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    • 专利摘要:
    The invention relates to a profiled air flow structure having a profiled leading edge (164) having, along a leading edge line (164a), a serration profile having a succession of teeth (30) and recess (32), characterized in that it comprises an acoustically absorbing porous region (52) located towards the bottom of the recesses (32).
    公开号:FR3078099A1
    申请号:FR1851360
    申请日:2018-02-16
    公开日:2019-08-23
    发明作者:Fernando Gea Aguilera；Simon Paul Gruber Mathieu；Jean Xavier Riou Georges
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    PROFILE STRUCTURE IN WALLS WITH SURFACES
    TREATED
    INTRODUCTION The present invention relates to the field of aeroacoustic management of profiled air flow structures, such as for example fixed blades in an aircraft turbomachine or in a test bench of such turbomachines, or a nozzle turbomachine primary air inlet.
    This type of fixed vane is found for example on OGV outlet guide vanes, or rectifiers, arranged downstream of a rotating body to straighten the air flow.
    An example will be given for a double flow turbomachine with a fan (front) and a rectifier arranged in a secondary stream.
    In particular in Ultra-High Bypass Ratio turbojets (UHBR; configuration of faired fan motor with very high dilution rate, beyond 15), it is envisaged to increase the diameter of the fan and to reduce the length of the aircraft suspension pod, thereby reducing the distance between the fan and the IGV (Inlet Guide Vanes) inlet vanes, the OGVs and the primary air inlet nozzle. In this type of engine, the interaction of the fan's wake with IGVs, OGVs and the nozzle is one of the dominant broadband noise sources.
    Beyond this observation in a turbomachine, other areas of turbomachinery, but also of profiled structures of air flow (wings, open-rotor blades - open rotor -... etc) are faced with aero-acoustic management issues.
    It has therefore already been proposed, in particular in the field of aircraft, to use profiled air flow structures having a profiled leading and / or trailing edge having, along a line of leading and / or trailing edge, a tightening profile therefore provided with a succession of teeth and hollows.
    Thus, this tightening profile extends along the leading and / or trailing edge, in other words in the direction of elongation of the structure at the leading and / or trailing edge.
    In particular on the reduced rope profiles, but also on the closed profiles - (line of) leading and / or trailing edge elongated along a line or direction of elongation closed on itself, perimeter, as on a turbomachine primary air inlet nozzle - noise is mainly produced at the leading and / or trailing edge, more precisely in the hollows of the clamps where the pressure fluctuations are more intense.
    Regarding the term "rope" used in this text, it should be noted that if there is not strictly a "rope" as in the case of a beak (referenced 16 below) of separation between the primary and secondary flows, we will consider that the expression "in the direction of the chord (marked 40 below) of the profile" then corresponds to the direction of what is called below "general axis (X)" or "axis X ”, namely the axis along which the fluid flow generally flows over the profiled structure concerned, this axis being typically:
    - the longitudinal axis of the turbomachine (axis of revolution) and / or of the aircraft in question,
    - And / or transverse, even perpendicular, to the elongation of the profiled structure, which extends in said "direction of elongation".
    It will be understood that the expression "transverse (e)" does not imply strict perpendicularity.
    The invention aims to attenuate the intense local pressure fluctuations, mentioned above, by using a porous surface (or an acoustic treatment) at the level of the hollows of the clamps.
    [012] It is thus proposed that the aforementioned profiled structure comprises an acoustically absorbent porous region located towards the bottom of the hollows of the clamps.
    To maximize the noise reduction, it may be useful for the center of the region with acoustic treatment or porous surface to be placed at a distance downstream of the leading and / or trailing edge of the profile considered, depending (c that is, as close as possible) to the position where the pressure fluctuations are greatest.
    [014] It is therefore advisable:
    - that, in the direction of the rope, the tightening profile has a maximum amplitude, h, and
    - that the center of the acoustically absorbent porous region is located at a distance downstream from the leading and / or trailing edge, at the bottom of the troughs such that:
    d = h / 10, to within 30%.
    An advantage is the taking into account of the thickness of the profiled structure, such as a blade, which causes the region where the pressure fluctuations on the surface of this profiled structure to move downstream of the trough.
    In the present text, all the dimensions (d, h, ... etc.) are to be considered on the same scale: in meters.
    [017] For similar considerations, and / or in order to optimize the surface to be treated in order to reduce the acoustic radiation, it is also proposed:
    - that, in the direction of the leading and / or trailing edge line, the tightening profile has a distance between two consecutive teeth, X, and
    - that the acoustically absorbent porous region has:
    - in the direction of the leading and / or trailing edge line, two limits separated by a distance a such that a = Λ / 3, to within 30%,
    - in the direction of the rope, two limits separated by a distance b such that b = h / 3, to within 30%.
    An advantage is that the acoustic treatment or the porous surface will be placed at the point where the pressure fluctuations on the surface of the blade are maximum, which optimizes the surface to be treated to reduce the acoustic radiation. .
    In terms of material solutions to be used, it is proposed:
    - That the acoustically absorbent porous region considered comprises a porous foam having pores of cross section less than a / 4 or b / 4, at the surface (that is to say at the surface) of said leading edge and / or of profiled leak from the profiled structure, and / or,
    that said region comprises, on the surface of said profiled leading and / or trailing edge of the profiled structure, a micro-perforated sheet or resonant cavities covering a porous foam having pores of cross section less than a / 4 or b / 4.
    The advantage is to reduce the pressure fluctuations and therefore the noise levels, knowing that the size of the cavities will have an influence on the frequency range to be attenuated.
    [021] It may also be preferred that said porous acoustically absorbent region comprises a Helmholtz resonator.
    [022] In fact, the operation of Helmholtz resonators, in which the depth of the cavities is closely linked to the target frequency to be attenuated, can be found on other parts of a turbojet engine, such as on nacelle acoustic treatments. .
    [023] As already noted, it is in particular in connection with aircraft that the invention finds its application.
    [024] It is therefore specified that the profiled structure will advantageously be one of:
    - an aircraft and turbomachine structure with front fan, or,
    - an aircraft wing, an aircraft wing beak or flap, an aircraft engine support pylon, a fin, an aircraft stabilizer, a helicopter blade, a propeller, or again
    - of the following parts of a turbomachine adapted to propel an aircraft:
    - a leading and / or trailing edge of an annular wall separating an air flow, downstream of a fan of the turbomachine, between a primary flow and a secondary flow,
    - first fixed vanes for guiding the primary flow (Fp),
    - second fixed vanes for guiding the secondary flow (Fs).
    [025] Indeed, in the above cases, the presence of a tightening profile as proposed makes it possible to deal with a delicate problem linking aero-acoustic management issues both static (presence of air intake structures, blades ...) as dynamic (blades rotation, taking into account certain flight configurations ...) and this all the more if it is a turbomachine with upstream fan on which the problems of acoustic / aerodynamic interference are very complex, and the noise generated is particularly significant.
    [026] In this regard, it was found that the acoustically absorbent porous region must target the place where the noise of interaction with the turbulence of the wake is generated. Thus, we will be able, via the solutions proposed here:
    - optimizing the surfaces to be treated, by limiting them in their extent, thus making it possible to limit the aerodynamic losses induced by the presence of these porous acoustically absorbing regions which disturb the fluid flows,
    - reduce the masses involved, for example thanks to the cavities of the porous surface or the low density of the acoustic treatments,
    - limit manufacturing costs compared to structures with acoustic treatment present on very large surfaces.
    [027] In terms of shapes, it is proposed that the teeth and hollows of the tightening profile individually have a wavy shape, with rounded or more pointed vertices.
    [028] It has indeed been found that these forms prove to be effective.
    [029] Rounded tops make it possible to reduce concentrations of mechanical stresses that are too strong locally, which increases the service life of the part in service.
    Sharp peaks allow increased noise reduction.
    [031] Furthermore, providing teeth and hollows individually having a shape with locally rectilinear side walls makes it possible to introduce a certain decorrelation between the sources of noise along the leading and / or trailing edge.
    [032] The air flow generated, axially (X axis below, also called general axis) downstream of a rotating structure, as downstream of a turbomachine fan towards a primary air stream nozzle, or which can be influenced by a disturbing structure, such as for example an aircraft fuselage with respect to a wing, or a drift with respect to a stabilizer, is swirling and is strongly influenced by a direction of rotation of the air or that of the fan, especially as the repeated passages of the blades of the fan in the air flow or certain conditions of contact with the "disturbing structure" create shock waves. For the blades of the fan, this leads to the appearance of lines at the harmonics of the frequency of rotation of the motor shaft.
    To take account of these phenomena and so that the surfaces of the teeth can be as fully active as possible in the expected acoustic effect, it is proposed that the teeth develop individually in an inclined manner relative to a parallel to said general axis. (X).
    [034] In the case of a fan rotation, the teeth will be inclined so as to be oriented towards the direction of rotation - generally oblique with respect to said axis X - of the rotary flow generated therefore by the fan. In other words:
    - the blower (upstream) being adapted to rotate in a predetermined direction around the aforementioned general axis (X), so that the air flow downstream of the blower is generally obliquely oriented relative to this axis (X) ,
    - The teeth can then be, circumferentially around said general axis (X), inclined (laterally) towards the generally oblique orientation of the air flow downstream of this blower, to make it generally face.
    In particular, an effect of limiting the acoustic impact on the IGVs was then observed.
    [037] The teeth will therefore be, in this case, individually non-symmetrical with respect to a perpendicular to the line of the leading and / or trailing trailing edge passing through the tooth in question.
    Another way of presenting things will be to consider that, from a first place (for example from a first end, or from a zone defined on a perimeter) to a second place (such as a second end, opposite the first or another area along the perimeter), the teeth of the profile in clamps will be individually inclined (laterally) towards the second place.
    [039] A priori the inclination will be the same for all the teeth. However, the teeth may have heterogeneous inclinations, different depending on the location.
    If one is located rather along the elongation at the leading and / or trailing edge of a said structure of the vane type (of rotor or stator), blade (of a propeller for example) or wing (plane, for example), the profiled structure:
    - which will have a span along the leading and / or trailing edge line, between a first end and a second end,
    - will then present said inclinations of teeth each oriented towards one of the ends.
    [041] The invention will be better understood if necessary and other details, characteristics and advantages of the invention may appear on reading the description which follows, given by way of nonlimiting example with reference to the accompanying drawings.
    BRIEF DESCRIPTION OF THE FIGURES
    - Figure 1 is a diagram in longitudinal section (axis X) of a conventional aircraft turbomachine;
    - Figure 2 shows schematically the upstream area (spout) of the partition wall between the primary and secondary flows, with a solution according to the invention;
    - Figure 3 can be either detail III of Figure 2, must a local diagram of profile in tightness present on what can be a helicopter blade, a blade of the fan, the rotor or the stator, a nozzle leading edge or wing flap of an aircraft;
    - Figure 4 is detail IV of Figure 1;
    - Figures 5-8 show schematically various forms of tightening profiles according to the invention;
    - Figure 9 shows schematically an aircraft carrying structures according to the invention;
    - Figure 10 is an enlargement of the solution of Figure 6;
    - Figure 11 shows section XI-XI;
    - Figures 12-13 show schematically, in a same section as that of Figure 11, ways of producing a porous region on a profile with clamps according to the invention, and air flow lines;
    - Figures 14-17 show schematically profiles with clamps according to the invention, and air flow lines (Figures 15-16).
    DETAILED DESCRIPTION [042] If we refer to FIG. 1, an aircraft turbojet 10 of an aircraft 100 is shown very schematically and is defined as follows:
    [043] The nacelle 12 serves as an outer casing for the various members, including, at the front (on the left in FIG. 1), an upstream fan (AM).
    [044] Downstream (AV) of the fan 14, the air flow (locally shown diagrammatically 38 in FIG. 4) is separated by the separating nozzle 16 from an annular wall 160 into a primary air flow and a flow of secondary air. The primary air flow passes through an internal annular air passage or primary stream 18 by entering the low pressure compressor 22 at the level of the inlet guide vanes 24 IGV, also called first vanes. The secondary air flow is deflected by the separating nozzle 16 in an external annular air passage 20 (secondary stream) in the direction of the outlet guide vanes 26 OGV, also called second blades, then towards the engine outlet.
    In FIG. 2, the front part 161 of the separating spout 16 comprising the leading edge 164 situated most upstream and at which the external wall 162 of the separating spout 16 joins the internal wall is viewed more precisely. 163 of the separating spout 16, the upper wall 162 forming the inner ring of the secondary stream 20.
    [046] For all purposes, it is specified that, in the present text, is axial which extends along or parallel to the longitudinal axis (X) of rotation of the part concerned of the turbomachine, which axis will be a priori the general axis of rotation of this turbomachine. Is radial (Z axis) and is circumferential which extends radially to and around the X axis, respectively. Is internal or internal and external or external which is radially, with respect to the X axis. Thus, the internal wall 163 is the radially internal wall of the separating nozzle 16. Furthermore, the upstream and downstream references are to be considered in connection with the flow of gases in the (part of) turbomachine considered: these gases enter upstream and exit downstream, circulating generally parallel to the aforementioned longitudinal axis of rotation.
    [047] In addition, the accompanying drawings, and the descriptions which relate to them, were defined with reference to the conventional orthogonal coordinate system X-Y-Z, with therefore the X axis as defined above.
    [048] The separator spout 16 is hollow, the external face of the wall 162 serving as a radially internal limit to the passage of external annular air 20 receiving the secondary flow while the internal face of the wall 163 serves as a radially external limit to the passage of internal annular air 18 receiving the primary flow.
    [049] The bottom wall 163 of the separator spout 16 forms the outer shell of the low pressure compressor 22.
    Even if the axial offset (X) downstream of the IGV vanes 24 with respect to the leading edge 164 of the separator nozzle 16 is less compared with that of the OGV vanes 26 with respect to this same leading edge 164, the portion of the front part 161 directly adjacent to the leading edge 164 of the separator spout 16 is released.
    [051] For the induced effect of aero-acoustic management by limiting the noise generated by this area, provision can therefore be made for this leading edge 164 to have a profile 28 with clamps having a succession of teeth 30 and hollows 32, as shown in the examples in Figures 5-11.
    [052] But structures other than on a turbomachine, such as the turbojet engine 10, may be concerned by the solution of the invention and therefore have a leading edge 164 with profile 28 with clamps having a succession of teeth 30 and hollows 32 [053] Figure 9 shows schematically an aircraft 100 on which profiled structures with such profile 28 with clamps are present, at the leading edge, on the wings 38, on a pylon 41 for supporting an engine 42 of the aircraft, on a fin 44, a stabilizer 46, a propeller or blade 48 of open-rotor.
    [054] Furthermore, Figure 3 shows locally a profile 28 in clamps present on what can be, marked 50, a helicopter blade, a blade of the fan, the rotor or the stator, a beak edge attack or wing flap of an aircraft.
    [055] All of these aerodynamic profiles have in common the generation of a boundary layer on the downstream surface, and therefore a turbulent flow.
    [056] Whatever the application, concerning profile 28 with clamps, we will here consider that it has undulations which define:
    - in a direction (L) of elongation of the leading edge 164, a repeating elementary geometry, two identical undulations (or quasi-identical, when two consecutive teeth have small variations in geometry, at +/- 25%) of two successive elementary geometries, such as 34,36 Figures 5-6, in said direction L having between them, in this direction, a distance, À (in m), and
    - a maximum amplitude, h (in m), perpendicular to this direction L, [057] The maximum amplitude h is defined as the maximum distance, following a perpendicular to this direction L, between the vertex - the most prominent if exist - teeth 30 and the bottom of the hollows 32 - the deepest if there are -, as seen in Figure 5 assuming an elementary geometry with several undulations, preferably two - two different teeth 30 and two different hollows 32 -.
    [058] It is also specified that:
    - direction L is the direction along which the leading edge line 164a extends which can be confused with the leading edge 164 if it is considered over its entire length. This direction L can be rectilinear (case for example of a wing, a drift, a stabilizer), or curved, even closed on itself (possible case for example of a propeller, a vane of blower, rotor or rectifier, or separator nozzle 16),
    - the direction of the maximum amplitude, h, can be typically parallel to the general axis X (Figure 2, Figure 9 in part); but can also be oriented in another direction, for example in the case of a helicopter blade (direction then a priori perpendicular to the Z axis).
    [059] According to the invention, to attenuate locally intense pressure fluctuations, we will therefore provide on the profiled structure concerned at least - a porous region 52 acoustically absorbent located towards the bottom of the troughs 32.
    It has been found that to favor this attenuation, it could be preferable for the center of the (each) region 52 with acoustic treatment or porous surface (whether rectangular, elliptical, or other) to be located at a distance d (in m) downstream (AV) of the profiled leading edge 164 / line 164a), at the bottom of the troughs (124) such that:
    d = h / 10, to within 30%.
    [061] In order to reach most of the region with high pressure fluctuations, it is further proposed that the porous region 52 acoustically absorbent considered presents:
    - in the direction of the leading edge line 164a (i.e. in the direction of the span or elongation), two limits separated by a distance a (in m) such that a = Λ / 3, to within 30%,
    - in the direction of the cord 40, two limits separated by a distance b (in m) such that b = h / 3, to within 30%.
    [062] Figures 10,11 schematize this.
    [063] The lengths a and b are used to size the edges of the rectangles or other shapes where the surface is acoustically treated. In the area where a is of the order of λ / 3, where the pressure fluctuations at the wall have been found to be the strongest, the effect of the porosity via the acoustically absorbent structure must be effective.
    [064] The margins indicated of 30% must allow the resolution of technical uncertainties / inaccuracies.
    In the claimed applications, the aim is to obtain a significant reduction in the surface of the structure / part considered, therefore aerodynamic losses, compared to what it would have been without the solution of the invention, with therefore a effect on broadband noise reduction. The porous surface or acoustic treatment targets the place where the noise of interaction with the turbulence of the wake is generated. Thus, a major contribution is considered to be that of optimizing the surface to be treated in order to reduce the acoustic levels.
    In connection with the example of FIG. 5, where the elementary geometry has several undulations, two in the example, the distance λ in the direction L is supplemented by other distances in the same direction L, here two, À1, À2, relating to the distances between two consecutive vertices of different but successive teeth.
    [067] In accordance with the aforementioned preferred rules, it will be considered preferable here, for the reasons already indicated, that: a = A1 / 3 or a = A2 / 3 (to within 30%), the greatest distance being preferably retained, therefore here we will prefer a = A 1/3 (to within 30%).
    [068] From a practical point of view, several technical solutions having an impact on the surface of the structure in the region 52 acoustically treated can be provided.
    [069] Two were preferred, making it possible to reconcile efficiency in reducing the acoustic response at the level of the hollows 32 and technical mastery, including in terms of maintenance.
    In the solution shown diagrammatically in FIG. 12, the porous region 52 which is acoustically absorbent comprises a porous foam 54, which may be metallic, having pores with a section (in m) less than a / 4 or b / 4. An alternative is that the pores are less than 1/10 mm, in section.
    [071] The porous foam 54 is present on the (outer) surface 56 towards said profiled leading edge 164 - where it could then define the shape of the profile - and can occupy a significant part of the thickness of the profiled structure, or even all this thickness, as in the figure.
    [072] To maintain this mass of foam, it can be provided that it has downstream (AV) a projecting tooth 58 shape, fixed, for example glued, in a recess 60 front of the body 62 of the structure, which could for example be pylon 41.
    One or more bars 64 could further anchor the mass of foam with its tooth 58 in the body 62.
    In the solution shown diagrammatically in FIG. 13, the porous region 52 which is acoustically absorbent comprises, on the surface 56 of the profiled structure, a material 66 with a micro-perforated sheet or with resonant cavities covering a porous foam 54 having pores of section (in m) less than a / 4 or b / 4. An alternative is still that the pores are less than 1/10 mm, in section.
    [075] A Helmholtz resonator can thus be formed in the region of this acoustically absorbent porous region 52.
    [076] With both the material 66 and the foam 54 on the surface, a surface condition 56 compatible with low aerodynamic losses can be obtained.
    [077] Screws 68 could secure the fixing of the material 66 in the body 62 of the structure.
    [078] In connection with FIGS. 14-16, we will now return to the specific case of application to IGV 24 of the solution of the invention, with its acoustically absorbent porous regions 52.
    [079] To benefit from favorable aerodynamics, in particular at the air inlet of the low pressure compressor 22, it is proposed here that around the X axis, at least some of the hollows 32 of the profile 28 with clamps are angularly offset (circumferentially) relative to the angular position of the IGV 24 vanes, so that these recesses 32 are interposed between two first circumferentially IGV 24 vanes 24, as illustrated.
    In these figures, the IGVs 24 are even placed axially (X) in the continuity of the teeth 30; more precisely each IGV 24 has been placed substantially in alignment, along the X axis, from the top of the tooth 30 which precedes it upstream (AM).
    [081] Figure 14, this alignment is parallel to the general axis X. And the teeth 30, which each have a vertex 31, are individually symmetrical therein with respect to a parallel to the axis X, this parallel passing through the vertex 31 of tooth 30 considered (see parallel X1 for example).
    [082] Figures 15-16, the IGVs 24 are inclined in the X-Y plane relative to the X axis; angle β. The teeth 30 are, circumferentially around this axis X, each inclined by the same angle β (but this angle could vary), in the same direction as that, common, of the IGVs 24. In fact, here, account has been taken of the influence of the rotation of the fan 14, which is supposed to rotate in the positive direction of the Y axis (see FIG. 1 and arrowhead in the direction L in FIG. 2).
    [083] Figure 9, the angle of inclination of the profile 28 in tightening is marked a to indicate that in particular out of provision downstream of a blower, the angle β will not necessarily be respected, but that this angle d the inclination a here takes account of the direction of the air flow which arrives on the profile 28.
    [084] An angle α, β, or even β ’(cf. FIG. 17, see below) of between 30 and 60 °, preferably between 35 and 45 °, would be appropriate, having regard to the first results of tests carried out. This is not limiting.
    [085] Thus, both the (leading edges of) IGV 24 and the (leading edges of) teeth 30 are in fact generally facing the air flow 38 whose overall oblique orientation U is the result of its components Ux along X and Uy along Y, taking into account the direction here of rotation of the fan 14.
    [086] The teeth 30 are individually asymmetrical axially by contribution to a parallel (see ΧΊ and X’2 Figures 10-11) to said general axis X, this parallel again passing through the apex 31 of the tooth considered.
    [087] The purpose of these positions can be considered to be twofold. First, it is a question of avoiding the interaction between the accelerated and turbulent flow produced in the hollows 32 and the leading edge 25 of the IGVs (Figures 14-16). This can indeed contribute significantly to the broadband noise of the low pressure compressor 22. Secondly, this technical solution could be used to optimize the air intake of low pressure compressor 22 and to reduce possible aerodynamic losses.
    [088] As shown in FIGS. 15-16, said first blades / IGV 24 may individually have a line 240 of average camber along their chord, to take account of the influence of the rotation of the fan 14.
    [089] The angle of inclination of the flow produced by the fan 14 depends on the engine speed, and therefore on the speed of rotation of the fan. Also, it is envisaged to orient the teeth 30 in the direction of the average camber of the IGVs or of the camber at the level of the leading edge 164. The values of angles retained may be averaged along the span. or lengthening of the IGV or take the values of the camber of the IGV at the head of the blade.
    [090] As illustrated and in this example, the upper surface 241 is directed in the positive direction Y, the lower surface on the opposite side.
    [091] To further limit the acoustic impact on the IGVs 24 of the swirling air flow that the fan 14 therefore generates downstream, it is also proposed, as shown in FIGS. 15-16, that the teeth 30 be, circumferentially around said general axis X, oriented generally in the direction of a tangent 42 to said line 240 of average camber of the IGV vanes 24, at their leading edges 25. The tangent forms a non-zero angle (β) relative to the direction of the general axis (X) of the turbomachine.
    [092] An advantage is then to align the teeth 30 in the direction of the camber of the IGVs and again to be able to adapt the geometry of the air intake of the compressor 22 to its environment. The direction of the air flow downstream of the blower 12 depending on its speed of rotation, aligning the teeth in the direction of the IGVs (which are a fixed part), could therefore be a good compromise between variable speeds and geometries to be fixed.
    [093] Note, however, that the direction of flow upstream of the IGV blades (or the teeth of the separator nozzle 16, moreover) will not necessarily be aligned with the camber of the IGVs.
    [094] Systematically, along the general axis X, in the preferred embodiments illustrated, the teeth 30 are located upstream relative to the leading edges 2 of the IGV vanes 24, as can be seen in the figures.
    [095] However, for a dimensional limitation which may exist between the leading edge of the nozzle and the IGV blades (typically of the order of 1-5 cm), as well as to have the possibility of increasing the size / l ' amplitude of the teeth 30, it is proposed that, still in this direction of the axis X, the bottoms 320 of the hollows 32 of the profile 28 with clamps belong at least for some to a first surface, transverse to said axis X, identified Y1 FIG. 15 and Y2 figure 16, positioned at the level (figure 15) or more downstream (AV; figure 16) than a second surface also transverse to the axis X, marked ΥΊ figure 15 and Y'2 figure 16, to which belong to the minus some of the leading edges 25 of the IGV blades 24. Despite the illustrations, this is a priori independent of the shape of the tops of the teeth 30 and of the bottoms 320 of the hollows 32.
    [096] In this regard, the teeth 30 and hollow 32 of the clamping profile 28 will individually have a wavy shape, with rounded (Figure 15) or sharp (Figure 16) vertices, this to promote effective noise reduction by minimizing the mechanical stresses supported by this geometry.
    [097] As for the shape of the side walls, identified 300 in FIG. 16 of these teeth 30 and hollow 32, they may be presented individually and locally as rectilinear (FIG. 16), this in order to promote the decorrelation of the noise sources along the edge. to facilitate the fabrication of this geometry.
    We will now return to the inclination of the profiled structure, in the case of a structure having, in the direction of its leading edge line 164a, opposite ends 70a, 70b, and therefore in a way a wingspan (like the length of the wing or that of the pylon 41), even if one (at least) of these ends is a root, as on a wing, see the example in figure 9 where the structure considered is - substantially linear along the Y axis.
    [099] In such cases (blades, blades, propellers, pylon, daggerboards, etc.) it will be noted that the inclinations of the teeth 30 will be favorably oriented each and all towards one of these ends (called the second end), that it is, for example for a wing, the root 70a or the free end 70b.
    [100] In the case of profiled "span" structures, the angle a will be located in the general plane of the structure, such as the plane P which contains the X-Y axes for the wings 38 in Figure 9.
    [101] It is also possible that the inclinations of the teeth 30 vary along the span / elongation (direction L).
    [102] Note also that the comments above in relation to the figures have only referred to situations on the leading edge. However, trailing edges could be concerned, as an alternative or complement, such as (lines of) trailing edges 164b with profile 28 in wing clamps, as shown in FIG. 9, other turbomachine or aircraft structures provided trailing edge may also be affected by the invention. As a trailing edge on an annular wall, mention may be made of a nozzle, at the outlet of the primary and secondary jets.
    [103] At the trailing edge, the noise source can typically be linked to the interaction between the turbulence in the boundary layer of the profile and this trailing edge.
    [104] FIG. 17, a situation has also been diagrammed in which, the turbomachine being always with a front fan (14 above) and has a general axis (X) around which this front fan can rotate, the teeth 30 are, circumferentially around the general axis (X), individually inclined (angle β ') in the direction of the average camber of the first IGV 24 blades.
    [105] It may also be noted that, in FIG. 15, the teeth 30 are further, circumferentially around the axis X, individually inclined in the direction of the camber of the IGV blades, at their leading edges 25. This angle, marked β, of the teeth 30 will be identical or not to the angle a of the speed vector U1 which marks the general direction of the flow downstream of the fan.
    [106] In the attached figures, it will be understood that those where a speed vector (U, U1 ...) is shown upstream of the leading edge illustrate cases where the teeth are oriented towards the direction of flow.
    权利要求:
    Claims (17)
    [1" id="c-fr-0001]
    1. Profiled air flow structure having a leading edge (164) and / or trailing edge having, along a line of leading edge (164a) and / or trailing edge (164b), a profile ( 28) in clamps having a succession of teeth (30) and hollows (32), characterized in that it comprises an acoustically absorbent porous region (52) located towards the bottom of the hollows (32).
    [2" id="c-fr-0002]
    2. Profiled structure according to claim 1 in which:
    - in the direction of the rope, the profile (28) in tightness has a maximum amplitude, h, and
    - the center of the acoustically absorbent porous region (52) is located at a distance downstream from the profiled leading or trailing edge (164), at the bottom of the troughs (32) such that:
    d = h / 10, to within 30%.
    [3" id="c-fr-0003]
    3. Profiled structure according to claim 1, in which:
    - in the direction of the leading or trailing edge line (164a) (164b), the profile (28) in tightness has a distance between two consecutive teeth, λ,
    - in the direction of the rope (40), the tightening profile has a maximum amplitude, h, and
    - the acoustically absorbent porous region (52) has:
    - in the direction of the leading and / or trailing edge line, two limits separated by a distance a such that a = Λ / 3, to within 30%, - in the direction of the chord, two limits separated by a distance b such that b = h / 3, to within 30%.
    [4" id="c-fr-0004]
    4. Profiled structure according to claim 2, in which:
    - in the direction of the leading and / or trailing edge line (164a) (164b), the profile (28) in clamps has a distance between two consecutive teeth, λ, and
    - the acoustically absorbent porous region (52) has:
    - in the direction of the leading and / or trailing edge line, two limits separated by a distance a such that a = Λ / 3, to within 30%,
    - in the direction of the rope, two limits separated by a distance b such that b = h / 3, to within 30%.
    [5" id="c-fr-0005]
    5. Profiled structure according to any one of the preceding claims, which is one of an aircraft structure (100,101,38,41,44,46) and a turbomachine structure with front fan (14).
    [6" id="c-fr-0006]
    6. Profiled structure according to any one of claims 1 to 4, which is one of:
    - an aircraft wing, an aircraft wing beak or flap, an aircraft engine support pylon, a fin, an aircraft stabilizer, a helicopter blade, a propeller,
    - one of the following parts of a turbomachine adapted to propel an aircraft:
    - a leading edge (164) or trailing edge of an annular wall (160) for separating an air flow, downstream of a fan of the turbomachine, between a primary flow and a secondary flow,
    - first vanes (24, IGV) fixed for guiding the primary flow (Fp),
    - Fixed second blades (26, OGV) for guiding the secondary flow (Fs).
    [7" id="c-fr-0007]
    7. Profiled structure according to any one of the preceding claims, in which the acoustically absorbent porous region (52) comprises a porous foam (54) having pores of cross section less than a / 4 or b / 4, on the surface of said edge d profiled attack (164) of the profiled structure.
    [8" id="c-fr-0008]
    8. Profiled structure according to any one of claims 1 to 6, in which the acoustically absorbent porous region (52) comprises, on the surface of the profiled structure, a material (66) with microperforated sheet metal or with resonant cavities covering a porous foam. (54) having pores of section less than a / 4 or b / 4.
    [9" id="c-fr-0009]
    9. Profiled structure according to any one of the preceding claims, in which the acoustically absorbent porous region (52) comprises a Helmholtz resonator.
    [10" id="c-fr-0010]
    10. Profiled structure according to any one of the preceding claims, in which the teeth (30) and hollow (32) of the profile in clamps individually have a wavy shape, with vertices (31) rounded or more pointed.
    [11" id="c-fr-0011]
    11. Profiled structure according to any one of the preceding claims, in which the teeth (30) and hollow (32) of the profile in clamps individually have a shape with side walls (300) locally rectilinear.
    [12" id="c-fr-0012]
    12. Profiled structure according to any one of the preceding claims, in which, along the leading edge (164a) and / or trailing line (164b), the teeth (30) of the tightened profile each have an apex (31) and are individually non-symmetrical about a perpendicular to the line (164a) of the leading edge passing through the tooth (30) considered.
    [13" id="c-fr-0013]
    13. Profiled structure according to any one of the preceding claims, in which, along the leading edge (164a) and / or trailing edge (164b), from a first place to a second place, the teeth (30 ) of the profile in locks each have a vertex (31) and are individually inclined towards the second place.
    [14" id="c-fr-0014]
    14. Profiled structure according to claim 13:
    - which has a wingspan along the leading and / or trailing edge line, between a first end (70a) and a second end (70b), and
    - in which the inclinations of the teeth (30) are each oriented towards one of said ends.
    [15" id="c-fr-0015]
    15. Turbomachine (10) for aircraft, comprising the profiled structure according to any one of the preceding claims.
    [16" id="c-fr-0016]
    16. Aircraft turbomachine, comprising the profiled structure according to claim 13 and in which:
    the turbomachine is with a front fan (14) and has a general axis (X) around which the front fan can rotate,
    the front fan (14) is adapted to rotate in a predetermined direction around said general axis (X), so that the air flow downstream of the fan is generally oriented obliquely relative to said general axis (X), and
    - The teeth (30) are, circumferentially around said general axis (X), individually inclined towards the generally oblique orientation of the air flow (angle a) downstream of the blower, to face it generally.
    [17" id="c-fr-0017]
    17. A turbomachine for aircraft, comprising the profiled structure according to claim 6, or claims 6 and 13, and in which:
    the turbomachine has a front fan (14) and has a general axis (X) around which the front fan can rotate, and
    - the teeth (30) are, circumferentially around said general axis (X), individually inclined (angle β, β ’):
    - in the direction of the average camber of said first blades (24, IGV), or
    - in the direction of the camber at the leading edge (25) of said first blades (24, IGV).
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    同族专利:
    公开号 | 公开日
    EP3752729A1|2020-12-23|
    CN111727313A|2020-09-29|
    FR3078099B1|2020-09-11|
    US20210003074A1|2021-01-07|
    CA3089694A1|2019-08-22|
    WO2019158876A1|2019-08-22|
    引用文献:
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    WO2013092368A1|2011-12-19|2013-06-27|Rolls-Royce Plc|Blade for a rotating machine|
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    WO2015193654A1|2014-06-16|2015-12-23|Brunel University|Noise reduction to the trailing edge of fluid dynamic bodies|
    WO2016184619A1|2015-05-21|2016-11-24|Siemens Aktiengesellschaft|Rotor blade with serrations|
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    法律状态:
    2019-01-23| PLFP| Fee payment|Year of fee payment: 2 |
    2019-08-23| PLSC| Publication of the preliminary search report|Effective date: 20190823 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 3 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 4 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1851360A|FR3078099B1|2018-02-16|2018-02-16|STRUCTURE WITH A PROFILE IN SERRATIONS WITH TREATED SURFACES|
    FR1851360|2018-02-16|FR1851360A| FR3078099B1|2018-02-16|2018-02-16|STRUCTURE WITH A PROFILE IN SERRATIONS WITH TREATED SURFACES|
    US16/969,738| US20210003074A1|2018-02-16|2019-02-15|Profiled structure and associated turbomachine|
    CA3089694A| CA3089694A1|2018-02-16|2019-02-15|Profiled structure and associated turbomachine|
    EP19712622.0A| EP3752729A1|2018-02-16|2019-02-15|Profiled structure and associated turbomachine|
    CN201980013716.6A| CN111727313A|2018-02-16|2019-02-15|Surface-treated zigzag contour line structure|
    PCT/FR2019/050350| WO2019158876A1|2018-02-16|2019-02-15|Profiled structure and associated turbomachine|
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