• 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 stator (1) intended to be placed radially in a flow passing through one or more rotors (2) sharing the same axis of rotation (LL), having a leading edge (11) and an edge of leakage device (12), said leading edge (11) and trailing edge (12) being connected by a lower face (10) and an extrados face (9), characterized in that at least one of the faces (9) 10) of said stator has radial corrugations extending axially from the leading edge (11) to the trailing edge (12), said radial undulations having at least two bumps (B) in the same azimuth direction of which amplitude is at least one centimeter over at least a portion of the axial length of the stator (1). It also relates to the propulsion unit formed by the rotor and the stator and a turbomachine comprising this assembly.
    公开号:FR3023329A1
    申请号:FR1456411
    申请日:2014-07-03
    公开日:2016-01-08
    发明作者:Pascal Romano；Norman Bruno Andre Jodet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to the field of thrusters comprising a stator in fluid interaction with a rotor. It relates more particularly to the design of a stator for reducing the tonal noise produced by the assembly without involving active devices. State of the art: In particular, a turbofan engine for transport aircraft propulsion comprises a generally upstream fan delivering an annular air flow with a central annular portion supplying the primary flow motor and an outer annular portion, secondary , which is ejected into the atmosphere while providing a significant fraction of the thrust. Currently, on the motors, a ring of fixed vanes, also called blades, is disposed in the secondary air stream, downstream of the rotor, to straighten the flow and increase the thrust provided. These fins are usually referred to as OGV, which stands for Outlet Guide Vane. The passage of air over the engine structures causes fluctuating pressure disturbances that propagate and form noise sources that are troublesome for the environment. In particular, the noise that propagates in the air intake duct of a turbojet engine is almost entirely due to the blower. In addition, the main source of tonal noise is usually the interaction between the fan and stator elements, while the broadband noise is due in particular to turbulence. The source of tonal noise is mainly the result of the periodic impact of the wakes of the fan rotor blades on the fins. It has been proposed, especially in patent EP1950383, to integrate Helmotz resonator cavities in the stator to dampen these acoustic excitations. However, this solution requires having a certain thickness in the stator. It is not easily applicable, even using the solution recommended in patent EP1950383, when seeking to have thin fins, to minimize flow disturbances outside the rectifier effect.
    [0002] The noise is amplified if all parts of the fin are impacted at the same time and the local contributions add up. With respect to this, it is known (see for example Journal of Engineering Science and Technology Review 6 (1) (2013) 59-61) to give shapes inclined axially and / or circumferentially to the stator to promote the phase shift between localized noise sources on the extension of the stator vane, compared to the wake created by the rotor blades. However, these shapes are not necessarily optimal from the point of view of the energy efficiency of the engine. In addition, in the case where the stator would be, for example, a pylon or a crank arm, these forms pose problems to obtain a structural strength to withstand the forces experienced by the stator. A solution studied, in the article of the AIAA Journal Vol. 51, No.11, November 2013 entitled "Experimental and Numerical Investigation of Turbulence-Airfoil Noise Reduction Using Wavy Edges (Experimental and Numerical Study of Noise Reduction Due to Turbulence on a Profile Through Wavy Ends)", was to design a leading edge with sinusoidal indentations to phase out the excitations on the different parts of the leading edge. However, the leading edge is not always the only seat of a large production of noise, in particular when the profile of the stator vane is strongly three-dimensional. The aim of the invention is to effectively reduce the tonal noise due to the interaction of the stator with the rotor for a wide range of stator shapes while avoiding the limitations observed on the solutions that have just been mentioned. Disclosure of the invention: For this purpose, the invention relates to a stator intended to be placed radially in a flow through one or more rotors sharing the same axis of rotation, having a leading edge and a trailing edge, said leading edge and trailing edge being connected by an intrados and an extrados face, characterized in that at least one of the faces of said stator has radial corrugations extending axially from the leading edge to the trailing edge said radial undulations having at least two bumps in the same azimuth direction whose amplitude is at least one centimeter over at least a portion of the axial length of the stator.
    [0003] The radial and axial directions are indicated on the stator with reference to the position that it must occupy relative to the axis of rotation of the rotors. The same is true of the definition of azimuth. On the other hand, the rotors are designed to rotate in one direction and to induce medium flow in a given axial direction. The average flow is obtained by averaging the values over at least one rotational period of the rotors and eliminating the fluctuations. It corresponds in the disk fins to a flow oriented axially downstream and rotated in the direction of rotation of the rotors. The terms extrados and intrados faces, as well as leading edge and trailing edge on the stator are therefore defined according to this direction of rotation and this axial direction of the mean flow. The radial undulation of a face of the stator means that the cutting line of this face by a plane transverse to the axis of the rotor undulates in this plane. The cutting line thus has crests oriented successively in one direction and in the opposite direction, with respect to a mean radial direction. A bump is thus defined as the part of this line which joins two successive peaks oriented in the same direction. The hump therefore passes through an intermediate ridge, oriented in the opposite direction, which is called here its summit. For the remainder of the document, the orientation of the hump corresponds to the orientation of its summit and the amplitude of the hump is the distance from the summit to the right joining the two ridges that surround it. The invention allows, in the case where the stator is downstream of the rotor, to phase out the radiation noise sources due to the scroll of the stator surface in the flow induced by the rotor or rotors. Indeed, by shifting with the radial corrugations the azimuth position of the surface of at least one of the faces, a temporal phase shift is introduced on the moment when the wake of the rotor blades meets the stator.
    [0004] Thus, noise sources located near the surface of the stator from this interaction mechanism not emitting exactly at the same time the passage of the wake, it avoids an amplification effect on far-field propagated noise in the harmonics related to the operation of the rotor. A first advantage of the invention lies in the fact that the corrugations make it possible to introduce phase shifts with respect to the overall rotational movement of the flow passing through the stator even if stresses, for example structural or aerodynamic, do not permit use a general shape of the stator having inclination in the axial and / or circumferential direction. Such a stator may be, in addition to an OGV fin behind a fan, a pylon ensuring the maintenance of a housing or motor, a stator blade in a compressor or a turbine. A second advantage of the invention lies in the fact that, in the case where the stator has a three-dimensional profile, the seat of the mechanisms for producing noise by the interaction of pressure fluctuations moving in rotation in front of the profile is no longer located at the leading edge only. The extension of the surface corrugations over the entire length of the stator cord makes it possible to treat the localized sources of noise on the whole of this surface. According to the invention again, the amplitude of the bumps is at least one centimeter to have a significant effect on the attenuation of the tonal noise. This amplitude remains, however, preferably less than ten centimeters. The radial undulations of a face also correspond to oscillations of the azimuth of the points of the radial profile between the peaks of bumps and the ridges which border them. These azimuth oscillations will advantageously have at least an amplitude of two degrees. According to the invention, the radial corrugations have at least two bumps. For different configurations, the number of bumps can be adapted to maximize the geometric phase shift of the acoustic sources taking into account the phase distribution on the surface of the stator. This number can be generally four and reach ten.
    [0005] The solution of the invention also has the advantage, particularly when the stator is upstream of the rotor, to create an overall disturbance of the wake behind the stator, with spatial oscillations. In this configuration, it is the sources of noise on the rotor blades that are out of phase by the spatial oscillations of the wake of the stator, when it is traversed by the blades of the rotor. Thus, an attenuation effect of the tonal noise in the operating harmonics of the rotor is also obtained by a similar effect in the case where the stator is downstream. The invention also has the advantage that, when radial corrugations are applied on a single face in certain configurations, a geometric phase shift is induced between the noise sources on each face, characterized by a variation in thickness which varies with the position radial. This can reduce the resulting noise levels. Advantageously, the radial corrugations have a substantially constant wavelength following the radial extension of the stator. In other words, these corrugations have a regular distribution between the inner radial edge and the outer radial edge of the stator. Preferably, the amplitude of the bumps of the radial corrugations is maintained greater than one centimeter from the leading edge to the trailing edge.
    [0006] According to one of the features, the intrados face and the extrados face may have radial corrugations. In this case, the corrugations of the two faces can be radially in phase. In particular, when the corrugations extend over the entire length of the stator, the latter provision implies that the leading edge and the trailing edge are themselves corrugated. This arrangement makes it possible to maintain the thickness of the stator on the wingspan and to offer a gain in aerodynamic performance.
    [0007] According to another characteristic of the invention, the stator may comprise a core arranged to ensure the mechanical strength of said stator and a skin forming the radial corrugations on said at least one of the faces. The core of the stator is a piece of structure extending radially on the inside which makes it possible to recover the forces that the stator has to bear. This arrangement separates the mechanical and aerodynamic functions by offering flexibility to design the shape of the stator. The invention also relates to an assembly comprising one or more rotors 10 sharing the same axis of rotation and at least one stator as described above, arranged to be in the flow passing through said rotors in operation, downstream or upstream of those this. Advantageously, the radial corrugations of the face of the stator propagate axially following average current lines in said flow. In the propulsive assembly described, the average flow along the intrados and extrados faces of the stator from the leading edge to the trailing edge. The term axial propagation of the radial corrugations along these current lines means in particular that the position of the bumps and hollows of the radial corrugations as a function of the abscissa on the axis of rotation follows current lines. Preferably, the scrolling of the stator in said flow creating on said corrugated face pressure fluctuations having oscillations of the time phase as a function of the radial position, the radial corrugations of said face have maxima and / or minima in azimuth of the radial profile of said face near the zones of zero mean phase shift for the pressure on the undulating face. Thus, the zones that radiate in phase are distributed geometrically along surface portions of the stator on which the azimuth shift variation around the axis of rotation has a constant sign. This azimuth variation ensures a phase shift of the noise emitted by these sources on the corresponding surface portion.
    [0008] The invention relates in particular to a turbomachine comprising an assembly as described above, a ring of fixed guide vanes form said stators. BRIEF DESCRIPTION OF THE FIGURES: The present invention will be better understood and other details, features and advantages of the present invention will emerge more clearly on reading the description which follows, with reference to the appended drawings, in which: FIG. axial, a schematic diagram of the arrangement of a rotor and a stator according to the invention in the case of a turbomachine with a double flow. Figure 2 shows in perspective a stator according to the invention behind a rotor. Figure 3 shows the phase distribution of the pressure fluctuations in the flow on a face of a stator according to the invention. Figures 4a and 4b show in cross section the undulations of two embodiments of a stator according to the invention.
    [0009] Figure 5 shows a three-dimensional view of a stator according to the invention having an increase in thickness towards the middle of the rope. DESCRIPTION OF AN EMBODIMENT With reference to FIG. 1, the invention relates in particular to stators formed by vanes 1 OGV, or vanes placed in the secondary flow driven by the blades 2 of a turbomachine fan, rotating around the axis LL of rotation of a motor 3. The fins 1 pass radially through the vein of the secondary flow, from the outer casing 4 of the engine 3 to the nacelle 5. As is illustrated in FIG. each fin 1 is periodically impacted by the wake 6 of each blade 2 of the fan.
    [0010] With reference to FIG. 2, the fin 1 can be defined by the evolution of its profile P (R) in surfaces of revolution between the surface of the casing 4 and the surface of the nacelle 5. With reference to FIG. , the profile P (R) evolves for example regularly inside the vein as a function of the radius R, said radius R being measured between the radial position in the vein and the axis LL of rotation. The profiles P (R) at the junction of the fin 1 respectively with the casing 4 and the nacelle 5, form the inner radial edges 7 and outer 8 of the fin 1.
    [0011] In the example of Figure 2, such a fin 1 is placed downstream of the blades 2 of the fan, which operates, for example, having a counterclockwise direction of rotation w. In this example, it is therefore possible to define on the fin with respect to the flow having passed through the fan 2, an extrados face 9 and a lower surface 10, as well as a leading edge 11 and a corresponding trailing edge 12. at the junction lines of the two faces 9, 10, upstream and downstream in the flow. With reference to FIG. 2, in a first variant, the stacking of these profiles P (R) follows a curve S, represented here on the trailing edge 12, which waves around a radial line XX. Still, in the example of FIG. 2, the shape of the profiles P (R) is substantially constant as a function of the radius R; furthermore, the extrados 9 and the intrados 10 faces are substantially parallel, separated by a small distance from the length of rope in the axial direction, outside the zones of connection to the leading edge 11 and to the trailing edge 12. The corrugations thus propagate on the extrados face 9 and the intrados face 10 of the fin 1 with a substantially constant amplitude. If the previously defined bump term is restricted to a local deformation of the surface corresponding to a corrugation of its radial profile in a transverse cutting plane in the direction of rotation w of the blower, the vertex (or ridge) B a hump is a peak corresponding to the extreme position of a corrugation in the direction of rotation w of the blower. The crests C of hollows, which form the ends of the bumps, correspond to the extreme position of a corrugation in the other direction. The example shown in Figure 2 has three bumps and three depressions. Other variants are possible. The corrugations on each of the faces 9, 10 may include up to at least ten bumps. Conversely, the number of bumps will be at least two. This corresponds, for regularly distributed corrugations, to the fact that the radial extension of the fin 1 is at least equal to one and a half times the wavelength of the radial corrugations.
    [0012] The maximum value of the amplitude of the bumps, as defined at the beginning of the presentation of the invention, defines that of the corrugations in a transverse section plane. Typically, for turbine engines installed on aircraft, fin 1 may be made using corrugation amplitudes between a hump top B and a peak C of hollow that can be at least up to 10 cm.
    [0013] With reference to FIG. 4a, this amplitude corresponds approximately to the sum of the distance d1 from the vertex B of a bump on the curve S to the radial line XX and the distance d2 from a peak C of adjacent valleys to the curve S at the radial line XX. To obtain the desired effects in terms of acoustic phase shift, this amplitude will not be less than 1cm. These figures can be transposed in terms of the variation of the azimuth 0 between the vertex B of a hump and the peak C of a hollow. With regard to the typical dimensions of a turbojet engine with a fan, this corresponds to the fact that the variation between the azimuth 01 of the vertex B of a hump and the azimuth 02 of the crest C of an adjacent hollow is at least about two degrees. A third important parameter in the definition of the corrugations corresponds to the way they propagate axially along a face 9, 10 of the fin 1, that is to say the way they evolve when changing. the transverse cutting plane of the leading edge 11 at the trailing edge 12.
    [0014] In the example shown in Figure 2, the cutting profiles of the fin 1 along a radius being substantially constant, the corrugations follow lines parallel to the axis of rotation LL. They thus approximately follow the flow lines of the average flow around the fin 1, so as to minimize the pressure drops caused by the presence of the stator in the flow. For various reasons, this average flow induced by the rotor 2 in operation may have on the faces 9, 10 of the fin 1 of currents lines not aligned with the axis of rotation. Preferably, in an alternative embodiment, the law of evolution of the profiles P (R) of the fin will be adapted as a function of the radius R in the vein so that the corrugations on at least one of the faces 9 , Follow the average flow lines.
    [0015] If the average flow lines vary according to the operating speed of the engine, this variant will be adapted to the operating regime for which the maximum acoustic efficiency is sought. By way of example, FIG. 3 illustrates how the distribution of the corrugations by positioning the bumps B and the recesses C can be optimized for a given configuration of rotor and stator, and at a given operating speed. FIG. 3 shows a typical observed shape of isophase lines cP of pressure fluctuations on the extrados face 9 'of a fin 1' set in place of the fin 1 according to the invention and having a defined planar face 9 ' by a leading edge 11 'and a trailing edge 12' having the same axial position as those of the vane 1. If the reference is taken to the phase of the pressure fluctuations on the downstream part of the face 9 ' of the fin 1 ', these isophase curves c1) show that, going from the internal radial edge 7' to the outer radial edge 8 'in the upstream part, we pass through regions where the pressure is successively in phase advance and then in phase delay.
    [0016] This result illustrates the fact that local fluctuations in the flow, in particular near the wake of a blade 2 of the fan, are superimposed on the periodic overall movement due to the rotation of the blades 2 of the rotor.
    [0017] The corrugations make it possible to take these phenomena into account in order to attenuate them. The horizontal arrows, in front of the leading edge 11 'in FIG. 3, indicate the way in which the peaks B of the bumps are positioned in a variant which therefore has, here, nine bumps. In this variant, the peaks B of the bumps and the peaks C of the valleys of the fin 1, made with nine bumps as described above, are located between the isophase lines cP with the pressure fluctuations on the downstream part of the face 9 '. Thus, the zones that radiate in phase on the undulating surface extrados 9 of the fin 1 are distributed locally on areas where the azimuth of the points of the face varies regularly. Such a structure allows a fluctuation of the acoustic waves interacting with the surface of the fin 1 by producing a phase shift of the sources relative to the wake of the blade 2 of the rotor. The invention has been presented in a simple case for an OGV fin 1 extending substantially radially in the flow of flow. However, it also concerns fins having more complex three-dimensional shapes, or, for example, other elements indicated in FIG. 1. It may be for a turbomachine: a stator 13 placed in the primary flow after the rotors 14 of a compressor; a stator 15 placed in the primary flow after the rotors 16 of a turbine; a pylon 17 of structural support placed in the secondary flow.
    [0018] In an embodiment adapted for example to the compressor stator, turbine or aerodynamic optimization of the OGV fins, the radial stacking curve S of the profiles can deviate significantly from a radial line. First, it may not be perpendicular to the rotor axis in a meridian plane. Second it can be inclined in the circumferential direction.
    [0019] FIG. 4b illustrates an embodiment of the invention of a stator according to a stacking curve S 'which waves around a mean line X' which is inclined in the circumferential direction with respect to the radial line XX. This variant presents here two bumps. In this case, the amplitude between the vertex B of a hump and the peak C of an adjacent hollow must be measured taking into account the correction to be made around the mean line X '. For this variant, the criterion of amplitude of the bumps is always applied, which corresponds approximately to the fact that the sum of the two deviations of 1, 2 in distance with respect to the mean line X 'must be greater than 1 cm. If we consider the difference in azimuth, neglecting the evolutions of X ', this always leads to applying the criterion indicating that an angular difference 0'1-0'2 of at least 2 degrees between the vertex B d a hump and the crest C of an adjacent hollow must be respected. Other embodiments may also be obtained by varying the thickness of the stator. In the example shown in Figure 2, the thickness can be considered negligible. The faces 9, 10 of the fin 1 are in this case two slightly offset surfaces in the circumferential direction, which follow the same undulations with respect to a flat surface. In an alternative embodiment, with reference to FIG. 5, the extrados 9 and intrados 10 faces may correspond to a stack of P (R) profiles whose thickness varies according to the rope. These thickness variations may be justified by aerodynamic considerations and / or structural considerations. In an alternative embodiment, they make it possible not to undulate the extrados and intrados surfaces in the same way. For example, one surface may be undulated and the other not. In an embodiment illustrated in FIG. 5, the two faces 9, 10 of the stator are corrugated. On the other hand, this stator is made with an internal structure 18 forming a core providing structural strength and a "skin" 19, which surrounds it and which forms the extrados 9 and intrados 10 faces of the stator interacting with the flow.
    [0020] As is illustrated in FIG. 5, the thickness of the profile P (R) makes it possible to give a substantially rectilinear shape to the core 18, little or not at all influenced by the undulations of the surfaces 9, 10. This allows to achieve structural performance more easily, in particular if the stator is a tower 17 to maintain elements of the engine 3.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Stator (1) intended to be placed radially in a flow passing through one or more rotors (2) sharing the same axis of rotation (LL), said stator (1) having a leading edge (11) and an edge of leakage device (12), said leading edge (11) and trailing edge (12) being connected by a lower face (10) and an extrados face (9), characterized in that at least one of the faces (9) 10) of said stator has radial corrugations extending axially from the leading edge (11) to the trailing edge (12), said radial undulations having at least two bumps (B) in the same azimuth direction of which amplitude is at least one centimeter over at least a portion of the axial length of the stator (1).
    [0002]
    2. Stator according to the preceding claim, wherein the radial corrugations have a substantially constant wavelength following the radial extension of the stator.
    [0003]
    3. Stator according to one of the preceding claims, wherein the amplitude of the bumps (B) of the radial corrugations is maintained greater than one centimeter from the leading edge (11) to the trailing edge (12).
    [0004]
    4. Stator according to one of the preceding claims, wherein the intrados face (10) and the extrados face (9) have radial corrugations.
    [0005]
    5. Stator according to the preceding claim, wherein the corrugations of the two faces (9, 10) are radially in phase.
    [0006]
    6. Stator according to one of the preceding claims, comprising a core (18) arranged to ensure the mechanical strength of said stator and a skin (19) forming the radial corrugations on said at least one face (9, 10).
    [0007]
    7. An assembly comprising one or more rotors (2) sharing the same axis of rotation (LL) and at least one stator (1) according to one of the preceding claims, arranged to be in the flow passing through said rotors (2) in operation downstream or upstream of these.
    [0008]
    8. An assembly according to the preceding claim, wherein the radial corrugations propagate axially following average current lines in said flow.
    [0009]
    9. An assembly according to one of claims 7 or 8, wherein, the movement of the stator (1) in said flow creating on said corrugated face pressure fluctuations having oscillations of the time phase as a function of the radial position (R ), the radial corrugations of said face (9, 10) have azimuth maxima and / or minima in the vicinity of the zones of zero mean phase shift for the pressure on the undulating face (9,
    [0010]
    10). 10. A turbomachine comprising an assembly according to one of claims 7 to 9, wherein a ring of guide vanes (1) forms said stators.
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    同族专利:
    公开号 | 公开日
    US20160003095A1|2016-01-07|
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    法律状态:
    2015-08-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-08| PLSC| Search report ready|Effective date: 20160108 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2016-08-04| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-02| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1456411|2014-07-03|
    FR1456411A|FR3023329B1|2014-07-03|2014-07-03|STATOR ONDULE TO REDUCE NOISE CREATED BY INTERACTION WITH A ROTOR|FR1456411A| FR3023329B1|2014-07-03|2014-07-03|STATOR ONDULE TO REDUCE NOISE CREATED BY INTERACTION WITH A ROTOR|
    US14/790,964| US10358938B2|2014-07-03|2015-07-02|Undulating stator for reducing the noise produced by interaction with a rotor|
    GB1511726.0A| GB2529757B|2014-07-03|2015-07-03|Undulating stator for reducing the noise produced by interaction with a rotor|
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