• 专利附录
  • 专利说明
  • 权利要求
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    • 专利摘要:
    The present invention relates to a part (1) or set of turbomachine parts comprising at least first and second obstacles (3I, 4, 3E) each having a leading edge (BA) and a trailing edge (BF), and a platform (2) from which the obstacles (3I, 4, 3E) extend; characterized in that the platform (2) has between the intrados of the first obstacle (3I, 4) and the extrados of the second obstacle (4, 3E) a non-axisymmetric surface (S) defining at least one fin (5) to substantially triangular section, each fin (5) being associated with a driving position and a trailing position on the surface (S), between which the fin (5) extends, such as: - said attack position is upstream of each of the leading edges (BA); said leakage position is downstream of each of the leading edges (BA).
    公开号:FR3059735A1
    申请号:FR1661945
    申请日:2016-12-05
    公开日:2018-06-08
    发明作者:Henri Joseph Riera William；Vincent Benoit Zielinger
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL AREA
    The present invention relates to a turbomachine part comprising obstacles and a platform having a nonaxisymmetric surface.
    STATE OF THE ART
    A double-flow turbomachine of the type in FIG. 1 has a fan (or "fan") compressing a large mass of cold air, part of which is injected into the compressor and heated (primary flow), the rest forming a cylindrical flow (secondary flow) enveloping the motor, rectified by an OGV grid ("Outlet Guide Vane", secondary flow rectifier) and directed towards the rear to create thrust.
    For this, the turbomachine typically comprises a hub bounding the secondary air stream internally, and a casing bounding the secondary air stream externally. Arms radially link the two (the hub is fixed relative to the casing, and movable relative to the central shaft), and transmit part of the forces between the motor and its support.
    In the arms pass various easements integrating engine components (such as an oil or fuel tube, cables, etc.). Two of the arms, clearly more massive, and generally placed at the top and at the base, are called pylons and serve as a support structure making it possible to connect the turbomachine to an aircraft.
    For reasons of mass reduction and performance gain, the arms and / or the pylons (called together “bifurcations”) can be joined in the same structure as the blades of OGV, and then be called “integrated”, like we see in Figure 1. More specifically, the rectifier stage comprises on its circumference the bifurcations arranged between sequences of blades of OGV.
    This leads to a shape of type "eagle beak" as visible in Figure 2 (with reference to the shape of the bifurcation near its leading edge) which generates less losses than in the configuration called "separate »Where the bifurcations are downstream of a crown of OGV blades. However, due to the massive nature of the bifurcation it is necessary that the OGV blades are arched on the lower surface and decambered on the upper surface of the bifurcation. This gives a so-called "multi-family" configuration of OGV.
    These multi-family OGVs make it possible to reduce the distortion which rises on the Fan and to reduce the pressure losses linked to the presence of the bifurcation just downstream. However, cambered and de-cambered blades are no longer as adapted to the aerodynamic load on blading as can be a grid of separate OGVs without bifurcation downstream.
    The aerodynamic load on the blades of arched OGVs is higher and they cannot completely deflect the flow. This brings about a detachment on the upper side of the pressure loss generator blade.
    Likewise, the inflection and strong curvature zones on the "eagle's beak" generate pressure losses at the bifurcation.
    The areas in contact with the hub are all the more sensitive to this increase in aerodynamic load and to these areas of inflection and strong curvature.
    At the junction between the platform and the various obstacles, a so-called "corner" separation takes place, which generates pressure losses and reduces the stability and operability of the turbomachine.
    This corner detachment phenomenon is amplified in the case of multi-family OGVs, in particular for highly cambered OGVs located on the underside of the bifurcation.
    On the bifurcations, the zone of minimum curvature (called inflection zone) surrounded by solid lines in FIG. 2, and the zones of maximum curvature surrounded by dotted lines in FIG. 2, are the most impacted by these detachment phenomena of corner.
    It can therefore be seen that the geometries of OGV grids remain perfectible, in particular in "integrated" configurations.
    It would thus be desirable to have a new geometry making it possible to reduce the corner detachments on these forms in order to improve the performances (reduction of the drag of friction) and the stability (reduction of the detachments of boundary layer and associated vein obstruction ).
    PRESENTATION OF THE INVENTION
    According to a first aspect, the present invention thus provides a part or assembly of parts of a turbomachine comprising at least first and second obstacles each having a leading edge and a trailing edge, and a platform from which extend the obstacles ;
    characterized in that the platform has between the lower surface of the first obstacle and the upper surface of the second obstacle a non-axisymmetric surface defining at least one fin of substantially triangular section, each fin being associated with an attack position and a flight position on the surface, between which the fin extends, such as:
    - Said attack position is upstream of each of the leading edges;
    - said trailing position is downstream of each of the leading edges.
    According to other advantageous and non-limiting characteristics:
    • the fin has a height of between 0.5% and 15% of the height of each obstacle, and more particularly between 0.5% and 5%;
    • the trailing position is located at least 50% relative length of an obstacle rope extending from the leading edge to the trailing edge of the obstacle having the most upstream trailing edge;
    • said trailing position is downstream of the trailing edge of the obstacle having the most upstream trailing edge;
    • said attack position extends upstream of each of the leading edges by up to 15% of relative length of an obstacle cord extending from the leading edge to the trailing edge of the obstacle having the most upstream trailing edge;
    • one of the first and second obstacles is a blade and the other is a bifurcation having a trailing edge downstream of the leading edge of said blade;
    • the bifurcation present on its lower surface or its upper surface facing said blade a point of maximum curvature downstream of the trailing edge of said blade;
    • said trailing position extends substantially axially up to the point of maximum bending of the bifurcation;
    • the part comprises at least two blades, a first blade and a second blade, the platform has at least two non-axisymmetric surfaces each defining said fin with substantially triangular section, including a first surface for which the first blade forms the first obstacle and the bifurcation forms the second obstacle, and a second surface for which the bifurcation forms the first obstacle and the second blade forms the second obstacle;
    • each fin has a trace corresponding to the mean line of the skeletons of the first and second obstacles;
    • the surface defines one or two fins side by side;
    • each of the first and second surfaces further defines a secondary fin shorter than the fin, and located on the upper surface of said fin;
    • the platform has an annular shape along which are regularly arranged a plurality of obstacles;
    • the part is a secondary flow rectifier.
    According to a second aspect, the invention relates to a turbomachine comprising a part according to the first aspect previously stated.
    PRESENTATION OF THE FIGURES
    Other characteristics 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 appended drawings in which:
    - Figure 1 previously described shows an example of a turbomachine;
    - Figure 2 previously described shows an example of known geometry of OGV integrated with a bifurcation;
    - Figure 3 shows a 3D view of an example of the geometry of a part according to the invention;
    - Figures 4a-4b show two examples of geometries of a part according to two embodiments of the invention.
    DETAILED DESCRIPTION
    With reference to FIG. 2, the present part 1 (or set of parts if it is not in one piece) of a turbomachine has, in known manner and as explained, at least two consecutive obstacles 3E, 4, 3I and a platform 2 from which extend the obstacles 3E, 4, 3I.
    A double-flow turbomachine typically includes a hub bounding the secondary air stream internally, and a housing bounding the secondary air stream externally. Arms radially link the two, and transmit part of the forces between the motor and its support.
    The present part or set of part 1 is advantageously a stage for the rectifier of the secondary flow, in particular a crown of fixed blades (called OGV for "Outlet Guide Vane") most often disposed at the outlet of the blower rotor, and even more advantageously a crown of integrated OGVs (ie some of the obstacles are not blades).
    In the remainder of this description, we will take the example of a stage of integrated OGVs, but those skilled in the art will be able to transpose to the other types of parts 1 (for example, a stage of separate OGVs or a primary flow rectifier stage (ie a compressor stator stage).
    The term "obstacle" designates any element placed across the air flow and having an influence on its flow, having a leading edge BA, a trailing edge BF, a lower surface and an upper surface.
    Most of them are 3E, 3I blades (and in particular in an embodiment where part 1 is a stage of secondary flow rectifier with integrated OGV, the obstacles are all 3E, 3I blades), but in a preferred embodiment where the part 1 is a stage of secondary flow rectifier with integrated OGV, at least one of the obstacles is a bifurcation 4, that is to say a wider element, longer and less profiled than the blades 3I, 3E, having as explained a structural function more than aerodynamics, in particular for the connection of the platform 2 to a casing or a hub of the part 1 and / or the passage of easements. In particular, it will be understood that the bifurcations 4 have a trailing edge clearly downstream (relative to the flow of fluid) of the trailing edge of the blades 3I, 3E. Furthermore, on each of their upper and lower surfaces, the bifurcations 4 have a maximum point of curvature (in the middle of the dotted area in FIG. 2), generally slightly downstream of the trailing edges BF of the neighboring blades 3I, 3E. .
    In general, it will be understood that the obstacles 3E, 4, 3I are chosen from blades 3E, 3I and bifurcations 4, the latter can themselves be of several types: arms or pylon, depending on their size and their importance in the structural integrity.
    In particular one or two of the bifurcations 4 are pylons, in particular a main pylon arranged at the top of the part 1 (so-called 12 o'clock position), and / or a secondary pylon arranged at the base of the part 1 (so-called 6 o'clock position ). The two pylons are thus diametrically opposed. The pylons are support elements for the entire turbomachine, in particular the main pylon which allows attachment to an aircraft.
    The pylons are significantly more massive than any other arm-type bifurcations (which are themselves significantly more massive than the blades 3E, 31), and the main pylon is itself significantly more massive than the secondary pylon. The pylons (and in particular the main pylon) have a trailing edge clearly downstream of the trailing edge of any other bifurcations of the arm type. These can be arranged regularly or not between the pylons.
    Preferably, all the bifurcations 4 are pylons, ie there is no "arm", and in the remainder of this description, we will take the general case of a bifurcation 4 of pylon type disposed between two blades equivalent 3E, 31, but those skilled in the art will know how to transpose the invention to any other configuration.
    The term "platform" is here interpreted in the broad sense and generally designates any element of a turbomachine on which obstacles 3E, 4, 31 are able to be arranged projecting by extending radially and having an internal / external wall against which the air circulates. The platform 2 generally has an annular shape along which is disposed said plurality of obstacles 3E, 4, 31.
    In particular, the platform 2 can be in one piece (and thus support all of the blades of the part 1), or formed of a plurality of elementary members each supporting a single obstacle 3I, 4, 3E (a "foot" of the obstacle) so as to constitute a dawn.
    In particular, the platform 2 can comprise a platform part for each of the obstacles 3E, 4, 3I in an advantageous embodiment which will be described later.
    In addition, the platform 2 can delimit a radially inner wall of the part 1 (the air flow passes around) by defining a hub, and / or a radially outer wall of the part 1 (the air flow passes at inside, the obstacles 3I, 4, 3E extend towards the center) then defining a casing of the part 1. It should be noted that the same part 1 can simultaneously comprise these two types of platform 2.
    Platform area
    This part 1 is distinguished by a particular geometry (non-axisymmetric) of at least one surface S (advantageously at least two referenced SE, SI) of a platform 2 of part 1, of which an example of advantageous modeling is observed. in Figure 3. It will be understood that in Figure 3 a single central obstacle 3E, 4, 3I is visible, but that other obstacles are inherently present.
    Each surface S extends between two obstacles 3E, 4, 3I. The surface or surfaces S are in fact part of a larger surface defining a substantially toroidal shape around the part 1. In the hypothesis (but not limiting) of a periodicity in the circumference of the part 1, one can find several occurrences of the various surfaces S.
    A surface S is limited upstream by a first extremal plane, the "Separation plane" and downstream by a second extremal plane, the "Connection plane", which each define an axisymmetric contour, continuous and of continuous derivative (the curve corresponding to the intersection between each of the extreme planes and the surface of the part 1 as a whole is closed and forms a loop). The surface S has a substantially parallelogrammic shape and extends continuously between the two extreme planes, and the two obstacles 3E, 4, 3I of a pair of consecutive obstacles. One of the blades of this pair of blades is the first blade 3I, 4, or lower surface obstacle. It indeed presents its lower surface on the surface S considered. The other obstacle is the second obstacle 4, 3E, or upper surface obstacle. It indeed presents its lower surface on the surface S. Each “second obstacle” 4, 3E is the “first obstacle” 3I, 4 of a neighboring surface in FIG. 3 (since each obstacle 3E, 4, 31 has a lower surface and an upper surface).
    In the following description, we take the example of two surfaces S referenced SI and SE. More precisely, two pairs of consecutive obstacles {31, 4} and {4, 3E} can be defined (the obstacle 4 being common to the two couples), and the surfaces SI and SE are two distinct surfaces, called respectively first and second surfaces, advantageously each according to the invention, and being understood between the two obstacles of each of the two couples respectively.
    Preferably, and in accordance with the preferred embodiments illustrated by FIGS. 4a, 4b, the common obstacle is a bifurcation 4, so that the surfaces SE and SI extend respectively to the lower surface and to the upper surface of the bifurcation 4 (it will indeed be understood that the references SI and SE are designated by proximity with the obstacles 31 and 3E to facilitate the reading of the text, and not to signify "surface of upper surface / lower surface"). In other words:
    - the blade 31 is the first obstacle of the first surface SI;
    - the bifurcation 4 is the second obstacle of the first surface SI and the first obstacle of the second surface SE;
    - the blade 3E is the second obstacle of the second surface SE.
    Fin
    The non-axisymmetric surface (s) SE, SI of the present part are remarkable in that they define at least one fin 5 with a substantially triangular section.
    By “substantially triangular section”, it is meant that the fins 5 have two oblique faces joining on a dorsal edge, either by an angle, or by a tangent connection. The two faces themselves are connected to the vein (rest of the surface S) either by an angle or by a tangent connection. Each fin 5 can also have beveled ends.
    ίο
    It is noted that the fact of having the fins between two blades of a part is known. But the known fins are generally either flat "strips" (see for example patent applications EP1927723, JP6022002, US4023350), or bumps (see document EP2194232), that is to say in no way substantially cross-section triangular within the meaning of the present invention. Indeed, these known elements (which are generally numerous) only have the role of acting as a barrier for the incident flow, and generating vortices.
    Application WO2015092306 proposes real fins with a substantially triangular section with a role of guiding the air flow, intended for a compressor stage. This geometry is adaptable to an OGV grid but is ineffective at the level of the eagle's beaks.
    The present fins 5 are distinguished from those of document WO2015092306 in their position in the vein. In fact, where the latter are arranged rather downstream relative to the direction of flow of the fluid, the one or more fins 5 protrude upstream from the obstacles 3I, 4, 3E.
    More precisely, each fin 5 is associated with an attack position and a flight position on the surface S, between which the fin 5 extends, such as:
    - Said attack position is upstream of each of the leading edges BA of neighboring obstacles 3I, 4, 3E;
    - Said flight position is downstream of each of the leading edges BA.
    More precisely and as will be seen in detail below, each obstacle 3I, 4, 3E has a leading edge BA and a trailing edge BF. Preferably and as explained, all the obstacles 3I, 4, 3E have leading edges BA with axial positions (ie along the longitudinal axis of the turbomachine) substantially identical, and trailing edges BF with axial positions different depending on the type of obstacle. More precisely, while all the obstacles of the blade type 3I, 3E have trailing edges BF with substantially identical positions, the obstacles of the bifurcation type 4 have trailing edges BF clearly downstream of the trailing edges BF of the blades 31, 3E.
    Thus, for a pair of obstacles 31, 4, 3E consecutive, the fin 5 between them begins upstream of the two leading edges BA of the pair of obstacles and ends downstream of these two leading edges BA.
    Preferably, there are one or two fins 5 on the vein (maximum three), preferably two as seen in the figures.
    The Applicant has indeed found that the present fins 5 "advanced upstream" prove to be very effective in avoiding significant detachments at the foot, in particular for the blades of OGVs around the bifurcations which are heavily loaded.
    In addition, this geometry makes it possible to ensure continuity with other fins (in particular of the type of those of document WO2015092306) between blades of the OGV, far from the bifurcations. This continuity preserves the ability of the fins to reduce the corner vortex and passage flow.
    Preferably, each fin 5 extends substantially axially in the vein (and not substantially azimuthally, as could be found for bosses in the prior art), or even has a trace (that is to say - say a trajectory) corresponding to the average line of skeletons of the first and second obstacles 3I, 4, 3E.
    It should be noted that the fins 5 offer another advantage: they can be used as a heat exchanger to facilitate the cooling of the part 1.
    Double surface
    In the preferred embodiment where an obstacle is a bifurcation 4, as preferably explained two surfaces S, including a first surface SI and a second surface SE, in accordance with the invention (ie having at least one occurrence of said fin 5 ) are defined. The bifurcation 4 is between the two surfaces SI and SE (and the assembly is flanked by the two blades 31 and 3E)
    For the first surface SI, a first blade 31 constitutes the first obstacle (i.e. presents its lower surface to it), and the bifurcation 4 constitutes its second obstacle (i.e. presents its upper surface to it). For the second SE surface, bifurcation 4 constitutes its first obstacle (i.e. presents its lower surface), and a second blade 3E constitutes its second obstacle (i.e. presents its upper surface).
    We can summarize by saying that in this double embodiment, the part or set of part 1 comprises at least three obstacles 3I, 4, 3E, including successively a first blade 3I, a bifurcation 4 and a second blade 3E, each having a leading edge BA and a trailing edge BF, and a platform 2 from which the obstacles 3I, 4, 3E extend; and presenting:
    - between the lower surface of the first blade 3I and the upper surface of the bifurcation 4, a first surface SI, and
    - Between the lower surface of the bifurcation 4 and the upper surface of the second blade 3E, a first surface SE, each of the first and second surfaces SE, SI being non-axisymmetric and defining at least one fin 5 of substantially triangular section, each fin 5 being associated with an attack position and a flight position on the surface SI, SE, between which the fin 5 extends, such that:
    - Said attack position is upstream of each of the leading edges BA;
    - Said flight position is downstream of each of the leading edges BA.
    Dimensions and position
    The fins 5 advantageously have a width of between 5% and 40% (preferably between 10% and 15%) of the distance between the lower surface of the first obstacle 31 and the upper surface of the second obstacle 3E. The width considered here is the maximum width of the base of the fin 5 (which is substantially constant, except at the level of any bevels of attack and flight). This width and the distance between the lower surface of the first obstacle 31, 4 and the upper surface of the second obstacle 4, 3E are preferably assessed according to planes parallel to the extreme planes (in other words according to the construction curves mentioned above) . The width will be around 30% or 40% for example for small spacings between obstacles.
    Preferably, each fin 5 has for example a height of between 0.5% and 5% of a height of each of the obstacles 31, 4, 3E. The fin height can even be up to 15% of the height of each of the obstacles 3I, 4, 3E. In the preferred embodiment of an OGV grid, all of the obstacles 3I, 4, 3E are fixed and have the same height. However, the fin can have a variable height by increasing, for example, regularly between 0.5% and 15% from upstream to downstream.
    As explained, each fin 5 is in particular defined by two extreme points: an attack position and a flight position on the surface S, between which the fin 5 extends (in particular by following the skeleton of obstacles 3I, 4, 3E).
    The position of attack is defined in the reference frame of the turbomachine by coordinates X B a and Yba, and the position of flight by coordinates X B f and Y BF . These coordinates are respectively an axial coordinate (ie along a longitudinal axis of the turbomachine oriented along the direction of movement of the gas flow) and an azimuthal coordinate (ie along an axis orthogonal to both the longitudinal direction of the turbomachine and the direction radial at the point considered, ie in a direction tangent to the surface S but orthogonal to the longitudinal direction) of the position. In FIGS. 4a and 4b, the longitudinal and azimuth axes are oriented to the right and to the top of the figure respectively. The radial axis is normal to the plane shown.
    The first X coordinate thus designates an (axial) position along an obstacle cord extending from a leading edge BA to a trailing edge BF of the most “upstream” obstacle, expressed in length. relative (in other words, at X = 0 corresponds to an alignment on the leading edges BA and X = 1 corresponds to an alignment with the trailing edge BF most upstream of the trailing edges BF of the obstacles 3I, 4 , 3E, ie that of a blade 3E, 3I and not of a bifurcation 4).
    These positions are such that:
    the attack (axial) position is located upstream of each of the attack edges BA (ie X BA <0) and
    - the (axial) leak position is located downstream of each of the leading edges BA (ie X BF >0);
    And preferably, these positions are such that:
    - the difference between the (axial) position of attack and the axial position of each of the leading edges BA is at most 15% of the relative length of the obstacle rope 3I, 4, 3E extending from the edge of attack BA at the trailing edge BF of the obstacle 3I, 4, 3E having the trailing edge BF most upstream (ie X BA e [-0.15; 0 [), and
    - the (axial) leak position located at least 50% (preferably at least 100%) of the relative length of the obstacle rope 3I, 4, 3E (ie X BF > 0.5, even X BF > 1). It will be understood that if the trailing position is located at least 100% of the relative length of the rope, it is because it is downstream of the trailing edge BF of the obstacle 3I, 4, 3E presenting the edge of LF leakage most upstream, ie that the fin 5 extends axially downstream of the leakage edge BF of an obstacle of the pale type, as seen for example in FIG. 4a.
    When the first and second barrier is a fork 4, as explained, it has a maximum curvature point (associated with an axial position X Cm ax) on its face which f has it opposite to the fin 5, generally au3059735 beyond the trailing edge BF of the blade 3E, 31 which constitutes the other obstacle bordering the fin 5 (ie the most upstream obstacle). So we have X Cmax > 1
    Said vaning position of the fin 5 advantageously extends substantially up to the said point of maximum curvature of the bifurcation 4, ie X BF ~ X C max, as seen in the example in FIG. 4a.
    The second Y coordinate designates a position (azimuthal) along a channel width extending from the lower surface of the first obstacle 31, 4 to the upper surface of the second obstacle 31, 4, expressed in relative length (in d other words, Y = 0 corresponds to a point against the lower surface of the first obstacle 31, 4 and Y = 1 corresponds to a point against the upper surface of the second obstacle 4, 3E).
    And preferably, these positions are such that each of the attack and flight positions associated with a fin 5 is located at a distance from the lower surface of the first obstacle 3I, 4 between 10% and 55% of the width of channel (ie Y BA , Y BF e [0.1,0.55]). Where the fins 5 can therefore be distributed in a balanced manner in the vein, but are preferably on average closer to the lower surface of the first obstacle 31, 4, see FIG. 4b.
    In the case of a single fin 5, preferably it will be substantially centered in the vein (see FIG. 4a).
    Furthermore, a person skilled in the art will be able to use the advantageous characteristics of the fins of application WO2015092306 if necessary by adapting them according to his general knowledge.
    Number of fins
    The best results are obtained for one or two fins 5. It is desirable not to exceed three fins 5.
    With two fins, these can be arranged in the middle of each of the platform parts 2 (as seen in FIG. 2), but preferably the fins 5 can, as explained, be rather on the side of the vein close to the lower surface obstacle 31, 4.
    In the preferred embodiment of Figure 4b, a main fin 5 is arranged in the middle of the vein, and a secondary fin 5 ', shorter (and more downstream: its attack position is not necessarily upstream of the leading edge BA of the obstacles 31, 4, 3E) is disposed on the upper surface of the main fin 5.
    In the case where one of the fins 5 is disposed in the middle of the vein (attack and flight positions associated with the fin 5 located at a distance from the lower surface of the first obstacle 31, 4 at approximately 50% of the width channel), it is possible to use the structure of the platform 2 to reconstitute this fin 5. Thus, if the platform 2 comprises a first platform part from which extend the first blade 31 and a second part of platform from which the second blade 3E extends (ie platform 2 formed of a plurality of elementary members each supporting an obstacle 31, 4, 3E), the connection between these two consecutive parts of platform 2 can be provided to match the trace of the fin 5.
    A protuberant cross-platform seal of suitable shape can then form the fin 5.
    This solution has many advantages, because it requires only few modifications compared to known parts and can facilitate assembly / disassembly by allowing greater tangential clearances between the platform parts 2.
    Alternatively or in addition, at least one fin 5 is inherent in the surface S.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1. Part (1) or set of parts of a turbomachine comprising at least first and second obstacles (3I, 4, 3E) each having a leading edge (BA) and a trailing edge (BF), and a platform ( 2) from which the obstacles extend (3I, 4, 3E); characterized in that the platform (2) has between the lower surface of the first obstacle (3I, 4) and the upper surface of the second obstacle (4, 3E) a non-axisymmetric surface (S) defining at least one fin (5) at substantially triangular section, each fin (5) being associated with an attack position and a flight position on the surface (S), between which the fin (5) extends, such as:
    - Said attack position is upstream of each of the leading edges (BA);
    - said trailing position is downstream of each of the leading edges (BA).
    [2" id="c-fr-0002]
    2. Piece or set of pieces according to claim 1, in which the fin (5) has a height of between 0.5% and 15% of a height of each of the obstacles (3I, 4, 3E).
    [3" id="c-fr-0003]
    3. Piece or set of pieces according to one of claims 1 and 2, wherein the escape position is located at least 50% of relative length of an obstacle rope (3I, 4, 3E) extending from the leading edge (BA) to the trailing edge (BF) of the obstacle (3I, 4, 3E) having the most upstream trailing edge (BF).
    [4" id="c-fr-0004]
    4. Part or set of parts according to claim 3, wherein said trailing position is downstream of the trailing edge (BF) of the obstacle (3I, 4, 3E) having the most trailing edge (BF) upstream.
    [5" id="c-fr-0005]
    5. Piece or set of pieces according to one of claims 1 to 4 wherein said attack position extends upstream of each of the leading edges (BA) by up to 15% relative length of a obstacle rope (3I, 4, 3E) extending from the leading edge (BA) to the trailing edge (BF) of the obstacle (3I, 4, 3E) having the most trailing edge (BF) upstream.
    [6" id="c-fr-0006]
    6. Piece or set of pieces according to one of claims 1 to 5, in which one of the first and of the second obstacle (3I, 4, 3E) is a blade (3I, 3E) and the other is a bifurcation (4 ) having a trailing edge (BF) downstream of the leading edge of said blade (3I, 3E).
    [7" id="c-fr-0007]
    7. Part or set of parts according to claim 6, in which the bifurcation (4) has on its lower surface or its upper surface facing said blade (3I, 3E) a point of maximum curvature downstream of the trailing edge (BF) of said blade (3I, 3E).
    [8" id="c-fr-0008]
    8. Part or set of parts according to claims 4 and 7 in combination, wherein said leakage position extends axially substantially until said point of maximum bending of the bifurcation (4).
    [9" id="c-fr-0009]
    9. Part or set of parts according to one of claims 6 to 8, comprising at least two blades (3I, 3E) including a first blade (3I) and a second blade (3E), the platform (2) has at least two non-axisymmetric surfaces (S) each defining said fin (5) of substantially triangular section, including a first surface (SI) for which the first blade (3I) forms the first obstacle and the bifurcation (4) the second obstacle, and a second surface (SE) for which the bifurcation (4) forms the first obstacle and the second blade (3I) the second obstacle.
    [10" id="c-fr-0010]
    10. Piece or set of pieces according to one of the preceding claims, in which each fin (5) has a trace corresponding to the mean line of the skeletons of the first and
    5 second obstacles (3I, 4, 3E).
    [11" id="c-fr-0011]
    11. Part or set of parts according to one of the preceding claims, in which the surface (S) defines one or two fins (5) side by side.
    [12" id="c-fr-0012]
    12. Part or set of parts according to claims 9 and 11 in combination, in which each of the first and second surface (SI, SE) further defines a secondary fin (5 ′) shorter than the fin (5), and located on the upper surface of said fin (5).
    [13" id="c-fr-0013]
    13. Piece or set of pieces according to one of the preceding claims, wherein the platform (2) has an annular shape along which are regularly arranged a plurality of obstacles (3I, 4, 3E).
    [14" id="c-fr-0014]
    14. Part or set of parts according to claim 13, being a secondary flow rectifier.
    [15" id="c-fr-0015]
    15. Turbomachine comprising a part (1) or assembly 25 of parts according to one of the preceding claims.
    1/5
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    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    US20180156239A1|2018-06-07|
    FR3059735B1|2020-09-25|
    US10690149B2|2020-06-23|
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    法律状态:
    2017-11-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-08| PLSC| Publication of the preliminary search report|Effective date: 20180608 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 3 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661945A|FR3059735B1|2016-12-05|2016-12-05|TURBOMACHINE PART WITH NON-AXISYMETRIC SURFACE|
    FR1661945|2016-12-05|FR1661945A| FR3059735B1|2016-12-05|2016-12-05|TURBOMACHINE PART WITH NON-AXISYMETRIC SURFACE|
    US15/831,706| US10690149B2|2016-12-05|2017-12-05|Turbine engine part with non-axisymmetric surface|
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