• 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 blade (100) comprising: - a blade root (110), - a blade head (115), - a leading edge (120) extending between the foot (110) ) and the head (115), the leading edge having a serration profile having a succession of teeth (122) and recesses (124) each having an amplitude and a thickness, characterized in that a series (300) at least three teeth (122) and three recesses (124) consecutive from the blade root (110) and / or the blade head (115) has an amplitude and / or increasing thickness.
    公开号:FR3073016A1
    申请号:FR1760212
    申请日:2017-10-30
    公开日:2019-05-03
    发明作者:Claire Marie FIGEUREU；Eric Pierre Georges LEMARECHAL；Benjamin BULOT；Mathieu Simon Paul GRUBER；Raphael BARRIER；Cyril POLACSEK
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Modulation of tightening at the blade tip
    GENERAL TECHNICAL AREA
    The invention relates to the field of aero-acoustic management of a fixed blade in a turbomachine for an aircraft or in a turbomachine test bench for an aircraft.
    This type of fixed vane is found for example on OGV (outlet guide vane), or rectifiers, arranged downstream of a rotating body to straighten the air flow. We will speak of stator vane to designate a fixed vane.
    An example will be given for a double flow turbomachine with a blower and a rectifier arranged in a secondary stream.
    The interaction between the flow set in rotation by the blower and the rectifier in the secondary vein is the source of a predominant source of noise over the total noise generated by the engine, or even by the aircraft according to the speeds of operations.
    STATE OF THE ART
    Several approaches are envisaged to control and / or reduce the noise of aerodynamic origin, either by modification of the incident aerodynamic field (aerodynamic excitation), or by modification of the geometry of the stators (the aero-acoustic response).
    In the second case, it has been proposed to modify the geometry of the leading edge of the stator vanes in the form of a wavy leading edge commonly called "wavy leading edge", "serrated ieading edge" or "leading edge serrations" .
    The principle of reducing noise emissions generated by the OGV grid resides in the fact of spatially phase shifting the noise sources distributed along the leading edge by means of ripple, identical or not. For the principle to apply, the size (depth, width, thickness) of the undulations must be adapted to the content of the incident aerodynamic field (thickness and deficit of the average wakes, size of the vortices for turbulence) which varies according to the engine speed .
    As presented in the references listed below, the function of the geometric variations according to the chord is given by the following equation:
    c (r) = c 0 + h. sm (2nr / P)
    Where co is the reference chord, h the amplitude and the wavelength of the ripples and r the radius.
    The angle θ expressed below is a key parameter in noise reduction. Its value is determined by the following formula, illustrated in Figure 1:
    Θ = atan (4h / A)
    The value of λ is chosen from the wavelength of the turbulence of the fluid arriving at the leading edge of the blade.
    FIG. 2 illustrates the result of the application of these formulas on blades 100, where the teeth 112 and the hollows 114 of the leading edge 108 and the periodic undulations are observed. Figure 3 shows schematically these teeth and hollows.
    However, the presence of the teeth 112 at the leading edge 108 greatly reduces the mechanical balance of the LMOs, with high concentrations of stresses in the tooth hollows.
    Indeed under aerodynamic force the blade flexes tangentially, which induces a transverse shearing effect from one tooth to another. Thus the longer the teeth, the smaller the radius of the tooth recesses, and the greater the stress in the tooth recesses.
    However, this observation is opposite to the expected acoustic gain since the latter is maximized for fine and long teeth.
    There is therefore a need for solutions making it possible to protect the blades having tight profiles.
    PRESENTATION OF THE INVENTION
    For this, the invention proposes a stator blade comprising:
    - a foot of dawn,
    - a dawn head,
    a leading edge extending between the foot and the head, the leading edge having a tight profile having a succession of teeth and hollows each having an amplitude and a thickness, characterized in that a series of 'at least three teeth and three consecutive hollows from the blade root and / or the blade head have an increasing amplitude and / or thickness.
    The invention may include the following characteristics, taken alone or in combination:
    - the series includes at least four teeth and four hollows,
    - the series extends between 20 and 50% of the length of the blade,
    the tightening profile is of the sinusoidal type and in which, at the level of the series, the amplitude and / or the thickness of the teeth and of the depressions is combined with a linear, parabolic, sinusoidal or exponential function,
    - the tightening profile is expressed in the following form:
    c (r) = c 0 + h. sm (2nr / P)
    Where co is the reference chord, h the amplitude and the wavelength of the ripples and r the radius
    - at the level of the series, the amplitude and / or the thickness of the teeth and of the recesses is combined with a linear function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / À). K. r where K is a constant, or a parabolic function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / À). L. r 2 where L is a constant, or a sinusoidal function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / À) .sin (Mn / 2. r) where M is a constant, or an exponential function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / X). exp (N. r) where N is a constant.
    - the blade is made of composite material,
    - the amplitude of the first hollow or the first tooth from the head or the foot of the blade is not zero,
    The invention also relates to a rectifier ring comprising a plurality of blades as described above, the blades being distributed circumferentially around a hub.
    The invention also relates to a turbomachine or a test bench comprising a blade or a crown as described above.
    It is a turbomachine or a test bench, for example of the partial turbomachine type, this assembly being for example a single-flow rectifier of the partial turbomachine by constituting a stream which would correspond to a secondary stream considering the case of a complete turbomachine.
    PRESENTATION OF THE FIGURES
    Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and which should be read with reference to the appended drawings, in which:
    FIG. 1 represents a diagram illustrating the quantities defining a tightening profile,
    - Figures 2 and 3 illustrate a part of the stator blade with a tightening profile and its enlargement,
    FIG. 4 illustrates a portion of a stator blade with a tightening profile in accordance with an embodiment of the invention,
    - Figure 5 illustrates a sinusoid,
    - Figures 6 to 9 illustrate sinusoids combined with different functions in the context of the invention.
    DETAILED DESCRIPTION
    We place ourselves within the framework of a portion of a turbomachine, typically a stream which could be equivalent to a secondary stream of a turbofan with double flow with rectifier (OGV) arranged at the outlet of the fan. It can therefore be a test bench frame, for example for single-flow rectifiers or any type of test bench in which a fixed vane is used. Such a test bench is for example a partial engine making it possible for example to validate data on phenomena representative of those usually occurring in the secondary stream of a complete engine.
    FIG. 4 illustrates a blade portion 100 comprising a blade root 110 at one end, which is typically a radially internal end of the blade 100. The blade root 110 attaches to a hub 200, of revolution about a longitudinal axis, which corresponds to a main axis of rotation of the turbomachine portion. The hub 200 is generally part of the primary body of a double-flow turbomachine. The blade 100 extends in a radial direction Y relative to the hub 200 (each blade therefore has its own radial direction Y).
    At another end, radially external, the blade 100 is attached to a casing 250 by a blade head 115.
    To form the vein V, an interior platform 220 can be provided radially beyond the hub 200, which has no aerodynamic function.
    The blade 100 has a profiled shape to straighten the flow, with in particular a lower surface and an upper surface. The foot 110 of the blade 100 may have a shape in the extension of the lower surface and the upper surface.
    The blade 100 includes a leading edge 120 in tightness, that is to say that it has undulations, in the form of an alternation of teeth 122 and hollows 124, for example according to a sinusoidal pattern as described in the introduction.
    The blade 100 can be made of metal or a composite material (resin matrix with reinforcements, typically carbon).
    In order to protect the tightening profile, an objective of the invention is to mechanically relieve the teeth and hollows where the stresses are greatest.
    For this, as illustrated in FIG. 4, a series 300 of at least three successive teeth 122 and three successive hollows 124 is defined, starting from the blade root 110 and / or the blade head 115. In others terms, this 300 series includes the tightenings closest to the edge of the vein V.
    In this series, the amplitude of the teeth 122 and the hollows 124 decreases as it approaches the blade root 110 or the blade head 115. Alternatively or additionally, this is the thickness of the edge attack 120 which increases while approaching the blade root 110 or the blade head 115.
    This series 300 can be found at the level of the blade head 115 and / or the blade root 110.
    Amplitude is defined as the distance between the vertex (of the tooth or the hollow) relative to the straight profile. It therefore corresponds to the "h sin (2rcr // l)" of the formula given in the introduction.
    The thickness is defined at the level of the straight profile (that is to say for a zero amplitude of tooth or hollow). Indeed, the thickness of the blade 100 is variable between the upstream and the downstream of the blade: it is for example smaller at the tops of the teeth 122 than at the tops of the hollows 124.
    Such a blade 100 allows the load to be distributed by smoothing the stress over several tightenings.
    In the rest of the request, we will only speak of "decrease in amplitude", which can be replaced by "increase in thickness".
    To ensure this continuity, the reduction in amplitude can be governed by formulas.
    We recall that we place ourselves in the context of a blade 100 whose tightening profile is defined as follows:
    c (r) = c 0 + h. sm (2nr / A ~)
    Where co is the reference chord, h the amplitude and the wavelength of the ripples and r the radius. By the radius is meant the positioning along the leading edge 120 (which extends radially from the longitudinal axis, hence the term radius). We suppose that r = 0 means that we are against the edge of the vein V, either at the level of the blade head 115 or at the blade root 110.
    Conceptually, the equation is simplified by considering that A is an arbitrarily fixed constant.
    This regular sinusoidal profile Ps is illustrated in FIG. 5.
    Several embodiments make it possible to modulate the tightenings in the 300 series.
    In an embodiment illustrated in FIG. 6, the reduction is done by a linear function. The P1 profile on the 300 series is then expressed in the following form:
    c (r) = c 0 + h. sm (2nr / À). K. r where K is a constant chosen as a function of the desired rate of decrease.
    In an embodiment illustrated in FIG. 7, the reduction is done by a parabolic function. The Pp profile is then expressed in the following form:
    c (r) = c 0 + h. sm (2nr / À). L. r 2 where L is a constant chosen as a function of the desired rate of decrease.
    In an embodiment illustrated in FIG. 8, the reduction is done by a sinusoidal function. The Pc profile is then expressed in the following form:
    c (r) = c 0 + h. sin (2rcr // l). sin (Mn / 2. r) where M is a constant chosen as a function of the desired rate of decrease.
    In an embodiment illustrated in FIG. 9, the reduction is done by an exponential function. The Pe profile is then expressed in the following form:
    c (r) = c 0 + h. sm (2nr / X). exp (/ V. r) where N is a constant chosen as a function of the desired rate of decrease.
    Any strictly decreasing continuous function in the direction of the foot 110 or the blade head 115 is suitable in practice.
    Preferably, it is avoided that the first tooth 122 or the first hollow 124 has a zero amplitude, because this only transfers the load to the next tooth or hollow. For that, it is enough to integrate a slight offset, of type r-rO in the equations given above.
    In one embodiment, the 300 series comprises four, even five hollows and five successive teeth.
    In one embodiment, the series 300 extends between 20 and 50% of the length of the blade 100 in the vein.
    It is possible to combine the amplitude and thickness variations, in order to create a three-dimensionally variable blade profile 100.
    In addition to a turbomachine, this blade 100 can be mounted as part of a test bench or a test turbomachine.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    claims
    1. Dawn (100) of stator comprising:
    - a blade root (110),
    - a blade head (115),
    - A leading edge (120) extending between the foot (110) and the head (115), the leading edge having a tight profile having a succession of teeth (122) and hollows (124) having each an amplitude and a thickness, characterized in that a series (300) of at least three teeth (122) and three hollow (124) consecutive from the blade root (110) and / or the head d 'vane (115) have an amplitude and / or increasing thickness.
    [2" id="c-fr-0002]
    2. Dawn (100) according to claim 1, in which the series (300) comprises at least four teeth and four hollows or extends between 20 and 50% of the length of the blade (100).
    [3" id="c-fr-0003]
    3. Dawn (100) according to any one of claims 1 to 2, in which the tightening profile is of sinusoidal type and in which, at the level of the series (300), the amplitude and / or the thickness of the teeth and hollows is combined with a linear, parabolic, sinusoidal or exponential function.
    [4" id="c-fr-0004]
    4. Dawn (100) according to any one of claims 1 to 3, in which the tightening profile is expressed in the following form:
    c (r) = c 0 + h. sm (2nr / U)
    Where co is the reference chord, h the amplitude and the wavelength of the ripples and r the radius and in which, at the level of the series (300), the amplitude and / or the thickness of the teeth and hollows is combined with a linear function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sin (2rcr / A). K. r where K is a constant, or a parabolic function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / X). L. r 2 where L is a constant, or a sinusoidal function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / X) .sin (Mn / 2. r) where M is a constant, or an exponential function so that the profile is expressed at the level of said series:
    c (r) = c 0 + h. sm (2nr / X). exp (/ V. r) where N is a constant.
    [5" id="c-fr-0005]
    5. Dawn according to any one of claims 1 to 4, wherein the blade (100) is made of composite material.
    [6" id="c-fr-0006]
    6. Dawn according to any one of claims 1 to 5, in which the amplitude of the first hollow (124) or the first tooth (122) from the head (110) or the blade root (115) is not zero.
    [7" id="c-fr-0007]
    7. Rectifier crown comprising a plurality of blades according to any one of claims 1 to 6, the blades (100) being distributed circumferentially around a hub (200).
    [8" id="c-fr-0008]
    8. Turbomachine or test bench comprising a blade according to any one of claims 1 to 6 or a crown according to claim 7.
    1/4
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    同族专利:
    公开号 | 公开日
    US20190170003A1|2019-06-06|
    EP3477057A1|2019-05-01|
    FR3073016B1|2019-10-18|
    EP3477057B1|2022-02-09|
    US10941667B2|2021-03-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1607573A1|2004-06-02|2005-12-21|Rolls-Royce Deutschland Ltd & Co KG|Compressor blade with reduced aerodynamic vibration induction|
    US20130164488A1|2011-12-22|2013-06-27|General Electric Company|Airfoils for wake desensitization and method for fabricating same|
    FR3023329A1|2014-07-03|2016-01-08|Snecma|STATOR ONDULE TO REDUCE NOISE CREATED BY INTERACTION WITH A ROTOR|
    EP3205826A1|2016-02-10|2017-08-16|General Electric Company|Airfoil assembly with leading edge element|FR3103231A1|2019-11-19|2021-05-21|Safran Aircraft Engines|Turbomachine with wavy blades|US2749473A|1953-11-20|1956-06-05|Rca Corp|Beam convergence system for tri-color kinescope|
    US3365126A|1965-09-01|1968-01-23|Gen Electric|Compressor blade|
    US5455103A|1994-01-24|1995-10-03|Monsanto Company|Rough-surfaced interlayer|
    US10443399B2|2016-07-22|2019-10-15|General Electric Company|Turbine vane with coupon having corrugated surface|
    US11156099B2|2017-03-28|2021-10-26|General Electric Company|Turbine engine airfoil with a modified leading edge|
    FR3087483B1|2018-10-18|2022-01-28|Safran Aircraft Engines|PROFILE STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT|CN109114019A|2017-06-23|2019-01-01|博格华纳公司|axial fan|
    GB201809353D0|2018-06-07|2018-07-25|Rolls Royce Plc|Aerofoil|
    法律状态:
    2018-09-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-05-03| PLSC| Publication of the preliminary search report|Effective date: 20190503 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 4 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1760212|2017-10-30|
    FR1760212A|FR3073016B1|2017-10-30|2017-10-30|MODULATION OF THE SERRATIONS IN THE END OF DAWN|FR1760212A| FR3073016B1|2017-10-30|2017-10-30|MODULATION OF THE SERRATIONS IN THE END OF DAWN|
    US16/174,553| US10941667B2|2017-10-30|2018-10-30|Modulation of vane end serrations|
    EP18306419.5A| EP3477057B1|2017-10-30|2018-10-30|Modulation of serrations at blade end|
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