• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a profiled structure, - elongated in a direction in which the structure has a length (L1) exposed to an air flow (U), and - transversely to which the structure has a leading edge (164) and / or a trailing edge (165), at least one of which is profiled and presents, along said direction of elongation, geometric patterns of tightening ( 28) defined by successive teeth (30) and recesses (32). Along the leading edge and / or the profiled trailing edge (s), the tightening patterns (28) have a geometric pattern which repeats in the direction of elongation (L1), the shape of which exhibits a stretch and / or a contraction: - transversely to the direction of elongation, and / or - following the direction of elongation.
    公开号:FR3087483A1
    申请号:FR1859663
    申请日:2018-10-18
    公开日:2020-04-24
    发明作者:Fernando Gea Aguilera；Raphael BARRIER；Simon Paul Gruber Mathieu；Cyril POLACSEK；Dominique Jeanne Posson Helene
    申请人:Office National dEtudes et de Recherches Aerospatiales ONERA；Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    [0001] PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT INTRODUCTION
    [0001] [1] The present invention relates to the field of aeroacoustic management of aerodynamically profiled structures, or profiles of aerodynamic elements, such as for example fixed or rotating blades in an aircraft turbomachine or in a test bench of such turbomachines. , or on a primary air inlet nozzle of the turbomachine.
    [0002] [2] This type of fixed vane is found, for example, on OGV (Outlet Guide Vane) fan outlet guide vanes, or rectifiers, arranged downstream of a rotating body to straighten the air flow.
    [0003] This type of rotating blade is found, for example, on a wheel of rotating blades in a turbomachine, such as a fan or a non-faired wheel.
    [0004] [4] This concerns both ducted turbomachines (turbofans / turbofans) and non-ducted turbomachines (open-20 rotors).
    [0005] [5] An example will be given for a double-flow turbomachine with a fan (front) and a rectifier arranged in a secondary stream.
    [0006] [6] Particularly in Ultra-High Bypass Ratio (UHBR; ducted fan engine configuration at very high dilution ratio, beyond 15), it is envisaged to increase the diameter of the fan and reduce the length of the nacelle suspended from the aircraft, thus reducing the distance between the fan and the inlet guide vanes of IGV compressors (Inlet Guide Vanes), OGVs and the primary air inlet nozzle.
    [0007] [7] Beyond this observation in a turbomachine, other areas of turbomachines, but also aerodynamically profiled structures 2 (wings, open-rotor blades - open rotor -, pylon, etc.) are confronted with to aero-acoustic issues of interaction with air flow.
    [0008] [8] It has therefore already been proposed, in particular in the field of aircraft, to use aerodynamically profiled structures having a profiled leading and / or trailing edge having, following a leading edge line. and / or leakage, a serration profile therefore provided with a succession of teeth and hollows.
    [0009] [9] Thus, this serration profile extends along the leading and / or trailing edge, in other words in the direction of the elongation of the structure at the leading and / or trailing edge.
    [0010] [10] In particular on profiles with reduced chord, but also on closed profiles - (line of) leading and / or trailing edge elongated along a line or direction of elongation closed on itself - perimeter line -, as on a primary air inlet nozzle of a turbomachine, the noise is mainly produced at the level of the leading and / or trailing edge, more precisely at the troughs of the seams where the pressure fluctuations are more intense.
    [0011] [11] Regarding the term "string" used in the present text, it should be noted that if there is not strictly a "string" as in the case of a mouthpiece (marked 16 below) of separation between the primary and secondary flow, it will be considered that the expression "in the direction of the chord (marked 40 below) of the profile" then corresponds to the direction of what is hereinafter called "general axis (X) "Or" X axis ", namely the axis along which the fluid flow generally flows over the profiled structure concerned, this axis typically being transverse, or even perpendicular, to the elongation of the profiled structure, which extends along said "direction of elongation".
    [0012] [12] It will be understood that the expression "transverse (e)" does not imply a strict perpendicularity.
    [0013] [13] The invention aims to take into consideration the fact that a profiled structure must, in the presence of a turbulent flow (for example in the wake of a rotating part of a turbomachine or of a boundary layer on a wall) , face an inhomogeneous and / or anisotropic flow, that is to say that 3 the intensity of the turbulence and / or the size of the vortices vary in time and space.
    [0014] [014] To this end, a profiled structure is proposed, - elongated in a direction in which the structure has a length (L1, hereinafter) exposed to a flow of air, and - transversely to which the structure has a leading edge and / or a trailing edge, at least one of which is profiled and exhibits, in said direction of elongation, clamps defined by successive teeth and recesses, the profiled structure being characterized in that that, along the leading edge and / or the profiled trailing edge (s), the clamps present a transformed geometric pattern, over at least part of said length (L1) exposed to the air flow, by successive scaling, via multiplicative factors, according to the direction of elongation (hereinafter L2, L21, L22, L23,) and / or transversely to the direction of elongation (hereinafter d, di, d2 , d3, ...).
    [0015] [015] Thus, the tightening will present a geometric pattern along the direction of elongation (length L1), with a shape which, from repetition transformed into repetition transformed, stretches or contracts: - transversely to the direction of elongation (cf. said amplitude (d) which varies), and / or - depending on the direction of elongation (i.e. a length of the pattern in the direction of elongation which varies; cf. distance (L2) variable).
    [0016] [016] Thus the pattern can be modified by varying the local amplitudes of the serrations while maintaining the position of the minima of the hollows and the maxima of the teeth, or by varying the position of the hollows and of the teeth while maintaining the amplitude of the teeth and hollow. 30
    [0017] [017] Provision can in particular be made for, the geometric pattern which transforms evolving in a non-periodic manner, along said direction 4 of elongation and / or transversely to the direction of elongation, this geometric pattern which is transformed preferably evolves according to one or more laws of linear (s), quadratic (s), hyperbolic (s), exponential (s) or logarithmic (s). 5
    [0018] [018] This will facilitate the adaptation of the profile of the edges or of the leakage to the varying conditions of the air flows received.
    [0019] [19] To favorably take into account an established relation between amplitude and frequency (if one calls "frequency", the transformed repetition of the geometric pattern, according to the direction of elongation), it is also proposed that the scalings successive (amplitude and frequency) vary so that said geometric pattern evolves homothetically.
    [0020] [20] Thus, said geometric pattern will present, along all or part of the length L1, stretches or contractions evolving homothetically. 15
    [0021] [021] With a ratio, between 20 and 1.2, existing between the largest amplitude and the smallest amplitude, the ambition is to create tightening both efficient in terms of acoustic efficiency and the possibility of structural realization (mechanical resistance / integration into the local environment). 20
    [0022] [022] By varying shape in a controlled manner over at least part of said length exposed to the air flow, the profiled structure will be able to behave better in the presence of a turbulent flow (for example in the wake of a rotating part of a turbomachine or of a boundary layer on a wall), inhomogeneous and / or anisotropic, i.e. such that the intensity of the turbulence and / or the size of the vortices varies over time and 'space.
    [0023] [23] It is in this context that the invention proposes several heterogeneous profiles with in particular radial evolutions of the tightening according to a predefined geometric pattern.
    [0024] [24] With a comparable objective of ensuring a compromise between maximized acoustic effect and minimized mechanical stresses, it is proposed that, depending on the length exposed to the air flow, the clamps 5 begin with a tooth and end with a tooth, preferably its top.
    [0025] [025] To differentiate the acoustic treatments by zones, it may be advantageous that, over at least part of said length (1: 1) 5 exposed to the air flow, the profiled structure: - can have, by successive scaling, a geometric pattern which evolves stretched into a first zone and then contracted into a second zone, and comprises a connection between the first and second zones in a transition zone which smooths this connection.
    [0026] [26] Thus, we can locally alter, by a tangent connection, the strict shape of the pattern to round off the line of its profile.
    [0027] [27] To limit the impact of tightening to the zones where the turbulence is the most important and to limit the disturbances induced on the aerodynamic behavior in these zones, and this all the more if several profiled structures, being able to influence the ones on them. others, are provided, is also covered by the invention a set of profiled structures, each having all or part of the aforementioned characteristics: - of which the respective directions of elongation extend radially around a / of the general axis (X), and - of which said amplitude (d) and / or said distance (L2) between two geometric patterns of consecutive tightening (that is to say a said pattern and its stretched or contracted repetition which follows it) is more greater at a radially outer end of the length exposed to air flow than at a radially inner end of that length.
    [0028] [028] Thus, for example in the case where said profiled structures are OGVs located downstream of a fan, and with such amplitudes and / or wavelengths (distances between two successive peaks of hollows or teeth) of greater tightening near the outer casing (at the top of the OGV vanes) than at the foot, near the inter-vein zone, the drawbacks linked to the fact that the vortices at the end of the blades of the fan 6 are moreover absorbed. large size and quite energetic on many turbojets.
    [0029] [029] As a result, it will be understood all the better that the invention is also concerned with: of said general axis, and a stator, the stator or the rotor comprising profiled structures, each having all or part of the aforementioned characteristics, - and in particular a turbomachine in which the stator comprises: - an annular separation wall (inter-veins ), for the separation of the air flow, downstream of the fan, between a primary flow and a secondary flow, - vanes of fixed OGVs for guiding the secondary flow, which define said profiled structures, and / or 15 - blades of fixed IGVs guiding the primary flow, which define said profiled structures.
    [0030] [030] The invention will be better understood if necessary and other details, characteristics and advantages of the invention will appear on reading the description which follows, given by way of non-limiting example with reference to the accompanying drawings.
    [0031] [31] Referring to Figure 1, an aircraft turbojet 10 100 is shown schematically and is defined as follows:
    [0032] [32] The nacelle 12 serves as an outer casing for the various components, 5 among which, at the front (on the left in FIG. 1) an upstream fan 14 (AM).
    [0033] [33] Downstream (AV) of the blower 14, the air flow (locally shown diagrammatically 38 in FIG. 4) is separated by the separator nozzle 16 of an annular wall 160 into a primary air flow and a flow of secondary air.
    [0034] [034] In Figures 2 and 3, we see more precisely the front part 161 of the separator spout 16 comprising the leading edge 164 located most upstream and at which the outer wall 162 of the separator spout 16 joins the internal wall 163 of the separator spout 16, the upper wall 162 forming the internal ferrule of the secondary vein 20. 20
    [0035] [035] For all purposes, it is specified that, in the present text, is axial what extends along or parallel to the longitudinal axis (X) of rotation of the concerned part of the turbomachine, which axis will a priori the general axis of rotation of this turbomachine.
    [0036] [36] In addition, the accompanying drawings, and the descriptions relating thereto, have been defined with reference to the conventional orthogonal coordinate system X-Y-Z, therefore with the X axis as defined above.
    [0037] [37] The separator spout 16 consists of two faces: the outer face 5 of the wall 162 serving as a radially internal limit to the outer annular air passage 20 receiving the secondary flow Fs while the inner face of the wall 163 serves as a radially external limit to the internal annular air passage 18 receiving the primary flow Fp
    [0038] [38] The lower wall 163 of the separator nozzle 16 forms the outer shell 10 of the low pressure compressor 22.
    [0039] [39] Even if the axial offset (X) downstream of the IGV 24 blades relative to the leading edge 164 of the separator nozzle 16 is less compared with that of the OGV 26 blades relative to this same leading edge 164, the portion of the front part 161 directly adjacent to the leading edge 164 of the separator nose 16 is released.
    [0040] [40] In order to reduce the noise generated by the leading edge, for example of a mouthpiece 16, OGV 26, IGV 24, it is therefore possible to provide that this leading edge 164 has a profile 28 with serrations having a succession teeth 30 and recesses 32, as illustrated in the examples. 20
    [0041] [041] But structures other than on a turbomachine, such as the turbojet 10, may be concerned by the solution of the invention and therefore have a leading edge 164 with a profile 28 with serrations having a succession of teeth 30 and hollows. 32.
    [0042] [042] Figure 5 shows schematically an aircraft 100 on which profiled structures 25 such a profile 28 with serrations are present, at the leading edge, on the wings 39, on a pylon 41 supporting an engine 42 of the. aircraft, on a fin 44, a stabilizer 46, a non-faired propeller or blade 48 (open-rotor), or else fixed blades 49 (stator) downstream of an open rotor or non-faired propeller.
    [0043] [43] Furthermore, FIG. 3 locally shows a profile 28 in serrations present on what can be, marked 50, a helicopter blade, a fan blade, a part of the rotor or of the rectifier, a nozzle. leading edge or flap of aircraft wing.
    [0044] [44] All of these airfoils have in common that they generate a boundary layer on the downstream surface, and therefore a turbulent flow.
    [0045] [45] Whatever the application, concerning the profile 28 with serrations, we will consider here: - that this profile belongs to a profiled structure 1 (or aerodynamic profile), around which (of which) flows the 'air which is elongated in a direction Z along which the structure (or the profile) has a length L1 exposed to the air flow, and that, transversely to the direction Z, the structure (or the profile) 1 has a leading edge 164 and / or a trailing edge 165 (the separator beak 16 does not have a trailing edge), at least one of which is profiled and therefore has, along said direction of elongation Z, serrations (profile 28) defined by said teeth 30 and hollow 32 following one another. 20
    [0046] [046] The teeth 30 and hollow 32 follow each other alternately
    [0047] [47] The number of teeth 30 and that of the hollows 32 will be between 3 and 100, to optimize efficiency.
    [0048] [48] In order, as mentioned above, to take into consideration that, in a number of situations, a so-called profiled structure 1 is exposed to an inhomogeneous and / or anisotropic air flow and to ensure a compromise between the targeted noise reduction, the aerodynamic losses to be limited, as well as the mechanical stresses, and the integration of the profiled structure into its environment, it is therefore proposed that, along the leading edge 164 and / or the trailing edge 165 profiled (s) , over a part at least of said length L1, the clamps 28 present (see FIGS. 6.15 in particular) a geometric pattern 11 but the shape of which exhibits a stretching and / or a contraction, in a repetitive manner: - transversely to the direction of elongation (we then have an amplitude which varies; see di to d5 figure 23; see also figure 20), and / or 5 - according to the direction of elongation (we then have a length of the repeating pattern in the direction d 'elongation which varies; see lengths L21 to L25 figure 23; see also figure 21).
    [0049] [49] To achieve these stretching and / or contraction, we modified a periodic tightening profile, defined by a repeated geometric pattern ("reference" pattern, an example of which is shown in gray in Figures 20-22) presenting two characteristic directions (eg the directions X, r of the figures concerned, with r # X, and for example r = Z), this by means of the following transformation: the generic pattern is scaled as desired via a multiplicative factor in one characteristic direction, while in the other characteristic direction the dimensions of the pattern may remain unchanged (Figures 20-21), or follow a scaling (Figure 23).
    [0050] [50] As illustrated in Figures 20-23, these stretches and / or contractions of a “reference” geometric pattern will in this case keep the pattern either in amplitude or in frequency (length of the pattern). 20
    [0051] [051] Thus, FIG. 20, if we take as a pattern reference the one in gray in the figure, we see that according to the length L1, the length or frequency L2 of the pattern is preserved and that on the other hand the amplitude d varies (di, d2 ..).
    [0052] [052] However, for areas with a strong acoustic impact, stretching and / or contractions may be preferred which will vary in amplitude and frequency, as in the example of FIG. 23: frequency L2 and amplitude d of the pattern which vary together : L21, L22, L23 ... and di, d2, d3 ....
    [0053] [053] Once a relationship between amplitude and frequency has been established, it may then be desirable to keep the proportions of the stretched or contracted geometric pattern; see homothety of figure 23. 12
    [0054] [054] In a pattern of tightening, the amplitude d can be measured, along the X axis, between a top 300 of tooth 30 and the bottom 320 of a hollow 32 immediately adjacent.
    [0055] [055] It will also be noted that it could be advantageous to differentiate the acoustic treatments by zone.
    [0056] [56] With a ratio between the largest amplitude and the smallest amplitude between 1.2 and 20, including if necessary taking into account the transition / connection zone 28a mentioned below, the tightening 28 25 will be both efficient in terms of acoustic efficiency, mechanical resistance and integration (fixing) in their local environment.
    [0057] [57] To usefully complete, and for the same purposes, this constraint on d and L2, one can make heterogeneous (non-uniform over their active length L1) the profiles with tightening 28 of all the solutions which follow, with therefore 30 radial evolutions of these tightening; see figure 6.13
    [0058] [058] In particular, the successive teeth 30 and hollow 32 will only extend over a part L1a of this length L1 exposed to the air flow.
    [0059] [059] To further refine this compromise and in particular to prevent the formation of cracks at the level of the hollows, for example FIG. 6, illustrates the advantage that there may be in that the tightenings 28 respect, transversely to the direction of elongation Z, the relation: 0.005d / c50.5, with: - "d" the amplitude of the tightening, in m, and 10 - "c" the chord of the profiled structure, at the location of these tightening, in mr.
    [0060] [060] This chord c will be either the average chord (arithmetic mean of the chord over the length L1) over the length Lia, or that at each serration (a tooth followed by a hollow), along said direction Z; see figures 6,10, and 20-22. 15
    [0061] [061] The search for the aforementioned compromise has also brought to light the interest that there may be in providing a connection, also called a transition zone, 28a - where, by variation - and more precisely overall reduction, not necessarily monotonic - of amplitude d and / or spacing L2 between two patterns of tightening in the direction of elongation, the tightening will gradually join (transition / connection zone 28a) to said smooth part 280 of length L1 which does not have it ; see Figures 7-8, and / or - where the clamps 28 will end (at their end of connection to the smooth part) by a zone 280a which will tangent to said smooth part 280; see 25 figures 7-8.
    [0062] [062] In particular in this situation, at least structural advantage will be gained from the fact that, along the length L1, the clamps 28 begin and / or end with a tooth 30, as illustrated in FIGS. 6, 7, or FIG. 14.
    [0063] [063] Looking even further for this compromise may even lead to choosing that, in particular in the transition zone 28a, a series of at least two 14 (preferably three) teeth 30 and two (preferably three) consecutive hollows 32 from said part L1b of the length devoid of tightening presents: - a distance L2 (strictly) increasing, along said direction of elongation, between two consecutive pattern of tightening (s), and / or - an amplitude d (strictly) increasing, as illustrated in particular in Figures 7,8.
    [0064] [64] Furthermore, by providing a longer chord c on the smooth part 280 than it is at the bottom (tops 320) of the nearest hollow 32, the mechanical structuring and the limiting effect will be reinforced. acoustic, by promoting the definition of the transition zone 28a.
    [0065] [65] In what follows, we will focus the explanations on the example of OGVs 26 in that it is typically a critical zone since it is located just downstream of fan 14.
    [0066] [66] The tightening 28 at the leading edge 164 of the OGV 26 can disrupt the aerodynamic properties of the OGV or make the mechanical integration of the OGV into the vein 20 (FIG. 1) difficult.
    [0067] [67] Figures 11-14 illustrate different situations of such partial tightening zones 28 at the leading edge 164 and / or trailing edge 165. 25
    [0068] [068] Thus: - in Figure 11: Tightening 28 absent at the inner end 281 of the profiles (here absent at the foot of OGV).
    [0069] [069] Regarding the shape of the pattern of serrations 28, it may be rounded undulations, such as sinusoidal undulations, or other shapes, such as the fir tree illustrated in FIG. 16.
    [0070] [70] Depending on the cases, one can also adapt the deflection of structure 1 (in English, "sweep" angle) with respect to the perpendicular to the X axis, at the location of the structure.
    [0071] [71] To increase the decorrelation or phase shift between the noise sources along the span, it is also possible to choose that the leading edge 164 and / or the trailing edge 165 section (s) extend along a general curved line having a concavity oriented upstream, as illustrated for example in Figures 6 or 10.
    [0072] [72] It will also be understood from the above that the structure 1 out of 10 which we have reasoned can typically, as in the non-limiting case of an application to OGVs, belong to a set of profiled structures each having all or part of the aforementioned characteristics, and whose respective directions of elongation Z will extend radially around the axis X. 15
    [0073] [073] Particularly in the non-limiting case of such OGVs 1/26, it is also possible to seek to absorb the drawbacks associated with the end vortices of the blades of the fan 14, where they are larger than elsewhere and quite energetic.
    [0074] [74] For this, we will seek that the frequency of the pattern, namely therefore the distance L2 between two consecutive tightening patterns and / or the amplitude d is greater at the radially outer end 283 of the length L1 than at the radially inner end 281.
    [0075] [75] Thus, the amplitudes and / or wavelengths of the clamps 26 concerned will be greater near the outer casing 53 than near the inter-vein zone (hub 55 / wall 160).
    [0076] [76] It should also be noted that the invention makes it possible to take into account the local properties of the turbulent flow U concerned, such as that upstream of the OGV for example, to define the geometry of the undulations as a function of the distribution. radial of the integral scale of the turbulence (A 30 figure 17) in the wake of the fan 14. 17
    [0077] [77] In connection with this point, figure 6 shows an OGV 1/26 with undulations optimized according to the integral scale A of the local turbulence along the span.
    [0078] [78] Figures 18 and 19 also schematize respectively the intensity of turbulence and the radial evolution of the integral scale of the turbulence, in the wake of the fan 14, up to the OGV 26.
    [0079] [79] In connection with this, figures 24-26 show schematically three situations 15 where, over a part at least of said length (L1) exposed to the air flow, the transformations of the tightening follow laws of evolution respectively. : - linear (figure 24), - logarithmic (figure 25), 20 - parabolic (figure 26).
    [0080] [080] A quadratic, hyperbolic or exponential law may be preferred; this in amplitude (di, d2, d3, ...) and / or in distance (L2, L21, L22, L23, ...), in a direction of elongation.
    权利要求:
    Claims (15)
    [0001]
    CLAIMS 1. Profiled structure for an aircraft or turbomachine for an aircraft, - elongated in a direction of elongation in which the structure has a length (L1) exposed to an air flow (U), and - transversely to which the structure has an edge of attack (164) and / or a trailing edge (165), at least one of which is profiled and has, along said direction of elongation, clamps (28,28a) defined by teeth (30) and recesses (32) successively, the profiled structure being characterized in that, along the leading edge (164) and / or the trailing edge (165) profiled (s) the clamps (28,28a) have a geometric pattern transformed, over at least a part of said length (L1) exposed to the air flow, by successive scaling, via multiplicative factors, according to the direction of elongation (L2, L21, L22, L23) and / or transversely to the direction of elongation (d, di, d2).
    [0002]
    2. Profiled structure according to claim 1 in which, the geometric pattern which is transformed evolving in a non-periodic manner, it preferably evolves: - according to the direction of elongation, according to a linear, quadratic, hyperbolic, exponential law of evolution. or logarithmic, and / or - transversely to the direction of elongation, according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution.
    [0003]
    3. Profiled structure according to any one of the preceding claims, in which the successive scalings (di, d2 ...; L2, L21, L22, L23) vary so that said geometric pattern evolves homothetically.
    [0004]
    4. Profiled structure according to any one of the preceding claims, in which the successive teeth (30) and hollow (32) extend only over a part of said length exposed to the air flow, a part remaining (280) of said length being smooth, devoid of tightening.
    [0005]
    5. A profiled structure according to claim 4, wherein a series of at least three teeth (30) and three consecutive recesses (32), from said portion (280) of the length which is devoid of clamps, has a shape. increasing distance, along said direction of elongation, between two vertices (300,320) of consecutive teeth or hollow (s).
    [0006]
    6. Profiled structure according to any one of the preceding claims which, by the successive scalings, presents a geometric pattern which evolves in a stretched manner in a first zone (31) then in a contracted manner in a second zone (33), and comprises a connection between the first and second zones (31,33) in a transition zone (35) which smooths this connection.
    [0007]
    7. Profiled structure according to any one of claims 1 to 5, which has a connection zone (35) smoothing the connection between two said consecutive geometric patterns, the connection zone being able to extend, in the direction of elongation. , up to 30% of the distance (L2) between two patterns called consecutive geometric patterns.
    [0008]
    8. A profiled structure according to any one of the preceding claims, in which, along the length exposed to the air flow, the clamps (28) begin and / or end with the apex of a tooth (30).
    [0009]
    9. A profiled structure according to any one of the preceding claims, in which a ratio of between 20 and 1.2 exists between the largest amplitude and the smallest amplitude. 25
    [0010]
    10. Profiled structure according to any one of the preceding claims wherein the number of teeth (30) is between 3 and 100.
    [0011]
    11. Set of profiled structures, each according to any one of the preceding claims, of which the respective directions of elongation extend radially around an axis of revolution (X), and of which said distance (L2, L21, L22 , L23, ...) and / or said amplitude (d, di, d2, d3, ...) of the clamps (28) is greater at a radially outer end of the length exposed to air flow than 'at a radially inner end of this length.
    [0012]
    12. Turbomachine comprising a rotor (14,48) and a stator (49,55), the stator and / or the rotor comprising profiled structures (1), each according to any one of claims 1 to 10.
    [0013]
    13. Turbomachine according to claim 12, comprising two rotors (480a, 480b), rotatable parallel to said general axis (X), one and / or the other of the rotors comprising profiled structures (1), each according to l. any of the preceding claims.
    [0014]
    14. Turbomachine according to claim 12 or 13, wherein the stator comprises: - an annular separation wall (160) for the separation of an air flow, downstream of the fan, between a primary flow and a flow. secondary,
    [0015]
    15 - vanes (26, OGV) fixed for guiding the secondary flow (Fs), which define said profiled structures, and / or - vanes (24, IGV) fixed for guiding the primary flow (Fp), which define said structures profiled. 20
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    WO2020025886A1|2020-02-06|Turbomachine with coaxial propellers
    FR3093770A1|2020-09-18|Non-axisymmetric secondary vein portion
    BE1024827A1|2018-07-10|AUB GLACIOPHOBE OF AXIAL TURBOMACHINE COMPRESSOR
    FR3073018A1|2019-05-03|REINFORCED HOOD FOR TANK FOR DARK
    同族专利:
    公开号 | 公开日
    US20200148325A1|2020-05-14|
    GB201915075D0|2019-12-04|
    GB2579137A|2020-06-10|
    FR3087483B1|2022-01-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CN104612758A|2014-12-19|2015-05-13|中国民航大学|Low-pressure turbine blade with low loss|
    US20180023398A1|2016-07-22|2018-01-25|General Electric Company|Blade with parallel corrugated surfaces on inner and outer surfaces|
    US20180057141A1|2016-08-31|2018-03-01|David E. Shormann|Biomimetic airfoil bodies and methods of designing and making same|
    US7413408B1|2007-02-22|2008-08-19|Samuel B Tafoya|Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades|
    US8469313B2|2010-02-16|2013-06-25|The Boeing Company|Aerodynamic structure having a ridged solar panel and an associated method|
    GB201016455D0|2010-09-30|2010-11-17|Imp Innovations Ltd|Fluid flow modification|
    US9249666B2|2011-12-22|2016-02-02|General Electric Company|Airfoils for wake desensitization and method for fabricating same|
    US10539025B2|2016-02-10|2020-01-21|General Electric Company|Airfoil assembly with leading edge element|
    CN209192204U|2018-11-20|2019-08-02|辽宁壮龙无人机科技有限公司|Propeller and unmanned plane|FR3073016B1|2017-10-30|2019-10-18|Safran Aircraft Engines|MODULATION OF THE SERRATIONS IN THE END OF DAWN|
    JP2019178636A|2018-03-30|2019-10-17|三菱重工航空エンジン株式会社|Aircraft gas turbine|
    法律状态:
    2019-09-19| PLFP| Fee payment|Year of fee payment: 2 |
    2020-04-24| PLSC| Publication of the preliminary search report|Effective date: 20200424 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 3 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1859663A|FR3087483B1|2018-10-18|2018-10-18|PROFILE STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT|FR1859663A| FR3087483B1|2018-10-18|2018-10-18|PROFILE STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT|
    US16/657,278| US20200148325A1|2018-10-18|2019-10-18|Profiled structure for an aircraft or turbomachine for an aircraft|
    GB1915075.4A| GB2579137A|2018-10-18|2019-10-18|Profiled structure for an aircraft or turbomachine for an aircraft|
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