• 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 present invention relates to a part (1) or set of turbomachine parts comprising at least first and second blades (3I, 3E), and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2) has between the intrados of the first blade (3I) and the extrados of the second blade (3E) a non-axisymmetric surface (S) defining at least one fin (4) substantially section triangular extending downstream of a leading edge (BA) of each of the blades (3I, 3E), the fin (4) having a width of between 5% and 20% of the distance between the lower surface of the first blade (3I) and the extrados of the second blade (3E).
    公开号:FR3014943A1
    申请号:FR1362927
    申请日:2013-12-18
    公开日:2015-06-19
    发明作者:Vianney Christophe Marie Maniere；Matthieu Jean Luc Vollebregt；Gaetan Jean Marie Loupy；Paul Henri Joseph Mauclair
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] GENERAL TECHNICAL FIELD The present invention relates to a turbomachine part comprising blades and a platform having a non-axisymmetric surface. STATE OF THE ART The need for constant improvement of the performance of equipment, in particular aeronautical equipment, for example turbojet rotor (that is to say the assembly formed of a hub on which are fixed blades) extending radially, as shown in Figure 1), has today imposed the use of computer modeling tools. These tools help to design parts by automatically optimizing some of their characteristics by performing a large number of simulation calculations. The search for an aeromechanical and / or acoustic geometrical optimum on the rotors or stators leads today to obtaining hubs having a locally non-axisymmetric wall (that is to say a section along a perpendicular plane). to the axis of rotation is circular) at the level of the vein, that is to say the set of channels between the blades for the fluid flow (in other words the inter-blade sections) , in view of the particular conditions that prevail there. The nonaxisymmetric vein defines a generally annular surface of a three-dimensional space (a "slice" of the hub). However, it can be seen that these geometries remain perfectible, in particular at the compressor stages of the turbomachine. Indeed, the blade / wall connections remain the seat of secondary flows (and therefore significant losses in the compressor stages), because of the proximity of the wall on which a significant boundary layer develops from the upstream of the compressor , and the established pressure gradient of the extrados of a blade towards the intrados of the adjacent blade.
    [0002] The combination of these elements generates a rise of low energy fluid on the upper surface of each blade and is translated downstream by large vortices, sources of losses. There is also an over-deflection near the wall and a sub-deviation above. It would be desirable to have a new geometry to correct these problems in order to improve the performance in terms of equipment performance, but without degrading neither operability nor mechanical strength. PRESENTATION OF THE INVENTION The present invention thus proposes a part or set of turbomachine parts comprising at least first and second blades, and a platform from which the blades extend, characterized in that the platform between lower surface of the first blade and the upper surface of the second blade a non-axisymmetric surface defining at least one substantially triangular section fin extending downstream of a leading edge of each of the blades, the fin having a width between 5% and 20% of the distance between the lower surface of the first blade and the upper surface of the second blade. The wing or fins of this particular non-axisymmetric geometry of the surface of the part prevent aerodynamic detachment. The operability of the compressor stages and the efficiency thereof are all improved. According to other advantageous and non-limiting characteristics: the fin has a height-to-width ratio of between 0.3 and 1.3; The fin has a height of between 1 mm and 25 mm; the fin has a trace corresponding to the average line of skeletons of the first and second blades; The fin is associated with a driving position and a trailing position on the surface, between which the fin extends, such that: the driving position is between 5% and 35% relative length of a blade rope extending from a leading edge to a trailing edge of the blade, and - the trailing position located between 50% and 105% relative length of said blade rope; the attack and trailing positions associated with the fin are each located at a distance from the extrados of the second blade between 10% and 55% of the distance between the intrados of the first blade and the extrados the second blade; the surface defines two or three fins side by side, such that the further a fin is removed from the extrados of the second blade, the more the attacking position of said fin is axially remote from the leading edge of the blades; the surface defines a single fin; the platform comprises a first platform part from which extends the first blade and a second platform part from which the second blade extends, a connection between said first and second platform parts forming the fin ; the surface is bounded by a first and a second extremal plane, the surface being defined by at least one construction curve of class C1 each representing the value of a radius of said surface as a function of a position between the lower surface the first blade and the extrados of the second blade in a plane substantially parallel to the end planes disposed between the driving position and the trailing position of the fin; each construction curve has been modeled via the implementation by data processing means of steps of: (a) Parametrization of the construction curve as a class curve C1 representing the value of the radius of said surface in terms of a function of a position between the lower surface of the first blade and the upper surface of the second blade, the curve being defined by: - two extreme control points, respectively on each of the two blades between which said surface extends; - At least one intermediate control point located between the extremal control points; - At least one spline; the parameterization being implemented according to one or more parameters defining at least one of the control points; (b) Determining optimized values of said parameters of said curve. - The platform has an annular shape along which are regularly arranged a plurality of blades; the platform has the same non-axisymmetric surface between each pair of consecutive blades; the piece is a paddle wheel or a compressor straightener. According to a second aspect, the invention relates to a turbomachine comprising a part according to the first aspect. PRESENTATION OF THE FIGURES Other features and advantages of the present invention will appear on reading the description which follows of a preferred embodiment. This description will be given with reference to the appended drawings in which: FIG. 1 previously described represents an example of a turbomachine; - Figures 2 and 3 show two preferred embodiment of a part according to the invention; Figure 4 schematically shows the geometry of the embodiment of Figure 2; - Figure 5 schematically shows another embodiment of a part according to the invention; Figures 6a-6c show results of observation of the current and friction lines for three geometries. DETAILED DESCRIPTION Referring to FIGS. 2 and 3, the present part 1 (or set of parts if it is not a single piece) of turbomachine has at least two consecutive blades 3E, 31 and a platform 2 from which extend 3E, 31. The term platform is here interpreted in the broad sense and refers generally to any element of a turbomachine on which blades 3E, 31 are able to be mounted (extending radially) and having a wall internal / external against which the air circulates. In particular, the platform 2 can be monobloc (and thus support all the blades of the part 1), or formed of a plurality of elementary members each supporting a single blade 3E, 31 (a "foot" of the blade) so as to constitute a blade of the type of that represented by FIG. 3 In particular, the platform 2 may comprise a platform portion 21, 2E for each of the blades 3E, 31 in an advantageous embodiment which will be described later. . In addition, the platform 2 may delimit a radially inner wall of the part 1 (the gas passes around) by defining a hub, and / or a radially outer wall of the part 1 (the gas passes inside, the blades 31, 3E extend towards the center) by defining then a casing of the part 1. It should be noted that the same part 1 can comprise simultaneously these two types of platform 2. It will be understood that as explained the piece 1 can be of many types, in particular a rotor stage (DAM ("Aubade Monobloc Disk"), or impeller, according to the integral nature or not of the assembly) or a stator stage (fixed stator, or with moving blades VSV ("Variable Stator Vane")), especially at the input of the secondary flow (OGV rectifier, "Outlet Guide Vane"), see Figure 1 already introduced.
    [0003] In the remainder of the present description, the example of an OGV stage will be used for this purpose, but the person skilled in the art will be able to transpose to the other types of parts 1 (for example to a "fan", in part). other words a blower, or a stage of the compressor Low Pressure).
    [0004] Platform Surface The present part 1 is distinguished by a particular (non-axisymmetrical) geometry of a surface S of a platform 2 of the part 1, of which an advantageous modeling example is observed in FIGS. 2 and 3.
    [0005] The surface S extends between two blades 3E, 31 (only one of which is visible in each of FIGS. 2 and 3 for better observing the surface S. Nevertheless, the trace of the missing blade is found in each case), which limit it laterally. . The surface S is indeed a part of a larger surface defining a substantially toric shape around the piece 1. In the hypothesis (but not limiting) of a periodicity in the circumference of the piece 1 (that is, that is, if the blades 3E, 31 are identical and distributed uniformly), the wall consists of a plurality of identical surfaces duplicated between each pair of blades 3E, 31.
    [0006] The surfaces S 'also visible in FIGS. 2 and 3 are thus a duplication of the surface S. Still in this figure, a line is visible dividing each of the surfaces S and S' into two halves. This structure corresponds to an embodiment in which the platform 2 is composed of a plurality of elementary members each being a foot supporting a blade 3E, 31 with which it forms a blade. Each of these blade roots (referred to as "platform parts" in the remainder of the present description) thus extends on both sides of the blade 3E, 31, hence the surface S comprises surfaces juxtaposed associated with two separate feet of blade. The piece 1 is then a set of at least two vanes (blade / blade blade assembly) juxtaposed. We speak of "integrated" platforms, as opposed to "reported" platforms, that is to say independent of the blades (the surface S can then consist of a single element). It will be understood that the present invention is not limited to any particular structure of the platform 2. The surface S is limited upstream by a first extremal plane, the "Separation Plan" PS and downstream by a second extremal plane, the "Plan". "PR, which each define an axisymmetric contour, continuous and continuous derivative (the curve corresponding to the intersection between each of the planes PR and PS and the surface of the part 1 as a whole is closed and forms a loop). The surface S has a substantially parallelogram shape and extends continuously between the two end planes PS, PR, and the two blades 3E, 31 of a pair of consecutive blades. One of the blades of this pair of blades is the first blade 31, or blade of intrados. It has indeed its intrados on the surface S. The other blade is the second blade 3E, or blade of extrados. In fact, it has its underside on the surface S. Each "second blade" 3E is the "first blade" 31 of a neighboring surface such as the surface S 'in FIG. 2 (since each blade 3E, 31 has a lower surface and an extrados). The surface S is advantageously defined by PC construction curves, also called "Construction plans". Each PC construction curve is a class C1 curve representing the value of a radius of said surface S as a function of a position between the intrados of the first blade 31 and the extrados of the second blade 3E in a plane substantially parallel to extremal planes PS, PR. By radius is understood the distance between a point of the surface and the axis of the part 1. An axisymmetric surface thus has a constant radius.
    [0007] A PC construction curve is typically a spline, ie a parametric polynomial curve, among which we can notably mention the Bézier Ailette curves. The non-axisymmetrical S surface of the present part is remarkable in that it defines at minus a fin 4 having a substantially triangular section extending downstream from a leading edge (BA) of each of the blades 31, 3E, the fin 4 having a width of between 5% and 20% of the distance between the l intrados of the first blade 31 and the extrados of the second blade 3E. There may be one, two or three fins 4 on the vein (Figure 2 shows a solution to a fin 4, and Figure 3 a solution with two fins 4, the different possibilities will be described later). The fact of arranging the fins between two blades of a part is known (see for example the patent applications EP1927723, JP6022002, US4023350). But known fins are usually flat "slats". Indeed these known fins (which are in general many) have only role to act as a barrier for the incident flow, and generate vortices. The present fins 4 are intended to improve the deflection of the incident flow, and to prevent the rise of fluid along the extrados. By this, the fins 4 improve the efficiency and operability of a compressor stage, and prepare a cleaner / homogeneous fluid for the subsequent stages. In particular, it appears an increase in vorticity at the leading edge of the present fins 4, but further downstream the reduction of the vortex passage prevails and the vortex intensity decreases by up to 6%. The addition of at least one fin 4 thus decreases the detachment at the trailing edge. This is a direct consequence of the straightening effect of the fins on the flow at the boundary layer. Less energy hits the extrados of the second blade 3E, so the current lines can more difficult to mount. The peel height can be reduced by half (see below for comparison of different embodiments).
    [0008] In all cases, the fins 4 have a substantially triangular section, that is to say they have two oblique faces joining on a dorsal edge, either by an angle, or by a tangent connection. The two faces themselves are connected to the vein (rest of the surface S) either by an angle or by a tangent connection. Each fin 4 may further have bevelled ends as seen in Figures 2 and 3. Preferably, each fin 4 has a trace (that is to say a trajectory) corresponding to the average line of skeletons of the first and second blades 31, 3E. Most often, all the blades have the same skeleton, that is why all the fins 4 and blades 31, 3E have a similar curvature, but it will be understood that the invention is not limited to this case. This appears in particular in FIG. 4 (the skeletons of the blades 31, 3E and the trace of the fin 4 are the median lines represented for each of the elements). It should be noted that the fins 4 offer another advantage: they can be used as a heat exchanger to facilitate the cooling of the part 1. Dimensions and position As explained or the fins 4 have a width of between 5% and 20% (preferentially between 10% and 15%) of the distance between the lower surface of the first blade 31 and the upper surface of the second blade 3E. The width considered here is the maximum width of the base of the fin 4 (which is substantially constant, except at the level of the leading and trapping bevels). This width and the distance between the lower surface of the first blade 31 and the upper surface of the second blade 3E are preferentially assessed in planes parallel to the end planes PS, PR (in other words according to the previously mentioned construction curves ), which are visible in Figures 2 and 3, and shown vertically in Figure 4.
    [0009] Preferably, each fin 4 has a height-to-width ratio of between 0.3 and 1.3, which at the conventional dimensions of the compressor stages gives a height of between 1 mm and 25 mm. Each fin 4 is in particular defined by two extremal points: a driving position and a trailing position on the surface S, between which the fin 4 extends (in particular following the skeleton of the blades 31, 3E). The driving position is defined in the reference frame of FIG. 4 by XBA and YBA coordinates, and the trailing position by XBF and YBF coordinates. These coordinates are respectively an axial coordinate and an azimuthal coordinate of the position. The first coordinate X designates an (axial) position along a blade rope 31, 3E extending from a leading edge BA to a trailing edge BF of the blade 31, 3E, expressed in relative length ( in other words, at X = 0 corresponds to an alignment on the leading edges BA and X = 1 corresponds to an alignment with the trailing edges BF of the blades 31, 3E). And preferably, these positions are such that: the (axial) attack position is between 5% and 35% (preferably between 15% and 25%) of the relative length of the blade rope 31, 3E (ie XBA E [0.05, 0.35]), and - the (axial) leak position located between 50% and 105% (preferably between 70% and 85%) relative length of the blade rope 31, 3E (ie XBF E [0.5,1.05]). Note that the fin 4 is not necessarily between the leading edge BA and LF of the vanes 31, 3E and can extend axially downstream of the trailing edge BF.
    [0010] The second coordinate Y designates an (azimuthal) position along a channel width extending from the extrados of the second blade 3E to the underside of the first blade 31, expressed in relative length (in other words , Y = 0 corresponds to a point against the upper surface of the second blade 3E and Y = 1 corresponds to a point against the underside of the first blade 31). And preferably, these positions are such each of the attack and trailing positions associated with the fin 4 is located at a distance from the extrados of the second blade 3E between 10% and 55% of the channel width (ie Y - -BA, - [0.1,0.55]). The fin (s) 4 can therefore be - - YBF E - centered in the vein, but are preferentially closer to the upper surface of the second blade 3E. Number of fins According to an embodiment illustrated in FIGS. 2 and 4, the surface S can define a single fin 4, which can be arranged in the middle of the vein (attack and trailing positions associated with the fin 4 located at a distance from the upper surface of the second blade 3E to about 50% of the channel width).
    [0011] In the case of such a single fin 4 centered, it is possible to use the structure of the platform 2 to reconstruct this fin 4. Thus, if the platform 2 comprises a first platform portion 21 from which extend the first blade 31 and a second platform portion 2E from which extend the second blade 3E, the connection between the two parts 21, 2E of the platform 2 may be provided to correspond to the trace of the blade 4. A protruding inter-platform joint of suitable shape can then form the fin (as seen in Figure 5). This solution has many advantages because it requires only a few modifications compared to known parts and can facilitate assembly / disassembly by allowing greater tangential clearance between the platform portions 2.
    [0012] Alternatively, there may be more than one fin 4. The best results are obtained for two fins 4. It is desirable not to exceed three fins 4.
    [0013] With two fins, these can be arranged in the middle of each of the platform parts 21, 2E 2 (as seen in FIG. 3), but preferably the fins 4 can be rather on the extrados side of the vein . For example, a first fin may be associated with azimuth positions YB A, YBF E [0.2, 0.25], and a second fin associated with azimuth positions YBA, YBF E [0.5, 0.55]. In general, as soon as there is more than one fin 4, it is desirable that the more a fin 4 is moved away from the extrados of the second blade 3E, the more the (axial) position of attack of said fin 4 away from the leading edge BA of the blades 31, 3E. In other words, starting from the extrados, the fins are staggered with XBA growing. In this second case, the fins 4 are inherent to the surface S, and the use of the PC construction curves makes it possible to define them (which is also true in the case of a single fin 4 if it is not obtained by a joint). Preferably, at least three construction curves are used, as can be seen for example in FIG. 2, where there are seven: an attack curve (which passes through the point of attack defined above), at least one central curve, and a leakage curve (which passes through the vanishing point also defined above). The central curve or curves (the number of which may vary) are advantageously arranged at regular intervals. In FIG. 2, the first and the last central curve are arranged at the junction between the bevel and the fin body 4. If a plurality of fins 4 are defined, the leakage curve of one may be a central curve of another, and so on. Note that in the example of Figure 2 the leakage curve is coincident with the PS connection plane (the fin 4 extends beyond the trailing edge). On the contrary, there may be other construction curves arranged upstream or downstream of any fin 4 (and therefore not helping to define this or these). Each PC construction curve is thus defined by a plurality of control points (extremal and intermediate, at least one intermediate control point (and even two for the central curves) being required per fin 4 for each PC construction curve disposed between the attack position and the trailing position of a fin 4). The parameter or parameters defining a control point are selected from an abscissa of the point, an ordinate of the point, a tangent orientation to the curve at the point and a (in the case of an extremal control point, one can not take into account that half-tangent in the range of definition of the curve, left or right following the point) or two (in the case of an intermediate control point) voltage coefficients each associated with a half-tangent at the curve at the point.
    [0014] The positions of the extremal control points are constrained by the blades 31, 3E. On the other hand, the orientations of the tangent to the curve at these points (in other words the derivatives) make it possible to control the slopes of the surface S, in particular those of the flanks of a fin 4 (and therefore its width and height) Surface Modeling Surface definition via PC construction curves facilitates the automatic optimization of part 1.
    [0015] Each PC construction curve can thus be modeled via the implementation of steps of: (a) Parametrization of the PC construction curve as a class C1 curve representing the value of the radius of said surface S as a function of a position between the lower surface of the first blade 31 and the upper surface of the second blade 3E, the curve being defined by: - two extreme control points, respectively on each of the two blades 3E, 31 between which said surface S extends At least one (advantageously two) intermediate control point located between the extremal control points; - At least one spline; the parameterization being implemented according to one or more parameters defining at least one of the control points; (b) Determining optimized values of said parameters of said curve. These steps are performed by computer equipment comprising data processing means (for example a supercomputer).
    [0016] Some parameters of the extremal or intermediate control points, for example the inclination intervals of the tangents, are fixed so as to respect the desired slope conditions. Many criteria can be chosen as criteria to be optimized when modeling each curve. By way of example, it is possible to try to maximize mechanical properties such as resistance to mechanical stresses, frequency responses, blade displacements 3E, 31, aerodynamic properties such as efficiency, pressure rise, capacity flow rate or pumping margin, etc. For this it is necessary to parameterize the law that one seeks to optimize, that is to say to make a function of N input parameters. Optimization then consists in varying (generally randomly) these various parameters under stress, until they determine their optimal values for a predetermined criterion. A "smoothed" curve is then obtained by interpolation from the determined crossing points.
    [0017] The number of necessary calculations is then directly linked (linearly or even exponentially) to the number of input parameters of the problem. Numerous methods are known, but preferably a method similar to that described in patent application FR1353439, which allows an excellent modeling quality, without high consumption of computing power, while limiting the 5 Runge phenomenon (excessive "waving" of the surface). It should be noted that the blade 3E, 31 is connected to the platform 2 via a connection curve (visible for example in Figure 1b), which can be the subject of a specific modeling, including also via the use splines and user control points.
    [0018] Effect of the fins The current and friction lines were observed along the extrados of the second blade 2E: geometry without fins (FIG. 6a), non-axisymmetric geometry with a single fin (FIG. 6b) and non-axisymmetric geometry -axisymmetric with two fins (Figure 6c). We can clearly see in Figures 6b and especially 6c the reduction of the separation height, which decreases by nearly 33%. The vorticity gain was 2.3% for a fin, and 3.8% for two fins, resulting in a yield increase of a few tenths of a percent.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Part (1) or set of turbomachine parts comprising at least first and second blades (31, 3E), and a platform (2) from which the blades (31, 3E) extend, characterized in that the platform (2) has between the lower surface of the first blade (31) and the upper surface of the second blade (3E) a non-axisymmetric surface (S) defining at least one fin (4) with a substantially triangular section extending in downstream of a leading edge (BA) of each of the blades (31, 3E), the fin (4) having a width of between 5% and 20% of the distance between the intrados of the first blade (31 ) and the extrados of the second blade (3E).
    [0002]
    2. Part or assembly of parts according to claim 1, wherein the fin (4) has a height-to-width ratio between 0.3 and 1.3.
    [0003]
    3. Part or assembly of parts according to claim 2, wherein the fin (4) has a height of between 1 mm and 25 mm.
    [0004]
    4. Part or assembly of parts according to one of the preceding claims, wherein the fin (4) has a trace 25 corresponding to the average line of skeletons of the first and second blades (31, 3E).
    [0005]
    5. Part or assembly of parts according to one of the preceding claims, wherein the fin (4) is associated with a driving position and a trailing position on the surface (S), between which the fin ( 4) extends, such as: - the driving position is between 5% and 35% relative length of a blade rope (31, 3E) extending from a leading edge (BA) ) at a trailing edge (BF) of the blade (31, 3E), and - the trailing position situated between 50% and 105% relative length of said blade rope (31, 3E).
    [0006]
    6. Part or assembly of parts according to claim 5, wherein the attack and trailing positions associated with the fin (4) are each located at a distance from the extrados of the second blade (3E) between 10 % and 55% of the distance between the lower surface of the first blade (31) and the upper surface of the second blade (3E).
    [0007]
    7. Part or assembly of parts according to one of claims 5 and 6, wherein the surface (S) defines two or three fins (4) side by side, such that a fin (4) is removed from the extrados of the second blade (3E), plus the driving position of said fin (4) is axially remote from the leading edge (BA) of the blades (31, 3E).
    [0008]
    8. Part or assembly of parts according to one of claims 1 to 6, wherein the surface (S) defines a single fin (4).
    [0009]
    9. Part or assembly of parts according to claim 8, wherein the platform (2) comprises a first platform portion (21) from which extends the first blade (31) and a second platform portion (2E). from which extends the second blade (3E), a connection between said first and second platform portions (21, 2E) forming the fin (4).
    [0010]
    10. Part or assembly of parts according to one of claims 5 to 9, wherein the surface (S) is limited by a first and a second end plane (PS, PR), the surface (S) being defined by at least one Class C1 construction curve (PC) each representing the value of a radius of said surface (S) as a function of a position between the intrados of the first blade (31) and the extrados of the second blade (3E ) in a plane substantially parallel to the end planes (PS, PR) disposed between the driving position and the trailing position of the fin (4).
    [0011]
    11. Part or assembly of parts according to claim 10, for which each construction curve (PC) has been modeled via the implementation by data processing means of steps of: (a) Parametrization of the construction curve (PC) as a class C1 curve representing the value of the radius of said surface (S) as a function of a position between the intrados of the first blade (31) and the extrados of the second blade (3E), the curve being defined by: - two extreme control points, respectively on each of the two blades (31, 3E) between which said surface (S) extends; - At least one intermediate control point located between the extremal control points; - At least one spline; the parameterization being implemented according to one or more parameters defining at least one of the control points; (b) Determining optimized values of said parameters of said curve.
    [0012]
    12. Part or assembly of parts according to one of the preceding claims, wherein the platform (2) has an annular shape along which are regularly arranged a plurality of blades (31, 3E).
    [0013]
    13. Part or assembly of parts according to claim 12, wherein the platform (2) has the same nonaxisymmetric (S) surface between each pair of blades (31, 3E) consecutive.
    [0014]
    14. Part or assembly of parts according to claim 13, being a paddle wheel or a compressor rectifier.
    [0015]
    15. Turbomachine comprising a part (1) or set of parts according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    US10519980B2|2019-12-31|
    CN105829653B|2017-11-24|
    RU2666933C1|2018-09-13|
    JP6559138B2|2019-08-14|
    EP3084134A1|2016-10-26|
    US20170009781A1|2017-01-12|
    CA2933123A1|2015-06-25|
    JP2017500487A|2017-01-05|
    WO2015092306A1|2015-06-25|
    RU2016128925A|2018-01-23|
    EP3084134B1|2018-03-28|
    CN105829653A|2016-08-03|
    FR3014943B1|2019-03-29|
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    法律状态:
    2015-12-11| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-02| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362927A|FR3014943B1|2013-12-18|2013-12-18|TURBOMACHINE PIECE WITH NON-AXISYMETRIC SURFACE|
    FR1362927|2013-12-18|FR1362927A| FR3014943B1|2013-12-18|2013-12-18|TURBOMACHINE PIECE WITH NON-AXISYMETRIC SURFACE|
    CN201480070059.6A| CN105829653B|2013-12-18|2014-12-18|The part of turbine and the turbine of correlation|
    US15/105,359| US10519980B2|2013-12-18|2014-12-18|Turbomachine component or collection of components and associated turbomachine|
    CA2933123A| CA2933123A1|2013-12-18|2014-12-18|Turbomachine component with non-axisymmetric surface defining a plurality of fins|
    RU2016128925A| RU2666933C1|2013-12-18|2014-12-18|Turbomachine component or collection of components and associated turbomachine|
    EP14830831.5A| EP3084134B1|2013-12-18|2014-12-18|Turbomachine component or component assembly and corresponding turbomachine|
    PCT/FR2014/053437| WO2015092306A1|2013-12-18|2014-12-18|Turbomachine component or collection of components and associated turbomachine|
    JP2016541046A| JP6559138B2|2013-12-18|2014-12-18|Turbomachine component or group of components and associated turbomachine|
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