• 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 blade (1) for turbomachine rectifier (100) with a double flow of longitudinal axis (X), the blade (1) comprising a plurality of blade sections (2) stacked radially with respect to the axis (X) along a stack line (L) between a foot end (3) and a head end (4), each blade section (2) comprising a lower surface (7) and an extrados surface (8) extending axially between a leading edge (5) upstream and a trailing edge (6) downstream and being opposite tangentially. According to the invention, between the leading (5) and trailing edge (6) of each blade section (2) is formed a profile cord (CA) of substantially constant length between the leading end (4). ) and the foot end (3), and in that the stack line (L) has a curvature, in a plane passing substantially through the axis (X) and the stack line (L), located in the vicinity of the head end (4) and oriented from downstream to upstream.
    公开号:FR3070448A1
    申请号:FR1757896
    申请日:2017-08-28
    公开日:2019-03-01
    发明作者:Morgane Lemarchand Kevin；Bruno Andre Jodet Norman；Guillaume Martin；Laurent SOULAT
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Turbomachine fan rectifier blade, turbomachine assembly comprising such a blade and turbomachine equipped with said blade or said assembly.
    1. Field of the invention
    The present invention relates to the field of turbomachinery. It relates to a turbomachine blade and in particular a fan rectifier blade. The invention also relates to an assembly comprising a nacelle and a fan casing secured to the nacelle and which is equipped with at least one stator vane and a turbomachine equipped with such a vane or with such an assembly with a vane of rectifier.
    2. State of the art
    The natural evolution of multiflow turbojets with a fan, especially upstream, is to increase the propulsive efficiency via a reduction in the specific thrust, obtained by reducing the compression rate of the fan, which results in an increase in the rate dilution or BPR (for the English designation "Bypass Ratio"), which is the ratio between the mass flow of air through one or more veins surrounding the gas generator by the mass flow of air through the generator of gas, calculated at maximum thrust when the engine is stationary in an international standard atmosphere at sea level.
    The increase in the dilution rate influences the diameter of the turbomachine which is constrained by a minimum ground clearance to be respected due to the integration of the turbomachine most often under the wing of an aircraft. The increase in the dilution rate takes place as a priority on the diameter of the blower. The blower is surrounded by a blower casing which surrounds the blower blades and is connected to the gas generator by stator blades known as rectifiers or outlet guide vanes for the English designation of “Outlet Guide Vanes >> (logo OGV). These rectifier vanes are arranged radially from the casing of the gas generator, downstream of the fan blades and allow the flow generated by the latter to be rectified. These blades must be arranged at a predetermined minimum axial distance from the fan blades so as to limit the acoustic interactions responsible for significant noise. The predetermined axial distance between the blades determines the length of the fan housing. Added to this is the fact that the weight of the fan casing and in particular its length impact the drag of the turbomachine.
    3. Object of the invention
    The object of the present invention is in particular to limit the drag of the turbomachine nacelle and to limit the mass of the propulsion assembly.
    4. Statement of the invention
    This objective is achieved in accordance with the invention by means of a turbomachine rectifier vane with a double flow longitudinal axis, the vane comprising a plurality of vane sections stacked radially opposite the longitudinal axis along a stacking line between a foot end and a head end, each blade section comprising a lower surface and a upper surface extending axially between an upstream leading edge and a downstream trailing edge and being tangentially opposite, between the leading and trailing edges of each blade section being formed a profile cord of substantially constant length between the head end and the foot end, and the stacking line having a curvature in a plane passing substantially through the longitudinal axis and through the stacking line, located in the vicinity of the head end and oriented from downstream to upstream.
    Thus, this solution achieves the above-mentioned objective. In particular, the shape of the stator vane with this curvature makes it possible to shorten the length of the nacelle surrounding the fan casing intended to carry this stator vane, which advantageously reduces the drag. It also reduces the noise generated towards the end of the blade head when it is mounted in the nacelle. In particular, the acoustic intensity increases with the proximity between the fan blades and the stator vanes. The areas located around 75% of the height of the blade are particularly affected by these interactions due to the speeds observed and the aerodynamic load involved. The profile of the stator blade thus makes it possible to maintain a minimum axial distance required toward the top of the stator vanes.
    According to a characteristic of the invention, the curvature is located between 50% and 95% of the height of the blade between the end of the foot and the end of the head. This configuration makes it possible to act in the place where the acoustic and speed interactions are the highest and where the aerodynamic load involved.
    According to a characteristic of the invention, the shape of the blade, between 50% and 95% of the height of the blade, is determined by the following relationship: 0.1 <(L2 / L1) 50 % h <h <95% h <0.5, L2 corresponding to the minimum distance between the leading edge of the blade and a line passing through the foot end and the head end of the blade, L1 corresponding to the length between this same line and the trailing edge of the rectifier vane and H being the height of the vane. This configuration makes it possible, on the one hand, to limit the maximum angle at the foot end of the blade and, on the other hand, to limit the structural constraints. In other words, the curvature of the stator vane is defined between 50% and 95% of its height.
    According to another characteristic, the blade has a first portion of the foot, the stacking line of which extends along a straight line, and a second portion of the head, the stacking line of which comprises the curvature. This configuration only changes the upper part of the rectifier vane.
    According to yet another characteristic, the stacking line extending along a straight line is inclined relative to the longitudinal axis.
    According to yet another characteristic, the leading edge has a concave portion and the trailing edge has a convex portion at the level of the curvature. Thus, the directions of the leading edge and trailing edge of the blade have substantially parallel to the direction of the stacking line.
    The invention also relates to an assembly comprising a double-flow turbomachine nacelle extending along a longitudinal axis and a fan casing secured to the nacelle, the fan casing surrounding a blower and delimiting an annular vein in the downstream of the blower. which circulates an air flow, the fan casing comprising an annular row of stator vanes having any of the aforementioned characteristics arranged downstream of the fan vanes transversely in the annular stream. Such a characteristic makes it possible to reduce the length of the nacelle and to reduce the acoustic criterion in the upper part of the nacelle. In particular, for the same given fan diameter, an acoustic gain of about 2 EPNdB (“Effective Perceived Noise” in English or “effectively perceived noise level, in decibels”) is observed.
    According to a characteristic of the invention, the nacelle has a length substantially along the longitudinal axis of between 3000 and 3800 mm.
    According to another characteristic, the nacelle has a length substantially along the longitudinal axis and the blower has a diameter, substantially along the radial axis, the ratio of the length of the nacelle to the diameter of the blower being between 1 and 3 In particular, the diameter of the blower is measured at a leading edge, at its blower blade head.
    According to one characteristic, the relative axial distance between a fan blade and a stator blade is determined by the following condition: (d / C) with d being the distance between a trailing edge of the blower and the leading edge of rectifier blade, and C being the length of the axial chord of the fan blade, the curvature of the stacking line making it possible to verify the following relationship: (d / C) so% h <h <95% h> (d / C) ioo% h, with H the height of the stator blade between the head end and the foot end. (d / C) 50% h <h <95% h is the distance between the trailing edge of the blower and the leading edge of the stator vane divided by the length of the axial chord of the vane blower between 50% and 95% of the height of the stator vane, and (d / C) 100% H is the distance between the trailing edge of the blower and the leading edge of the stator vane divided by the length of the axial cord of the fan blade at the head of the stator blade. In particular (d / C) 100% H corresponds to the blade height at the contact between the stator blade and the fan casing.
    The invention also relates to a turbomachine comprising at least one stator vane having at least any of the above characteristics.
    5. Brief description of the figures
    The invention will be better understood, and other objects, details, characteristics and advantages thereof will appear more clearly on reading the detailed explanatory description which follows, of embodiments of the invention given by way of purely illustrative and nonlimiting examples, with reference to the appended schematic drawings in which:
    FIG. 1 schematically represents a turbomachine with a fan upstream of a gas generator and to which the invention applies;
    Figure 2 schematically illustrates a front view of a turbomachine blade according to the invention;
    FIG. 3 schematically represents a cross section of a blade according to the invention;
    FIGS. 4 and 5 are schematic views in axial and partial sections of a nacelle housing a turbomachine fan according to the invention, and,
    FIG. 6 is a schematic representation of a graph on which is illustrated the variation of the angles with respect to the longitudinal axis of the turbomachine measured at the trailing edge of the turbomachine vane.
    6. Description of embodiments of the invention
    FIG. 1 illustrates a turbomachine 100 for aircraft to which the invention applies. This turbomachine 100 is here a double flow turbomachine which extends along a longitudinal axis X. The double flow turbomachine generally comprises an external nacelle 101 surrounding a gas generator 102 upstream of which is mounted a blower 103. In the present invention , and generally, the terms "upstream" and "downstream" are defined with respect to the circulation of gases in the turbomachine 100. The terms "upper" and "lower" are defined with respect to a radial axis Z perpendicular to the X axis and with regard to the distance from the longitudinal axis X. A transverse axis Y is also perpendicular to the longitudinal axis X and to the radial axis Z. These axes, X, Y , Z form an orthonormal coordinate system.
    The gas generator 102 comprises in this example, from upstream to downstream, a low pressure compressor 104, a high pressure compressor 105, a combustion chamber 106, a high pressure turbine 107 and a low pressure turbine 108. The gas generator 102 is housed in an internal casing 109.
    The fan 103 is here faired and is also housed in the nacelle 101. In particular, the turbomachine comprises a fan casing 56 which surrounds the fan. On this fan housing 56 is fixed a retention housing 50 which surrounds the plurality of movable fan blades 51 which extend radially from the fan shaft mounted along the longitudinal axis X. The fan housing 56 and the retention housing 50 are integral with the nacelle 101 which envelops them. The nacelle 101 has a generally cylindrical shape. The fan casing 56 is located downstream of the retention casing 50 ensuring the retention of the fan blades 51.
    The blower 103 compresses the air entering the turbomachine 100 which is divided into a hot flow circulating in an annular primary stream V1 which passes through the gas generator 102 and a cold flow circulating in an annular secondary stream V2 around the gas generator 102 In particular, the primary vein V1 and the secondary vein V2 are separated by an annular inter-vein casing 110 disposed between the nacelle 101 and the internal casing 109. In operation, the hot flow circulating in the primary vein
    V1 is conventionally compressed by compressor stages before entering the combustion chamber. The combustion energy is recovered by turbine stages which drive the compressor stages and the blower. The latter is rotated by a power shaft of the turbomachine via, in the present example, a power transmission mechanism 57 to reduce the speed of rotation of the fan. Such a power transmission mechanism is provided in particular because of the large diameter of the fan. The large diameter of the blower increases the dilution rate. The power transmission mechanism 57 comprises a reduction gear, arranged here axially, between a blower shaft integral with the blower and the power shaft of the gas generator 102. The flow of cold air F circulating in the secondary stream V2 is oriented along the longitudinal axis X and participates for its part in providing the thrust of the turbomachine 100.
    Referring to Figures 1 and 4, each fan blade 51 has a leading edge 52, upstream and a trailing edge 53, downstream axially opposite (along the longitudinal axis X). The fan blades 51 each have a foot 54 located in a hub 30 which is crossed by the fan shaft and a head 55 facing the retention casing 50. The fan blades 51 have a diameter DF included, for example, between 1700 and 2800 mm. The diameter DF is measured at the leading edge 52 and at the level of the head 55 of the fan blade 51, along the radial axis Z. Preferably, but not limited to, the diameter DF is between 1900 and 2700 mm. As for the nacelle 101, this has an outside diameter DN of between 2000 and 4000 mm for example. Preferably, but not limited to, the outside diameter DN is between 2400 and 3400 mm.
    In the secondary stream V2 is arranged at least one stator vane 1 or radial stationary known as the fan rectifier vane or the fan flow guide vane. The rectifier blade is also known by the acronym OGV for "Outlet Guide Vane" in English and therefore makes it possible to straighten the cold flow generated by the blower 103.
    In the present invention, we mean by the term "fixed blade >> or" stator blade >>, a blade which is not driven in rotation about the axis X of the turbomachine 100. In other words, this stator blade is distinct and contrary to a movable or rotor blade of the turbomachine 100. In the present example, a plurality of stator vanes 1 is arranged transversely in the fan nacelle 101 substantially in a plane transverse to the longitudinal axis X. To straighten the flow of the fan 103, between ten and fifty stator vanes 1 are distributed circumferentially to form a stator stage. These stator vanes 1 are arranged downstream of the fan 103. These are secured to the fan casing 56. These are also regularly distributed around the axis X of the turbomachine.
    Referring to Figures 2 and 3, each stator vane 1 comprises a plurality of transverse vane sections 2 stacked in a radial direction (parallel to the radial axis Z) along a stacking line L between one end foot 3 and a head end 4. The stacking line L passes through the center of gravity of each transverse blade section 2. Each blade section comprises a lower surface 7 and a lower surface 8 extending substantially in an axial direction, between a leading edge 5, upstream and a trailing edge 6, downstream. The lower and upper surfaces 7, 8 are opposite one another in a tangential direction (parallel to the Y axis). Between the trailing edge 6 and the leading edge 5 extends a profile cord CA. The blade section 2 includes a curved transverse profile. The profile cord CA has a substantially constant axial length between the foot end 3 and the head end 4. In other words, the length of the profile cord at the foot end is substantially equal to the length of the profile cord at the head end.
    The stacking line L of the blade sections 2 forming the blade has a curvature in the vicinity of the head end 4 thereof. The rectifier vane 1 here has substantially a boomerang shape. As illustrated in Figure 2, the curvature is oriented from downstream to upstream (radially outward). In particular, the leading edge 5 and the trailing edge 6 follow the curvature movement of the stacking line L. That is to say that the direction of the leading edges 5 and trailing edge 6 are substantially parallel to the direction of the curvature of the stacking line L in the upper part of the blade 1. The curvature of the stacking line L is oriented in a perpendicular plane passing through the longitudinal axis X. The stacking line L is therefore defined in this plan. The curvature is also located towards the head end 4. This is located between 50% and 95% of the height H of the blade 1 taken between the foot end 3 and the head end 4 of l 'dawn as described later in the description.
    Each stator vane 1 is fixed to the internal casing 110 and to the fan casing 56 secured to the nacelle 101. The stator vanes 1 provide a structural role, they allow the recovery of forces. With reference to FIG. 4, the foot end 3 is connected, in this example, to the internal casing 110 while the head end 4 is connected to the fan casing 56. In the curved part of the blade 1, the leading edge 5 is concave while the trailing edge 6 is convex. We thus observe an axial deviation (or deformation) of the stacking line L. In particular, the blade 1 has a first portion whose stacking line L is substantially straight. This so-called straight stacking line is located in the lower part of the vane 1. The latter has an inclination downstream, in a plane containing the longitudinal axis X, with respect to the axis X. The inclination forms an angle a between 105 ° and 145 ° between the stacking line L and the axis X (the stacking line being oriented downstream).
    Similarly, according to Figure 4, a first portion of the trailing edge 6 extends along a straight line forming an angle β1 with the longitudinal axis. This is angle β1 is between 90 ° and 120 °, the trailing edge 6 being oriented downstream. This angle β1 varies from the longitudinal axis from upstream to downstream. The blade 1 also has a second portion where the stacking line L has the curvature or an elbow. The trailing edge 6 also has a curvature or bend on the second portion of the blade 1. In particular, the curvature of the trailing edge 6, in the upper part of the blade 1, is determined by an angle β1 formed between a tangent straight line T at the trailing edge 6 and the longitudinal axis X. In the present example, the angle β1 varies in the upper part of the blade 1. The upper part of the trailing edge having the curvature is situated between 50% and 95% of the height H of the blade 1 from the end of the blade tip. The angle β1 of curvature of the trailing edge 6 is between 75 ° and 90 °, the trailing edge being oriented upstream and the value of 90 ° not being included. In other words, the angle β1 between the longitudinal axis and the trailing edge 6 is substantially constant between 0 and 50% of the height of the blade. The angle β1 then varies between 50% and 95% of the height of the blade 1. Such a configuration makes it possible on the one hand, to reduce the overall dimensions and on the other hand, to maintain a predetermined minimum axial distance d close of the initial predetermined minimum axial distance of a conventional stator vane. The minimum axial distance is measured between the trailing edge 53 of the fan blade 51 and the leading edge 5 of the stator blade.
    The angles β1 presented by the trailing edge 6 relative to the longitudinal axis are shown in a graph in FIG. 6 in comparison with the angles of the trailing edge of the state of the art rectifier vanes. In this figure the angles of the trailing edge of the blades of the state of the art have an angle whose value is between 90 ° and 120 ° and is constant along the height of the blade (OGV10 and OGV12) , or whose value varies between 90 ° and 120 ° between 50% and 95% of the height of the blade (OGV11), or whose value is between 0 and 90 ° and is constant along the height of l 'dawn (OGV13). Conversely, the rectifier blade of the present invention has an angle whose value is constant and between 90 ° and 120 °, between 0 and 50% of the height of the blade, and whose value varies between 75 ° and 90 ° between 50% and 95% of the height of the dawn.
    In particular, at least two areas of variation of the angle at the trailing edge of the rectifier vane according to the invention must be distinguished. According to a mathematical representation with P a point belonging to the curve representing the height H of the rectifier vane 1 and in particular between 50% and 95% of the height H:
    - the first area of dawn 1 is: Height = [5%; P] where the value of β1 is greater than or equal to 90 °, and
    - the second area of dawn 1 is: Height = [P; 95%] where the value of β1 is strictly less than 90 °.
    We can thus see in FIG. 4, that the head end 4 of the stator vane 1 is connected to the fan casing 56 in a fixing zone further upstream from the fixing zone of a rectifier vane AR of the prior art shown in dotted lines. In other words, the head end 4 of the blade of the present invention is offset upstream due to the curvature. This offset and / or the curvature makes it possible to shorten the length, substantially along the longitudinal axis X, of the nacelle 101. The nacelle here has a length LN of between 3000 and 3800 mm taken between an upstream end 20 forming a lip of air inlet and a downstream end 21 forming a nozzle edge. Preferably, but not limited to, the length LN is between 3100 and 3500 mm. The gain in reduction of the length of the nacelle is, for example, between 5 and 15% compared to a standard turbomachine nacelle without the invention as it is shown in dotted lines in FIG. 4.
    More specifically, the arrangement of the blade 1 according to the invention allows the reduction of the length of the nacelle 101 without aggravating the noise pollution for the same given fan diameter. The gain in length makes it possible to reduce the aerodynamic drag of the turbomachine and / or the integration of larger surfaces of acoustic panels for equivalent drag as described below in the invention. The acoustic gain is approximately 2 EPNdB ("Effective Perceived Noise" in English or "effectively perceived noise level, in decibels").
    For the same given fan diameter, and with iso acoustic margin, the ratio of the length of the nacelle to the diameter of the fan (LN / DF) can be between -5% and -15% compared to a turbomachine without the invention, which implies a reduction in the length of the nacelle of between -5% and -15% compared to a turbomachine without the invention. In particular, the LN / DF ratio is for example between 1 and 3. Preferentially, but not limitatively, the ratio is between 2.1 and 2.8.
    The relative minimum axial distance between the fan blades and the stator vanes is determined by the relationship d / C. d is the minimum predetermined axial distance between the trailing edge 53 of the blower and the leading edge 5 of the stator vane 1. And C is the length of the axial chord of the blower. The axial chord C of the blower is measured between the leading edge 52 and the trailing edge 53 of the blower blade.
    The solution can also result in the following condition at
    respect: 50% H <H <95% H ^ c '100% H
    H corresponds to the outside radius of the rectifier blade 1 taken between the foot end and the head end of the blade 1. In other words, between 50% and 95% of the height H of the blade, the minimum relative axial distance between the fan 103 and the stator vane 1 is greater than the minimum relative axial distance measured at the head end of the vane, that is to say for 100% of the height H of l rectifier blade 1.
    According to yet another characteristic of the invention, it makes it possible to implement the following two conditions:
    > a ^ c '80% H ^ c '100% H
    With f-) <Ω.
    ^ c '100% H
    The parameter a corresponds to an efficiency factor. The parameter considered to be greater than 1.1 is defined as being a condition making it possible to guarantee the effectiveness of the invention. The parameter Ω is a parameter characterizing the condition Ω <3 to constrain the length of the nacelle and maintain the desired advantage in performance. In particular, we consider d the distance between the fan blade and the stator blade as a function of the height H (d (H)), the percentage of blade height 1 with 0% H (at dawn foot end 1) and 100% H (at the dawn head end 1). For each distance d considered between 50% and 95% of the height of the blade, it is greater than the distance d located at the head end of the blade 1 (100% H): d (r [ 50% -95%])> d (100%). This allows the stator blade to be brought closer to the fan blade at the foot and head end of blade 1 without impacting the distance of blade 1 on the height portion of the blade included. between 50% and 95% where the aeroacoustic phenomena are most intense. In other words, the spreading distance of the fan's wake as well as its dissipation are maximized and optimized.
    Since the length of the nacelle after the blades (between the head end of the vane 1 and the downstream end 21 of the nacelle) is not shortened, it is possible to envisage an acoustic treatment of the nacelle. Such acoustic treatment may include the provision of acoustic panels to further reduce noise. These acoustic panels are advantageously, but not limited to, arranged on an internal face of the nacelle 101 downstream of the stator vanes 1.
    According to an embodiment illustrated in FIG. 5, the shape of the blade 1 is characterized by the following relation:
    0.1 <
    L2
    - L1 '50% H <H <95% H <0.5.
    L2 corresponds to the minimum distance between the leading edge 5 of the rectifier blade 1 and the line A passing through the foot end and the head end of the blade taken at the leading edge 5. L1 corresponds to the length between this same line A and the trailing edge 6 of the rectifier vane. The lower (0.1) and upper (0.5) limits are determined so as to limit the maximum angle of inclination of the stacking line L at the foot end 3 of the stator vane 1 while limiting the curvature of the stacking line. We obtain a curvilinear shape allowing to limit the structural constraints (flexibility of the rectifier vane). This is a particular advantage for a slightly structural rectifier blade (which does not contribute to the suspension of the motor).
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Dawn (1) of turbomachine rectifier (100) double flow of longitudinal axis (X), the blade (1) comprising a plurality of blade section (2) stacked radially with respect to the axis (X) along a stacking line (L) between a foot end (3) and a head end (4), each blade section (2) comprising a lower surface (7) and a upper surface (8) extending axially between a leading edge (5) upstream and a trailing edge (6) downstream and being tangentially opposite, characterized in that between the leading edges (5) and trailing (6) from each blade section (2) is formed a profile cord (CA) of substantially constant length between the head end (4) and the foot end (3), and in that the line stack (L) has a curvature, in a plane passing substantially through the axis (X) and through the stack line (L), located near the head end (4) and oriented from downstream worm upstream.
    [2" id="c-fr-0002]
    2. Dawn (1) according to claim 1, characterized in that the curvature is located between 50% and 95% of the height of the blade (1) between the foot end (2) and the head end (4).
    [3" id="c-fr-0003]
    3. Dawn (1) according to one of the preceding claims, characterized in that the shape of the blade between 50% and 95% of the height of the blade is determined by the following relationship: 0.1 <(L2 / L1) n / a% h <h <95% h <0.5, with L2 corresponding to the minimum distance between the leading edge of the blade and a line (A) passing through the end of the foot and the head end of the blade, L1 corresponding to the length between this same line (A) and the trailing edge (6) of the blade, and H being the height of the blade.
    [4" id="c-fr-0004]
    4. Dawn (1) according to one of the preceding claims, characterized in that it has a first portion of the foot whose stacking line (L) extends along a straight line and a second portion of the head whose line stacking (L) includes curvature.
    [5" id="c-fr-0005]
    5. Dawn (1) according to any one of the preceding claims, characterized in that the leading edge (5) has a concave portion and the trailing edge (6) has a convex portion at the level of the curvature.
    [6" id="c-fr-0006]
    6. Assembly comprising a nacelle (101) of a double-flow turbomachine extending along a longitudinal axis (X) and a blower casing (56) secured to the nacelle, the blower casing (56) surrounding a blower (103) and delimiting downstream of the blower (103) an annular stream (55) in which an air flow circulates, characterized in that the blower casing (56) comprises an annular row of stator vanes (1) according to the any one of claims 1 to 5 arranged downstream of the fan blades (51) transversely in the annular vein (55).
    [7" id="c-fr-0007]
    7. Assembly according to the preceding claim, characterized in that the nacelle (101) has a length (LN) substantially along the longitudinal axis (X) and the fan (103) has a diameter (DF), substantially along the axis radial, the ratio (LN / DF) of the length of the nacelle to the diameter of the blower being between 1 and 3.
    [8" id="c-fr-0008]
    8. Assembly according to one of claims 6 and 7, characterized in that the relative axial distance between a fan blade (51) and a stator blade (1) is determined by the following condition: (d / C), with d being the predetermined minimum axial distance between a trailing edge (53) of the blower and the leading edge (5) of the stator vane (1), and C being the length of the axial chord of the fan blade (103), and in that the curvature of the stacking line (L) is determined by the following relation: (d / C) 50% h <h <95% h> (d / C) ioo % h, with H being the height of the stator blade between the head end (4) and the foot end (3).
    [9" id="c-fr-0009]
    9. Turbomachine (100) double flow, characterized in that it comprises at least one stator blade according to any one of claims 1 to 5 or an assembly according to any one of claims 6 to 8.
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    同族专利:
    公开号 | 公开日
    US20200355085A1|2020-11-12|
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    WO2019043330A1|2019-03-07|
    引用文献:
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    法律状态:
    2019-03-01| PLSC| Search report ready|Effective date: 20190301 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 4 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1757896A|FR3070448B1|2017-08-28|2017-08-28|TURBOMACHINE BLOWER RECTIFIER DRAWER, TURBOMACHINE ASSEMBLY COMPRISING SUCH A BLADE AND TURBOMACHINE EQUIPPED WITH SAID DAUTH OR DUDIT TOGETHER|
    FR1757896|2017-08-28|FR1757896A| FR3070448B1|2017-08-28|2017-08-28|TURBOMACHINE BLOWER RECTIFIER DRAWER, TURBOMACHINE ASSEMBLY COMPRISING SUCH A BLADE AND TURBOMACHINE EQUIPPED WITH SAID DAUTH OR DUDIT TOGETHER|
    CN201880059958.4A| CN111108262A|2017-08-28|2018-08-28|Turbomachine fan rectifier blade, turbomachine assembly comprising such a blade and turbomachine equipped with said blade or said assembly|
    PCT/FR2018/052114| WO2019043330A1|2017-08-28|2018-08-28|Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly|
    US16/642,150| US20200355085A1|2017-08-28|2018-08-28|Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly|
    EP18769761.0A| EP3676480A1|2017-08-28|2018-08-28|Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane, and turbomachine equipped with said vane or with said assembly|
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