• 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 proposed invention is a turbomachine air flow rectification assembly comprising: - a cylindrical platform (15) centered on an axis (XX), - at least one stator blade (20) extending from of the platform, and - a mechanical member (40) projecting from the platform (15), the straightening assembly being characterized in that it further comprises a fairing (50) of the protruding mechanical member, the fairing having a three-dimensional surface defined by: at least one upstream end point (Ai, Ae) situated axially upstream of the mechanical member with respect to the direction of flow of the air in the turbomachine, and - at least one downstream end point (Ci, Ce) situated axially downstream of the mechanical member, the three-dimensional surface being tangent to the platform at the upstream and downstream end points (Ai, Ae); , Ci, Ce).
    公开号:FR3039598A1
    申请号:FR1557262
    申请日:2015-07-29
    公开日:2017-02-03
    发明作者:Vianney Christophe Marie Maniere；Henri-Marie Damevin；Philippe Jacques Pierre Fessou；Sebastien Nicolas Juigne；Michael Franck Antoine Schvallinger
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION The invention relates to a turbomachine flow rectification assembly, and a turbomachine comprising such an assembly. The invention applies in particular to turbomachines of the double-flow type.
    STATE OF THE ART
    A turbomachine with a double flow for aeronautical propulsion is shown in FIG. 1. It comprises a fan 10 delivering a flow of air of which a central part, called primary stream FP1, is injected into a compressor 12 which supplies a turbine 14 driving the fan.
    The peripheral part, called the secondary flow Fs, of the air flow is in turn ejected to the atmosphere to provide the major part of the thrust of the turbomachine 1, after having passed a fixed blade crown disposed downstream of the blower. This ring, called the rectifier 20 (also known by the acronym OGV for "Outlet Guide Vane"), straighten the secondary air flow at the output of the fan, while limiting losses to the maximum.
    In the same figure is shown a structural arm 30, which connects the outer ring of the intermediate casing to the inner shell of the intermediate casing, thus contributing to support and maintain in position the (s) shaft (s) motor and ensure the holding structural of the whole. The structural arms also have the function of allowing the transmission of movement or fluids between the turbomachine and the rest of the aircraft on which it is mounted. To do this, the structural arms are hollow, and can accommodate pipes, shafts, etc..
    In order to improve the aerodynamic performance of a dual-flow turbomachine, it is sought to increase the turbomachine dilution ratio, that is to say the ratio between the flow in the secondary vein and the flow in the vein. primary.
    However, the presence of the structural arm 30 and other intrusive mechanical organs protruding into the secondary vein disturb the flow of air in the secondary vein and limit the improvement of the dilution ratio.
    Indeed, the outer diameter of the turbomachine is constrained by the integration of all the elements under the wing of the aircraft to which is attached the turbomachine, while maintaining a sufficient guard between the bottom of the turbomachine once hooked under the wing and the ground (in particular sufficient guard to cross the lights installed on the runways of take-off and landing). As a result, some organs are sometimes prominent in the secondary vein.
    The structural arm is frequently the housing of a radial transmission shaft, the projecting members inside the secondary vein may comprise, at one end of this arm, a gearbox (or TGB for Transfer GearBox) or an intermediate gear for driving the radial shaft (or IGB for Intermediary GearBox).
    It is therefore necessary to mitigate the harmful aerodynamic consequences of these problems of integration of the mechanical elements.
    DESCRIPTION OF THE INVENTION The purpose of the invention is to propose a turbomachine air flow rectification assembly, in particular with double-flow, having improved aerodynamics. In this regard, the invention relates to a turbomachine air flow rectification assembly comprising: a cylindrical platform centered on an axis, at least one stator blade extending from the platform, and a mechanical member projecting from the platform, the straightening assembly being characterized in that it further comprises a fairing of the projecting mechanical member, the fairing having a three-dimensional surface defined by: at least an upstream end point located axially upstream of the mechanical member with respect to the direction of flow of air in the turbomachine, and at least one downstream end point located axially downstream of the mechanical member, the three-dimensional surface being tangent to the platform at the upstream and downstream endpoints.
    Advantageously, but optionally, the assembly according to the invention may further comprise at least one of the following features: the stator vane comprises a leading edge, and the axial position of each upstream endpoint of the three-dimensional surface is defined by:
    XBA + 0-25 Cqgv - XA - X1KOZ where xA is the axial position of the upstream end point of the three-dimensional surface, xBA is the axial position of the leading edge of the stator vane, c0GV is the string of the rectifier blade, and x1KOz is the axial position of the upstream end of the mechanical member. the three-dimensional surface is further defined by at least one point of maximum height with respect to the platform to the right of a point of maximum height of the mechanical member relative to the platform, and the three-dimensional surface has, between this point and a downstream end point, a slope less than 30%. The assembly may further comprise a structural arm extending radially with respect to the axis, and the three-dimensional surface of the fairing may be defined by an upstream end point on the side of the intrados of the structural arm, and a point upper end of the extrados side, said points having axial positions at most 0.1 c0GV. The assembly may further comprise a structural arm extending radially relative to the axis, and the three-dimensional surface of the fairing may be defined by a downstream end point on the side of the intrados of the structural arm, and a point the downstream end of the extrados side, said points having axial positions at most 0.1 c0GV. The assembly may further comprise a structural arm extending radially with respect to the axis, wherein the three-dimensional surface of the fairing has a larger section measured along an axis orthogonal to the first, and the surface is further defined by two lateral endpoints corresponding to the ends of said larger section respectively of the intrados and extrados side of the structural arm (30), the axial positions of said points being at most 0.1 c0GV.
    The three-dimensional surface can also be defined by a point of maximum height with respect to the platform on the side of the intrados of the structural arm and a point of maximum height with respect to the platform on the side of the upper surface of the structural arm, and the axial positions of the lateral extreme points and the points of maximum height are at most 0.1 Cqqv. the three-dimensional surface of the fairing can be tangent to the platform at the extreme lateral points. the protruding mechanical member may be one of the group comprising: a radial shaft, an angular gearbox of a radial shaft, an electrical, hydraulic or pneumatic connection element, an intermediate gear of drive of a radial shaft. The invention also relates to a turbomachine, comprising a set of air flow rectification according to the foregoing description.
    The proposed fairing allows, by covering the mechanical members projecting in the air flow channel, while proposing a continuity of tangency between the surface of the fairing and the support platform of the stator vanes and the structural arm, to limit the disturbances of the flow of air in the vein. The application of such an assembly to a double-flow turbomachine therefore makes it possible to obtain a better dilution ratio.
    The fact of proposing a limited slope on the downstream side of the fairing also makes it possible to limit the appearance of aerodynamic detachments.
    Finally the fairing extends from at least a quarter of the cord of the stator blade to limit the size of the vein and the rise of static pressure distortion.
    DESCRIPTION OF THE FIGURES Other features and advantages of the present invention will appear on reading the following description of a preferred embodiment. This description will be given with reference to the accompanying drawings, in which: FIG. 1 previously described represents an example of a turbomachine; FIG. 2a represents a top view of a set of airflow rectification according to one embodiment. of the invention,
    FIG. 2b represents a cross-sectional view of an air flow rectification assembly according to a sectional plane identified in FIG. 2a,
    FIG. 2c represents a view of an air flow rectification assembly on the intrados side of the structural arm.
    DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION
    Referring to Figures 2a to 2c, there is shown a set of air flow rectification of a turbomachine double-flow. This assembly comprises a platform 15 which is constituted by an inner or outer rotor support ring 20 of secondary flow rectifier Fs air flowing in the turbomachine. Stator blades 20 may also be referred to by the acronym OGV for Outlet Guide Vane.
    The platform 15 is a crown centered on an axis X-X, this axis being the main axis of the turbomachine. The assembly also comprises at least one straightener blade 20 extending from the platform, radially about the axis XX, FIG. 2a being a developed view of an angle sector covered by two vanes. 20 of straightener extending on either side of a structural arm. The stator vane 20 has a leading edge 21 whose axial position is denoted xBa, a trailing edge 22, and a chord c0gv, which is the distance, measured in the direction of the axis XX, between the edge 21 and the trailing edge 22.
    In addition, the assembly comprises a structural arm 30.
    The structural arm is advantageously, but not exclusively, of the "integrated stator vane" type, that is to say that it comprises an upstream end portion 31 having the profile of a stator vane. This is the case in the example shown in FIG. 2a.
    The structural arm 30 further comprises a hollow zone 32 called "prohibited design" (or KOZ for Keep-Out Zone) which is a housing dedicated to the implantation of mechanical elements necessary for the operation of the turbomachine such as servitudes, and in particular the housing of pipes, for example oil or fuel, electrical connections, one or more shafts, etc. The assembly also comprises a mechanical member 40 projecting into the airflow channel from the platform 15. This mechanical member is located at one end of the structural arm 30 and, for the integration reasons indicated in introduction, emerges inside the vein. The mechanical member 40 may comprise, in the case where the structural arm 30 houses a radial transmission shaft, an end of this shaft, a gearbox of this shaft (or Transfer Gear Box) or an intermediate gear of training of this tree (or Intermediary Gearbox). In the case where the structural arm 30 houses servitudes, the mechanical member 40 may also or alternatively comprise electrical connection elements, hydraulic (oil or kerosene lines), or pneumatic. The assembly further comprises a fairing 50 of the projecting mechanical member, that is to say a wall covering this body having an aerodynamic shape limiting disturbances of the flow of air flowing into the vein. In this respect, the fairing has a three-dimensional surface whose geometry depends on that of the mechanical member 40. The mechanical member 40 is parameterized by:
    The axial position of its upstream end XiKoz, which is downstream of the leading edge 21 of the stator vane 20: x1KOz ^ xba - The axial position of its downstream end: x2koz, which is downstream of the upstream end : χζκοζ - χικοζ - The maximum height of the organ hKoz, that is to say the maximum radial distance of the mechanical organ from the axis XX, and - The largest width that it occupies in a orthogonal plane to the XX axis. As can be seen in FIG. 2b, this width is parameterized by the positions yeKoz and yiKoz, on an axis YY orthogonal to the axis XX and orthogonal to a radial axis around X (YY is thus tangential to a circle centered on the axis XX), ends of this width respectively of the extrados side and the intrados side of the structural arm 30. The positions yeKoz and yiKoz on the YY axis are measured with respect to an origin taken in the middle of the prohibited area of the drawing 32.
    Then the three-dimensional surface of the shroud 50 is also parameterized by a set of points.
    Thus, A and Ae denote the upstream end points with respect to the air flow of the three-dimensional surface of the fairing 50, respectively on the intrados and on the extrados side of the structural arm 30.
    The upstream end points A and Ae are preferably axially aligned but a tolerance is allowed such that their axial positions are at most one tenth of the cord of the stator vane:
    In order to cover the mechanical member 40, each upstream end point is upstream of the upstream end of the mechanical member 40:
    In addition, as shown in FIG. 2c, the three-dimensional surface of the fairing 50 is advantageously tangential to the platform 15 at the upstream end points A and Ae. Indeed, it results in a continuity between the platform surface and that of the fairing which limits the disturbances on the air flow and maintains good aerodynamic performance.
    In addition, in order not to disturb the flow of air at the inlet of the vein, the axial position of each upstream end point is advantageously distant from the leading edge 21 of the stator vanes 20 by at least a quarter of the dawn rope:
    C, and Ce are the downstream end points with respect to the air flow of the three-dimensional surface of the fairing 50, respectively on the intrados and the extrados side of the structural arm.
    The downstream end points C 1 and C 2 are preferably axially aligned, but a tolerance is allowed such that their axial positions are at most one tenth of the cord of the stator vane:
    In order to cover the mechanical member 40, each downstream end point of the fairing surface 50 is located downstream of the downstream end of the mechanical member 40:
    In addition, as shown in FIG. 2c, the three-dimensional surface of the fairing 50 is also tangent to the platform 15 at the downstream end points Q and Ce, to limit the disturbances of the air flow in the vein.
    The three-dimensional surface of the fairing 50 is also parameterized by two points Dj, De of maximum height measured radially with respect to the axis X-X, respectively of the intrados and the extrados side of the structural arm. We denote rDi and rDe respectively the radial distance of these points with respect to the axis, and xDi and xDe their axial position. The points of maximum height Dj, De have the same axial position as the point of maximum height hKoz of the mechanical member 40.
    So that the three-dimensional surface covers the mechanical member 40 we have:
    However, to limit the size of the fairing in the vein, the heights of points Di, De are the lowest possible. We have advantageously:
    The points Dj, De are advantageously aligned axially, to one tenth of the string of the dawn 20 of the rectifier:
    Advantageously, the axial position of the downstream end points is adapted to that of the points of maximum height to limit the slope of the three-dimensional surface to less than 30%. The minimization of the slope makes it possible to reduce the unfavorable pressure gradients and to avoid the detachment of the flow.
    Finally, the three-dimensional surface is parameterized by two extreme lateral points B ,, Be. These points correspond to the ends of the largest cross section of the mechanical member 40 measured along the Y-Y axis. We denote xBi and xBe the axial positions of these points, and yBi and yBe their position along the Y-Y axis with respect to the center of the forbidden drawing zone 32.
    So that the three-dimensional surface covers the mechanical member 40 we have:
    However, the maximum space along the Y-axis, and therefore the positions yei and yBe, are constrained by the width Sogv of the channel between the structural arm 30 and the adjacent stator vane 20:
    The points Bj, Be are advantageously aligned axially, to one tenth of the string of the vane 20 of the straightener:
    As can be seen in FIG. 2b, the three-dimensional surface of the fairing 50 is advantageously tangential to the platform 15 at the points B and Be to limit the disturbances of the air flow in the vein.
    In addition, the axial positions of the lateral extreme points and the points of maximum height are advantageously distant at most one tenth of the cord of the stator vane 20.
    The parameterization indicated above thus makes it possible to preserve the aerodynamic performances of the secondary vein of a double-flow turbomachine, and thus to improve the dilution ratio, without impacting the ground clearance of the aircraft on which the turbomachine is installed.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A turbomachine airflow rectifying assembly comprising: a cylindrical platform (15) centered on an axis (XX), at least one stator blade (20) extending from the platform, and a mechanical member (40) projecting from the platform (15), the straightening assembly being characterized in that it further comprises a fairing (50) of the projecting mechanical member, the fairing having a three-dimensional surface defined by: at least one upstream end point (Ai, Ae) located axially upstream of the mechanical member (40) with respect to the direction of flow of air in the turbomachine, and at least one downstream end point (Ci, Ce) located axially downstream of the mechanical member, the three-dimensional surface being tangential to the platform at the upstream and downstream end points (A 1, Ae, C, Ce ).
    [2" id="c-fr-0002]
    The airflow rectifying assembly of claim 1, wherein the stator vane (20) comprises a leading edge (21), and the axial position of each upstream endpoint (A 1, A 2 ) of the three-dimensional surface is defined by:

    where xA is the axial position of the upstream end point of the three-dimensional surface, xBA is the axial position of the leading edge (21) of the stator blade (20), cOGV is the rope of the blade (20) ) of the rectifier, and x1KOz is the axial position of the upstream end of the mechanical member (40).
    [3" id="c-fr-0003]
    3. airflow rectifying assembly according to one of claims 1 or 2, wherein the three-dimensional surface is further defined by at least one point of maximum height (Di, De) with respect to the platform ( 15) to the right of a point of maximum height of the mechanical member relative to the platform, and the three-dimensional surface has, between this point (Db De) and a downstream end point (Q, Ce), a slope less than 30%.
    [4" id="c-fr-0004]
    An airflow rectification assembly according to one of the preceding claims, further comprising a structural arm (30) extending radially with respect to the axis (XX), wherein the three-dimensional surface of the fairing (50) ) is defined by an upstream end point (A,) on the intrados side of the structural arm (30), and an upstream end point (Ae) on the extrados side, said points having axial positions distant at most 0.1 c0GV.
    [5" id="c-fr-0005]
    The airflow rectification assembly according to one of the preceding claims, further comprising a structural arm (30) extending radially with respect to the axis (XX), wherein the three-dimensional surface of the fairing (50) ) is defined by a downstream end point (C,) on the underside side of the structural arm (30), and a downstream end point (Ce) on the extrados side, said points having axial positions distant at most 0.1cOGV ,.
    [6" id="c-fr-0006]
    Airflow straightening assembly according to one of the preceding claims, further comprising a structural arm (30) extending radially with respect to the axis, wherein the three-dimensional surface of the shroud has a larger section. measured along an axis (YY) orthogonal to the first, and the surface is further defined by two lateral extreme points (B ,, Be) corresponding to the ends of said larger section respectively of the intrados and extrados side of the structural arm (30), the axial positions of said points being at most 0, 1cogv-
    [7" id="c-fr-0007]
    7. straightening assembly according to claim 6, wherein the three-dimensional surface is further defined by a point of maximum height (D,) with respect to the platform on the side of the intrados of the structural arm (30) and a point of maximum height (De) with respect to the platform on the extrados side of the structural arm (30), and the axial positions of the lateral extreme points and the maximum height points are separated by at most 0AcOGV.
    [8" id="c-fr-0008]
    8. straightening assembly according to one of claims 6 or 7, wherein the three-dimensional surface of the fairing (50) is tangential to the platform at the lateral end points.
    [9" id="c-fr-0009]
    9. airflow rectifying assembly according to one of the preceding claims, wherein the projecting mechanical member (40) is one of the group comprising: a radial shaft, - a gear box a radial shaft, an electrical, hydraulic or pneumatic connection element, an intermediate gear for driving a radial shaft.
    [10" id="c-fr-0010]
    10. Turbomachine, comprising a set of air flow rectification according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
    CA2862280C|2020-01-28|Jet engine fan blade
    CA2975570A1|2016-08-18|Guide assembly with optimised aerodynamic performance
    CA2826153A1|2012-08-16|Blade-platform assembly for subsonic flow
    EP2085620B1|2011-04-13|Jet engine compressor
    EP3204620B1|2018-11-21|Stator of an aircraft turbine engine
    WO2016128665A1|2016-08-18|Turbine engine air guide assembly with improved aerodynamic performance
    WO2017017392A1|2017-02-02|Air-flow straightening assembly having improved aerodynamic performances
    CA2798680A1|2011-12-01|Vortex generators for generating vortices upstream of a cascade of compressor blades
    EP3477050B1|2022-03-02|Turbomachine compressor with asymmetricly contoured wall ring
    FR2938871A1|2010-05-28|Blade grid for use as e.g. mobile wheel of compressor of aeronautical turbomachine, has rings with discharge guides placed circumferentially between blades, where rings are extended along directions parallel to skeleton lines of blades
    EP3290656B1|2021-09-29|Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process
    FR2982842A1|2013-05-24|PLANE
    WO2017144807A1|2017-08-31|Hub for propeller having variable-pitch blades, with radial and axial dimensioning variation
    CA3024433A1|2019-05-22|Mast for a propulsive assembly
    CA2956347A1|2017-08-08|Turbine engine compressor blade
    EP3290657B1|2021-02-24|Stator with adjustable vanes for the compressor of an axial turbine engine
    EP3444444B1|2020-06-17|Variable pitch blade system for a turbomachine compressor
    FR3081185A1|2019-11-22|STATOR ELEMENT OF TURBOMACHINE
    BE1028097B1|2022-01-26|Turbomachine compressor blade, compressor and turbomachine fitted therewith
    EP3473813A1|2019-04-24|Turbine engine with a rectifier unit
    WO2017187093A1|2017-11-02|Air flow rectification assembly and turbomachine comprising an assembly of this type
    WO2019158875A1|2019-08-22|Turbine engine with a flow splitter having a profile with inclined serrations
    WO2021044107A1|2021-03-11|Turbomachine polyspherical hub for variable pitch blades
    FR3088972A1|2020-05-29|Centrifugal compressor impeller, compressor equipped with this impeller and turbomachine equipped with this compressor
    FR3087828A1|2020-05-01|MOBILE TURBOMACHINE BLADES
    同族专利:
    公开号 | 公开日
    US10641289B2|2020-05-05|
    FR3039598B1|2019-12-27|
    WO2017017392A1|2017-02-02|
    US20180231025A1|2018-08-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20120093642A1|2009-05-07|2012-04-19|Volvo Aero Corporation|Strut and a gas turbine structure comprising the strut|
    US20130259672A1|2012-03-30|2013-10-03|Gabriel L. Suciu|Integrated inlet vane and strut|
    WO2014018137A2|2012-04-25|2014-01-30|General Electric Company|Aircraft engine driveshaft vessel assembly and method of assembling the same|
    EP2878796A1|2012-07-26|2015-06-03|IHI Corporation|Engine duct and aircraft engine|
    FR3010154A1|2013-09-05|2015-03-06|Snecma|INTERMEDIATE CASTER SEAL PANEL FOR A DOUBLE FLOW AIRCRAFT TURBOMACHINE|FR3073891A1|2017-11-22|2019-05-24|Safran Aircraft Engines|MAT OF A PROPULSIVE ASSEMBLY|FR3039598B1|2015-07-29|2019-12-27|Safran Aircraft Engines|AIR FLOW RECTIFICATION ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE|FR3039598B1|2015-07-29|2019-12-27|Safran Aircraft Engines|AIR FLOW RECTIFICATION ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE|
    FR3090033B1|2018-12-18|2020-11-27|Safran Aircraft Engines|TURBOMACHINE OUTLET AND BIFURCATION DIRECTOR VANE ASSEMBLY|
    法律状态:
    2016-07-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-03| PLSC| Publication of the preliminary search report|Effective date: 20170203 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557262A|FR3039598B1|2015-07-29|2015-07-29|AIR FLOW RECTIFICATION ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE|
    FR1557262|2015-07-29|FR1557262A| FR3039598B1|2015-07-29|2015-07-29|AIR FLOW RECTIFICATION ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE|
    US15/748,165| US10641289B2|2015-07-29|2016-07-29|Airflow straightening assembly having improved aerodynamic performances|
    PCT/FR2016/051990| WO2017017392A1|2015-07-29|2016-07-29|Air-flow straightening assembly having improved aerodynamic performances|
    [返回顶部]