; characterized in that the transition zone comprises a central portion located between the first and the second end on which the riblets comprise on the one hand the height and the width which are respectively equal to the height and the width of the riblets of the first zone , and on the other hand a spacing equal to the spacing of the riblets of the second zone.
    The part according to the invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combinations: the piece is a turbine engine blade for an aircraft, the blade comprising a lower surface and an upper surface; riblets being located on the intrados and / or the extrados of said blade; the blade comprises a leading edge and a trailing edge, the first zone extending from the leading edge and the second zone extending from the trailing edge, the height, the width and the spacing of the riblets of the second zone being respectively greater than the height, the width and the spacing of the riblets of the first zone; the blade comprises a radial axis and an axis perpendicular to the radial axis, the riblets formed on the first zone having an angle of inclination with respect to the axis perpendicular to the radial axis which is constant on the first zone; , the riblets formed on the second zone having an angle of inclination with respect to the axis perpendicular to the radial axis which is greater than or equal to the angle of inclination of the riblets of the first zone and which is constant on the second zone, the riblets formed on the transition zone having an angle of inclination with respect to the axis perpendicular to the radial axis which evolves along said transition zone between the angle of inclination of the riblets of the first zone at the first end of the transition zone, and the angle of inclination of the riblets of the second zone at the second end of the transition zone; - the angle of inclination of the riblets of the first zone is between 0 ° and 15 °, and the angle of inclination of the riblets of the second zone is between 0 ° and 30 ° - the piece is a blade of rectifier for a secondary rectifier of a turbomachine for an aircraft. The invention also relates to an aircraft turbomachine comprising a part according to any one of the preceding characteristics. The invention also relates to an aircraft turbomachine comprising a part according to the main characteristic, in which the turbomachine comprises a primary vein, a secondary vein, a blower, and a secondary straightener located in the secondary vein, the part being a separation spout. between the primary vein and the secondary vein which is located between the blower and the secondary rectifier, the riblets being located on a portion of the separation nozzle forming an internal wall of the secondary vein. The invention also relates to a method of attenuating the drag of a workpiece created by the flow of air flow along a wall of said workpiece, said method comprising the following steps: forming a network of riblets on a first zone of the wall, the riblets comprising a vertex, a height, a width, and a spacing which corresponds to the distance between the vertices of neighboring riblets, the height, the width, and the spacing of the riblets of the first zone being constant over the entire first zone; forming a network of riblets on a second zone of the wall, the riblets comprising a vertex, a height, a width, and a distance which corresponds to the distance between the neighboring vertex vertices, the height, the width, and the spacing riblets of the second zone being constant over the entire second zone, the ratio between the spacing and the height of the riblets of the first zone being equal to the ratio between the spacing and the height of the riblets of the second zone; forming a network of riblets on a transition zone between the first zone and the second zone, the riblets comprising a vertex, a height, a width, and a distance corresponding to the distance between the vertices of neighboring riblets, the height, the width, and the spacing of the transitional zone riblets along said transition zone so as to move from the height, width, and spacing of the riblets of the first zone to a first end of the zone of transition. transition, at the height, width, and spacing of the riblets of the second zone at a second end of the transition zone, the transition zone comprising a central portion located between the first and the second end on which the riblets comprise on the one hand the height and the width which are respectively equal to the height and the width of the riblets of the first zone, and on the other hand a separation equal to the distance nts of the second zone.
    According to an independent aspect, the invention also relates to a blade of a turbomachine, for example a blade of a secondary straightener, which comprises a lower surface, an upper surface, a leading edge, a trailing edge, a top, a foot, a radial axis and an axis perpendicular to the radial axis, riblets being formed on a first zone, a second zone and a transition zone of the intrados and / or the extrados, the transition zone being located between the first zone and the second zone, the riblets formed on the first zone having an angle of inclination with respect to the axis perpendicular to the radial axis which is constant on the first zone, the riblets formed on the second zone having a angle of inclination with respect to the axis perpendicular to the radial axis which is greater than the angle of inclination of the riblets of the first zone and which is constant on the second zone, the riblets formed on the transition zone po an angle of inclination with respect to the axis perpendicular to the radial axis that is moving along said transition zone between the angle of inclination of the riblets of the first zone at a first end of the transition zone, and the angle of inclination of the riblets of the second zone at a second end of the transition zone.
    Other features, objects and advantages of the invention will appear on reading the following description of various embodiments shown in the following drawings: FIG. 1 represents part of a half-view of a turbomachine; Figure 2a shows a perspective view of a stator blade; Figure 2b shows a sectional view of the stator blade illustrated in Figure 2a; Figure 3a shows a front view of a portion of the extrados of a stator blade on which riblets are formed, only the tops of the riblets being shown in Figure 3a; Figure 3b shows a sectional view of Figure 3a along the axis A-A located at a first zone of the extrados; Figure 3c shows a sectional view of Figure 3a along Iaxe B-B located at a transition zone of the extrados; FIG. 3d represents a sectional view of FIG. 3a along the axis C-C situated at the level of the second zone; FIG. 4 represents a diagram illustrating the adaptation of the shape of the riblets on the first zone and the second zone so as to optimize the reduction of the drag along the upper surface of the blade; Figure 5 shows a front view of the upper part of the upper surface of the blade according to a variant in which the inclination of the riblets varies along said extrados, only the tops of the riblets being shown in Figure 5; FIG. 6 represents a possible implementation of a process for attenuating the drag of a part according to the invention.
    Description of the invention
    As represented in FIG. 1, a turbomachine 1 for aircraft has a main direction extending along a longitudinal axis Ω, and creates two separate air flows from an air stream 2 admitted at the inlet of the aircraft. said turbomachine 1.
    The air flow 2 admitted at the inlet of the turbomachine 1 is first compressed by a fan 3. At the outlet of the fan 3, the air flow 2 is then separated into two distinct streams, a first stream forming a stream primary 21 which circulates in a primary stream 11 of the turbomachine 1, and a second stream forming a secondary stream 22 which circulates in a secondary vein 12 of said turbomachine 1.
    The separation of the primary stream 21 and the secondary stream 22 is provided by a separation spout 4 which is disposed downstream of the blower 3. The splitter 4 comprises a first face forming an internal wall of the primary vein, and a second face forming an inner wall of the secondary vein.
    Subsequently, the primary stream 21 is compressed by a low pressure compressor CBP and a high pressure compressor CHP, and then burned with fuel in a combustion chamber.
    The secondary flow 22 is directed towards a secondary rectifier 5 located in the secondary vein 12 in order to straighten said secondary flow 22 with respect to the axis Ώ of the turbomachine 1 and to compress said secondary flow 22.
    As represented in FIGS. 2a and 2b, the secondary rectifier 5 is a disc formed of a plurality of rectifier vanes 50 which is centered on the axis Ω of the turbomachine 1.
    Each stator vane 50 comprises a leading edge 51 through which the secondary flow 22 comes into contact with the stator vane 50 during operation of the turbomachine 1, and a trailing edge 52 through which the secondary air flow 22 escapes from the stator vane 50. The stator vane 50 includes a lower surface 53 and an upper surface 54 which each form a wall extending between the leading edge 51 and the trailing edge 52 of the Rectifier blade 50. Rectifier blade 50 also includes a top 50a and a foot 50b. The top 50a forms the end of the blade 50 which is located radially outwardly relative to the axis Ω when said blade 50 is mounted in the turbomachine 1. The foot 50b forms the end of the blade 50 which is located radially inward with respect to the axis Ω when said blade 50 is mounted in the turbomachine 1. The top 50a is flat and is parallel to the axis Ω of the turbomachine. The stator vane 50 further comprises a radial axis Θ which is perpendicular to the axis Ω of the turbomachine 1 and to the axis of the rectifier (which coincides with the axis Ω of the turbomachine 1). The radial axis Θ forms a main axis of elongation of the stator blade 50 and connects the top 50a to the foot 50b.
    During the operation of the turbomachine 1, the secondary flow 22 comes into contact with the stator vane 50 by the leading edge 51. The secondary flow 22 bypasses the stator vane 50 by dividing in two, part of the secondary flow 22 along the intrados 53, another part of the secondary flow 22 along the extrados 54. These two parts of the flow then meet at the trailing edge 52 of the stator vane 50 where the secondary flow 22 is expelled from the dawn of rectifier 50.
    As represented in FIGS. 3a, 3b, 3c and 3d, in order to limit the drag created by the circulation of the secondary flow 22 along the extrados 54 of the stator vane 50, a network of riblets 6 is formed on the extrados 54 of said stator vane 50.
    The riblets 6 are ribs which are directed parallel to the direction of flow of the secondary air stream 22, and which are therefore directed in a direction comprising a component along the axis Ω of the turbomachine 1. The riblets 6 can be parallel to the Ω axis.
    The riblets 6 comprise a vertex S forming an upper end and a base B forming a lower end.
    Each riblet 6 comprises a height corresponding to the distance between the base B and the vertex S of the riblet 6, and a width corresponding to the width of the base B.
    The riblets 6 are spaced apart at a distance corresponding to the distance between the vertex S of a riblet 6 and the vertices S of the neighboring riblets 6. The extrados 54 comprises three zones each comprising a network of riblets 6 of different shapes. The upper surface 54 thus comprises a first zone 541 extending from the leading edge 51 and a second zone 542 extending from the trailing edge 52. The first zone 541 and the second zone 542 are separated. by a transition zone 54t located between said first and second zones 541 and 542. The transition zone 54t preferably has a length which is not greater than 5% of the length of the rope of the blade 50. the boundary between the first zone 541 and the transition zone 54t is preferably between 10% and 40% of the blade rope 50 starting from the leading edge 51, and the boundary between the second zone 542 and the transition zone 54t is preferably located between 15% and 45% of the rope from the leading edge 51.
    The rope of a dawn is a theoretical line connecting the leading edge to the trailing edge.
    As illustrated in FIG. 3a and FIG. 3b, the first zone 541 located at the level of the attacking edge 51 comprises riblets 6 which have a height H1, a gap E1, and a width L1. The spacing E1 of the riblets 6 of the first zone 541 is equal to the width L1, so that the bases B of the neighboring riblets 6 are in contact.
    The shape of the riblets 6 (their height H1, their spacing E1, and their width L1) is constant all along the first zone 541 of the extrados 54.
    As illustrated in FIG. 3a and FIG. 3d, the second zone 542 located at the trailing edge 52 comprises riblets 6 which have a height H2, a spacing E2, and a width L2. The spacing E2 of the riblets 6 of the second zone 542 is equal to the width L2, so that the bases B of the neighboring riblets 6 are in contact.
    The shape of the riblets 6 (their height H2, their spacing E2, and their width L2) is constant all along the second zone 542 of the extrados 54.
    As illustrated in FIG. 4, the shape of the riblets 6 (their height, their spacing, and their width) formed on the first zone 541 and the second zone 542 of the extrados 54 is adapted as a function of the variation of the speed of rotation. flow of the secondary air stream 22 along the extrados 54 so as to limit as much as possible the drag created by the flow of the secondary air stream 22.
    To do this, on the one hand the shape of the riblets 6 formed on the first zone 541 is adapted to obtain a maximum of drag reduction for a flow rate of the secondary air flow 22 corresponding to the average speed of the flow of secondary air 22 along the first zone 541; on the other hand the shape of the riblets 6 formed on the second zone 542 is adapted to obtain a maximum of drag reduction for a flow rate of the secondary air flow 22 corresponding to the average speed of the secondary air flow 22 along the second zone 542.
    FIG. 4 illustrates the drag reduction obtained by the riblets 6 along the extrados 54 of the blade 50, where x is the curvilinear abscissa of the extrados 54, with x being equal to 0 at the leading edge 51 and x is 1 at the trailing edge 52.
    The flow velocity of the secondary air stream 22 at the trailing edge 52 is greater than the flow velocity of said secondary air stream 22 at the leading edge 51, the height H2 and the spacing E2 of the riblets 6 formed on the second zone 542 are respectively greater than the height H1 and the spacing E1 of the riblets 6 formed on the first zone 541.
    In order to ensure a better reduction of the drag along the entire upper surface 54, the ratio E1 / H1 is equal to the ratio E2 / H2.
    Furthermore, preferably, the height H2 of the riblets 6 formed on the second zone 542 is equal to twice the height H1 of the riblets 6 formed on the first zone 541, and the distance E2 of the riblets 6 formed on the second zone 542 is equal to twice the spacing E1 of the riblets 6 formed on the first zone 541. In fact, for a stator vane 50 of a secondary rectifier 5, the optimum ratio between the spacing of the riblets 6 formed at the level of the leak edge 52 and the spacing of the riblets 6 formed at the leading edge 51 is a ratio of 2.
    As illustrated in FIG. 3a and FIG. 3c, the transition zone 54t located between the first zone 541 and the second zone 542 comprises riblets 6 which have a height Ht, a spacing Et and a width Lt.
    The shape of the riblets 6 (the height Ht, the spacing Et, and the width Lt) on the transition zone 54t evolves along said transition zone 54t so as to pass from the height H1, the spacing E1, and the width L1 at a first end of the transition zone located at the first region 541, at the height H2, the distance E2, and the width L2 at the second end of the transition zone 54t situated at the level of the second zone 542.
    Such a transition zone 54t between the first zone 541 and the second zone 542 makes it possible to avoid a phenomenon of over-friction by limiting the disturbances in the boundary layer of the secondary flux 22 along said transition zone 54t.
    Furthermore, the transition zone 54t comprises a central portion located between its first and second end on which the riblets 6 comprise firstly a height Ht and a width Lt which are respectively equal to the height H1 and the width L1 of the riblets 6 of the first zone 541, and secondly a spacing And which is equal to the spacing E2 of the riblets 6 of the second zone 542.
    Thus, on the central portion of the transition zone 54t, the neighboring riblets 6 are spaced apart so that there is a gap Ep between the bases B of said neighboring riblets 6. Indeed, the width Lt of the riblets 6 being smaller than the spacing And, the neighboring riblets 6 are spaced apart, or in other words are not in contact. This space Ep allows there to be a flat surface Sp between the neighboring riblets 6.
    Such a gap Ep between the neighboring riblets 6 on the central portion of the transition zone 54t makes it easier to manufacture the riblets 6 on the extrados 54. Indeed, such a space Ep makes it possible to facilitate the transition in the shape of the riblets 6 facilitating for example the tool change.
    In addition, such a transition zone 54t having such riblets 6 makes it possible to keep a ratio spacing / height which is identical for the first zone 541 and the second zone 542.
    The riblets 6 can be manufactured according to two possible variants of the manufacturing process.
    According to a first variant, the riblets B are formed during the molding of the blade 50. To do this, the mold in which the blade 50 is molded comprises a ribbed internal wall forming a negative impression of the riblets 6 to be formed on said dawn 50.
    In order to form this print of the riblets on the inner wall of the mold, said wall of the mold can be machined. The space Ep between the riblets 6 (which is also present on the negative impression of the riblets 6 on the inner wall of the mold) makes it possible to facilitate the machining of the inner wall of the mold by facilitating the tool change. first tool being used to form the fingerprint of the riblets of the first zone 541 and the fingerprint of the riblets 6 of the transition zone 54t, and a second tool larger than the first tool being used to form the fingerprint of the riblets 6 of the second zone 542 by aligning with the footprint of the riblets 6 formed on the transition zone 54t. In order to form the footprint of the riblets 6 of the transition zone 54t, the first tool cross-scans the direction of advancement of said first tool, the amplitude of the sweep changing along the transition zone to vary the shape of the riblets 6 of the transition zone 54t.
    In a second variant, the riblets 6 are formed by depositing a ribbed film of polymer material on the blade 50. The ribs of the film which correspond to the riblets 6 are formed by calendering said film. In order to form the riblets 6 on the film, one of the rolls used for the calendering is ribbed so as to include the negative impression of said riblets 6. The ribs of the cylinder may be formed by machining said cylinder. Again, similarly, the space Ep between neighboring riblets 6 facilitates the machining of the footprint of the riblets 6 on the cylinder.
    In the embodiment shown, only the extrados 54 comprises a network of riblets 6 separated into a first zone 541, a second zone 542, and a transition zone 54t.
    However, it is possible for a network of riblets 6 separated into a first zone, a second zone, and a transition zone to be formed only on the intrados 53 of the blade 50. However, the formation of riblets 6 on extrados 54 has more impact on drag reduction than formation of riblets 6 on the lower surface 53.
    It is also possible that both the extrados 54 and the intrados 53 comprise a network of riblets 6 separated into a first zone, a second zone and a transition zone.
    In addition, in the embodiment presented above, the wall of the blade 50 on which the riblets 6 are formed comprises two zones on which the riblets 6 have a constant shape and a transition zone on which the riblets have an evolutionary shape. .
    It is possible, however, to increase the number of zones on which the riblets 6 have a constant shape so as to better adapt the shape of the riblets 6 to the flow velocity of the air flow. To do this it is only necessary to have a transition zone on which the shape of the riblets 6 evolves between each zone on which the shape of riblets 6 is constant. In addition, the ratio spacing / height of the riblets 6 formed on the areas on which the shape of the riblets is constant must be equal for each of said zones on which the shape of the riblets is constant.
    In addition, in the embodiment presented above, the part on which the riblets 6 are formed is a stator blade 50.
    However, it is possible to form riblets 6 as described above (at least two zones on which the shape of the riblets 6 is constant, and at least one transition zone on which the shape of the riblets 6 evolves in the form of the riblets 6 of the first zone to the shape of the riblets 6 of the second zone) on other parts of the turbomachine 1 located in the secondary vein 1,2.
    Thus, it is possible to form riblets 6 as previously described on the separating spout 4 between the primary vein 11 and the secondary vein 12. More specifically, the riblets 6 are formed on the face of the separation spout 4 forming a wall internal vein secondary 12.
    The riblets 6 illustrated in FIGS. 3b, 3c and 3d comprise a section of triangular shape. However, other forms of riblets 6 are possible. The riblets 6 may for example be with a section of square or trapezoidal shape.
    Finally, as illustrated in FIG. 5, the inclination with respect to the top 50a of the blade 50 of the riblets 6 along the extrados 54 and / or the underside 53 can vary. More specifically, the inclination of the riblets 6 on the first zone 541 and the second zone 542 is different and constant on the first and second zones 541, 542. The inclination of the riblets 6 evolves along the transition zone 54t between d on the one hand the inclination of the riblets 6 of the first zone 541 and on the other hand the inclination of the riblets 6 of the second zone 542.
    This variation of the inclination of the riblets 6 with respect to the vertex 50a also causes a variation of the inclination of the riblets 6 with respect to the axis Ω of the turbomachine 1.
    Indeed, in the embodiment shown in FIGS. 3a-3d, the riblets 6 are parallel to the top 50a and to the axis Ω of the turbomachine 1 all along the extrados 54.
    However, in the variant illustrated in Figure 5, the riblets 6 formed on the first zone 541 are inclined at an inclination angle β1 with respect to an axis Ψ which is an axis perpendicular to the radial axis Θ of the blade 50. The axis Ψ is parallel to the vertex 50a and to the axis Ω.
    The riblets 6 formed on the second zone 542 are inclined at an angle of inclination β2 with respect to the axis Ψ which is an axis perpendicular to the radial axis 0 of the blade 50. The angle of inclination β1 is less than or equal to the angle of inclination β2. The angle of inclination β1 is constant along the first zone 541, and the angle of inclination β2 is constant along the second zone 542. Preferably, when the secondary air flow 22 tends to rise towards the the top 50a of the blade 50 during its circulation along said blade 50, the angle of inclination β1 is strictly less than the angle of inclination β2.
    The riblets formed on the transition zone 54t have an angle of inclination βί with respect to the axis Ψ which evolves along said transition zone 54t. The angle of inclination βί changes from the angle of inclination β1 at the first end of the transition zone 54t to the angle of inclination β2 at the second end of the transition zone 54t.
    This inclination from riblets 6, and this variation of the inclination in certain possible variants, makes it possible to adapt the orientation of the riblets 6 to the evolution of the flow direction of the secondary air flow 22 along the blade 50, so as to optimize the reduction of the drag.
    Indeed, the reduction of the drag by the riblets 6 is optimal when said riblets 6 are parallel to the direction of flow of the secondary air stream 22. However, the secondary air stream 22 may tend to rise towards the top 50a of the aube 50 during its circulation along said dawn 50.
    According to one possible variant, the angle of inclination β 1 of the riblets 6 formed on the first zone 541 is between 0 ° (as represented in FIG. 5) and 15 °, and the inclination angle β 2 of the riblets 6 formed. on the second zone 542 is between 0 ° and 30 °.
    Moreover, as shown in FIG. 6, according to one possible implementation of a method for manufacturing a turbomachine part, the drag created by the circulation of an air flow along a wall of said part is reduced, said method comprises the following steps: 100: forming a network of riblets 6 on a first zone 541 of the wall (for example the extrados 54 of a blade 50), the riblets 6 comprising a vertex S, a height H1, a width L1, and a spacing E1 which corresponds to the distance between the vertices S of neighboring riblets 6, the height H1, the width L1, and the spacing E1 of the riblets 6 of the first zone 541 being constant over any the first zone 541. 200: forming a network of riblets 6 on a second zone 542 of the wall, the riblets 6 comprising a vertex S, a height H2, a width L2, a distance E2 corresponding to the distance between the vertices S of 6 neighboring riblets, height H2, the lar Geur L2, and the spacing E2 of the riblets 6 of the second zone 542 being constant over the entire second zone 542. The ratio E1 / H1 between the spacing E1 and the height H1 of the riblets 6 of the first zone 541 is equal to the E2 / H2 ratio between the spacing E2 and the height H2 of the riblets 6 of the second zone 542 to improve the reduction of the drag. 300: forming a network of riblets 6 on a transition zone 54t located between the first zone 541 and the second zone 542, the riblets 6 comprising a vertex S, a height Ht, a width Lt, and a spacing Et corresponding to the distance between the vertices S of neighboring riblets 6, the height Ht, the width Lt, and the spacing And of the riblets 6 of the transition zone 54t moving along said transition zone 54t so as to pass from the height H1, the width L1, and the spacing E1 of the riblets 6 of the first zone 541 at a first end of the transition zone 54t, at the height H2, the width L2, and the spacing E2 of the riblets 6 of the second zone 542 to a second end of the transition zone 54t. The transition zone 54t comprises a central portion situated between the first and the second end on which the riblets 6 comprise on the one hand the height Ht and the width Lt which are respectively equal to the height H1 and the width L1 of the riblets 6 of the first zone 541, and secondly a spacing And equal to the spacing E2 of the riblets 6 of the second zone 542.
    These three formation steps of riblets 100, 200 and 300 can be performed in any order. However, preferably, the formation step of the riblets 6 on the transition zone 54t is carried out in second, that is to say after the step 100 of forming the riblets 6 on the first zone 541, or else after the formation step 200 of the riblets 6 on the second zone 542. It is for example possible to form the riblets 6 on the first zone 541, then on the transition zone 54t, then on the second zone 542. Another Possible example is to form the riblets 6 on the second zone 542, then on the transition zone 54t, then on the first zone 541.
    In addition, as described above, these three steps of forming riblets 100, 200 and 300 can be performed simultaneously by depositing a film of ribbed polymeric material on the workpiece, or by molding the workpiece in a mold comprising a ribbed inner surface.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Part of a turbomachine (1) for an aircraft comprising a wall which comprises a first zone (541), a second zone (542), and a transition zone (54t) situated between the first zone (541) and the second zone (542), a network of riblets (6) being formed on the first zone (541), on the second zone (542), and also on the transition zone (54t), so as to reduce the drag of the part during the circulation of an air flow (22) along said wall; the riblets (6) comprising a vertex (S), a height (H1, H2, Ht), a width (L1, L2, Lt), and a spacing (E1, E2, Et) corresponding to the distance between the vertices (S) neighboring riblets (6); the height (H1), the width (L1), and the spacing (E1) of the riblets (6) of the first zone (541) being constant on the first zone (541); the height (H2), the width (L2), and the spacing (E2) of the riblets (6) of the second zone (542) being constant over the second zone (542); the ratio (E1 / H1) between the gap (E1) and the height (H1) of the riblets (6) of the first zone (541) being equal to the ratio (E2 / H2) between the gap (E2) and the height (H2) of the riblets (6) of the second zone (542); the height (Ht), the width (Lt), and the spacing (Et) of the riblets (6) of the transition zone (54t) moving along said transition zone (54t) so as to pass height (H1), the width (L1), and the spacing (E1) of the riblets (6) formed on the first zone (541) at a first end of the transition zone (54t), at the height (H2), the width (L2), and the spacing (E2) of the riblets (6) formed on the second zone (542) at a second end of the transition zone (54t); characterized in that the transition zone (54t) comprises a central portion located between the first and the second end on which the riblets (6) comprise on the one hand the height (Ht) and the width (Lt) which are respectively equal to the height (H1) and the width (L1) of the riblets (6) of the first zone (541), and secondly a spacing (Et) equal to the spacing (E2) of the riblets (6) of the second area (542).
    [2" id="c-fr-0002]
    2. Part according to claim 1, wherein the part is a blade (50) turbomachine for aircraft, the blade (50) comprising a lower surface (53) and an upper surface (54), the network of riblets (6) being located on the underside (53) and / or the extrados (54) of said blade (50).
    [3" id="c-fr-0003]
    3. Part according to claim 2, wherein the blade (50) comprises a leading edge (51) and a trailing edge (52), the first zone (541) extending from the leading edge. (51) and the second zone (542) extending from the trailing edge (52), the height (H2), the width (L2) and the spacing (E2) of the riblets (6) of the second zone (542) being respectively greater than the height (H1), the width (L1) and the spacing (E1) of the riblets (6) of the first zone (541).
    [4" id="c-fr-0004]
    4. Part according to claim 3, wherein the blade (50) comprises a radial axis (Θ) and an axis (Ψ) perpendicular to the radial axis (Θ), the riblets (6) formed on the first zone ( 541) having an angle of inclination (β1) with respect to the axis (Ψ) perpendicular to the radial axis (Θ) which is constant on the first zone (541), the riblets (6) formed on the second zone (542) having an angle of inclination (β2) with respect to the axis (Ψ) perpendicular to the radial axis (Θ) which is greater than or equal to the angle of inclination (β1) of the riblets (6) of the first zone (541) and which is constant on the second zone (542), the riblets (6) formed on the transition zone (54t) having an angle of inclination (βί) with respect to the axis (Ψ ) perpendicular to the radial axis (Θ) which evolves along said transition zone (54t) between the angle of inclination (β1) of the riblets (6) of the first zone (541) at the first end of the transition zone (54t), and the angle of inclination (β2) of the riblets (6) of the second zone (542) at the second end of the transition zone (54t).
    [5" id="c-fr-0005]
    5. Part according to claim 4, wherein the angle of inclination (β1) of the riblets (6) of the first zone (541) is between 0 ° and 15 °, and wherein the angle of inclination ( β2) riblets (6) of the second zone (542) is between 0 ° and 30 °.
    [6" id="c-fr-0006]
    6. Part according to any one of claims 2 to 5, wherein said part is a stator blade for a secondary rectifier (5) of a turbomachine (1) for an aircraft.
    [7" id="c-fr-0007]
    7. A turbomachine (1) for aircraft comprising a part according to any one of claims 1 to 6.
    [8" id="c-fr-0008]
    8. Turbine engine (1) for aircraft according to claim 7, wherein the turbomachine (1) comprises a primary vein (11), a secondary vein (12), a blower (3), and a secondary rectifier (5) located in the secondary vein (12), the part being a separation spout (4) between the primary vein (11) and the secondary vein (12) which is located between the blower (3) and the secondary straightener (5), the riblets (6) being located on a portion of the separation spout (4) forming an inner wall of the secondary vein (12).
    [9" id="c-fr-0009]
    9. A method of manufacturing a turbomachine part (1), said method comprising the following steps: (100) forming a network of riblets (6) on a first zone (541) of a wall of the part, the riblets (6) comprising a vertex (S), a height (H1), a width (L1), and a spacing (E1) which corresponds to the distance between the vertices (S) of neighboring riblets (6), the height (H1 ), the width (L1), and the spacing (E1) of the riblets (6) of the first zone (541) being constant over the entire first zone (541); (200) forming a network of riblets (6) on a second zone (542) of the wall, the riblets (6) comprising an apex (S), a height (H2), a width (L2), a spacing (E2 ) corresponding to the distance between the vertices (S) of neighboring riblets (6), the height (H2), the width (L2), and the distance (E2) of the riblets (6) of the second zone (542) being constant over the entire second zone (542), the ratio (E1 / H1) between the spacing (E1) and the height (H1) of the riblets (6) of the first zone (541) being equal to the ratio (E2 / H2 ) between the spacing (E2) and the height (H2) of the riblets (6) of the second zone (542); (300) forming a network of riblets (6) on a transition zone (54t) of the wall located between the first zone (541) and the second zone (542), the riblets (6) comprising a vertex (S), a height (Ht), a width (Lt), and a spacing (Et) corresponding to the distance between the vertices (S) of neighboring riblets (6), the height (Ht), the width (Lt), and the spacing (Et) from the transition zone (54t) riblets (6) moving along said transition zone (54t) so as to pass from the height (H1), the width (L1), and the gap ( E1) riblets (6) of the first zone (541) at a first end of the transition zone (54t), at the height (H2), the width (L2), and the spacing (E2) of the riblets ( 6) of the second zone (542) at a second end of the transition zone (54t), the transition zone (54t) comprising a central portion located between the first and the second end on which the riblets (6) comprise 'a part the height (Ht) and the width (Lt) which are respectively equal to the height (H1) and the width (L1) of the riblets (6) of the first zone (541), and secondly a spacing (Et) equal to the spacing (E2) of the riblets (6) of the second zone (542).
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    同族专利:
    公开号 | 公开日
    US20190168862A1|2019-06-06|
    US11220326B2|2022-01-11|
    EP3475532B1|2020-04-15|
    CN109477392A|2019-03-15|
    FR3053074B1|2018-06-15|
    CN109477392B|2021-01-19|
    EP3475532A1|2019-05-01|
    WO2018002514A1|2018-01-04|
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    EP2977549B1|2014-07-22|2017-05-31|Safran Aero Boosters SA|Axial turbomachine blading and corresponding turbomachine|FR3076540B1|2018-01-08|2021-04-16|Airbus Operations Sas|AERODYNAMIC ELEMENT OF AN AIRCRAFT, PROVIDED WITH A SET OF PROTUBERANT ELEMENTS.|
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    法律状态:
    2017-04-27| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-29| PLSC| Publication of the preliminary search report|Effective date: 20171229 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 3 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-04-10| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200304 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1656025|2016-06-28|
    FR1656025A|FR3053074B1|2016-06-28|2016-06-28|PIECE AND METHOD FOR MANUFACTURING A REDUCED ROLLED ROLLED PIECE|FR1656025A| FR3053074B1|2016-06-28|2016-06-28|PIECE AND METHOD FOR MANUFACTURING A REDUCED ROLLED ROLLED PIECE|
    PCT/FR2017/051721| WO2018002514A1|2016-06-28|2017-06-27|Part and method for producing a part having reduced drag by non-constant riblets|
    US16/313,722| US11220326B2|2016-06-28|2017-06-27|Part and method for producing a part having reduced drag by non-constant riblets|
    CN201780046052.4A| CN109477392B|2016-06-28|2017-06-27|Component with reduced drag by non-constant ribs and method of producing the same|
    EP17745402.2A| EP3475532B1|2016-06-28|2017-06-27|Part and method for producing a part having reduced drag by non-constant riblets|
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