• 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 present invention relates to a blade (25) of a turbomachine rectifier (23) of a height (H) extending between a blade root (26) and a blade head (27) in a radial direction ( Z), said blade (25) comprising a succession of five curved portions in a tangential direction (Y) perpendicular to the radial direction (Z), this succession of curved portions extending over the entire height (H) of the dawn (25), and the convexity of the successive curved portions being alternately in one direction and in the other. The blade (25) has the advantage of having a natural frequency for the first band vibration mode which is different from the biasing frequencies of said blade (25) during operation of the turbomachine.
    公开号:FR3043428A1
    申请号:FR1560771
    申请日:2015-11-10
    公开日:2017-05-12
    发明作者:Stephane Roger Mahias；Baptiste Batonnet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL FIELD
    The present invention relates to a stator vane of a turbomachine which is designed to limit the coincidences between the natural frequency of the vane and the first band vibration mode and the vane loading frequencies during the operation of the vane. the turbomachine.
    STATE OF THE ART
    In a conventional manner, the turbomachines with a double flow extend along a main axis and comprise an air shaft through which a flow of gas enters the turbomachine and in which the flow of gas passes through a fan. Downstream of the blower, the flow of gas separates into a flow of primary gas flowing in a primary stream and a flow of secondary gas flowing in a secondary vein.
    In the primary vein, the primary flow passes, from upstream to downstream, a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, a low pressure turbine, and a gas exhaust casing to which is connected an exhaust nozzle. In the secondary vein, the secondary flow passes through a fan rectifier and then mixes with the primary flow at the exhaust nozzle.
    Each compressor of the turbomachine comprises several stages, each stage being formed by a fixed blade or stator or rectifier, and a rotating blade or rotor around the main axis of the turbomachine. The rectifier and the rotor of a compressor stage each comprise a plurality of blades distributed regularly around the main axis of the turbomachine and extending radially with respect to this axis, inside the primary vein so as to be traversed by the primary flow.
    When the turbomachine is in operation, the blades of a compressor stator vibrate due to the flow of the primary flow along said vanes.
    However, the blades of the compressor rotor or rotors which are adjacent to the stator vanes generate, due to their rotation around the main axis of the turbomachine, harmonic excitations which when their frequency is too close to a natural frequency of the The blades of the rectifier cause too large amplitudes of vibration of the stator vanes which can lead to their deterioration or even to their rupture.
    It is known from the prior art the document FR 2 981 396 which describes a turbine engine compressor blade of radial principal orientation with respect to the main axis of the turbomachine, the blade having a radially internal portion of the foot, a radially outer portion of the head, a radially intermediate portion, a curved portion tangentially in one direction and at least a straight portion at the foot portion and / or at the head portion. The curved portion tangentially modifies the vibration response of the blade to vibrational stresses, and distances the eigenfrequencies of the blade from the biasing frequencies during operation of the turbomachine.
    However, such a blade geometry is not effective enough, when it is the first mode of vibration band or mode 2S1 (also called "stripe mode" according to the English terminology). Indeed, such a blade geometry does not sufficiently distance the eigenfrequencies of the blade with respect to the biasing frequencies with respect to the 2S1 mode.
    FIG. 1 shows a stator blade of a turbomachine compressor according to the prior art, in the static state (hatching) and in the state deformed according to the mode 2S1. It is observed in this figure that the nodal lines (In) mode 2S1 extend globally vertically over the entire height of the blade and therefore delimit bands, hence its name mode "strip".
    PRESENTATION OF THE INVENTION
    The present invention aims to provide a stator blade of a turbomachine which is made so that the natural frequency of the blade for the first band mode is different from the biasing frequencies of said blade, during operation of the turbine engine.
    More specifically, the subject of the present invention is a turbomachine stator blade, of a height extending between a blade root and a blade head in a radial direction, said blade comprising a succession of five curved portions according to a tangential direction perpendicular to the radial direction, this succession of curved portions extending over the entire height of the blade, and the convexity of the successive curved portions being alternately in one direction and the other.
    Preferably, the blade is defined by a plurality of sections stacked in said radial direction, each section being able to be defined on the one hand by a height in the radial direction from the root of the blade and on the other hand by a coordinate tangential positioning the center of gravity of said section in a tangential direction perpendicular to the radial direction, the curve of the stacking law which defines for each section, the tangential coordinate of the center of gravity of said section as a function of the height of that being a curve which is continuous from the foot to the head of the dawn and which satisfies at least the following conditions: - the curve is situated below a segment connecting the point of the curve corresponding to the section at foot of the dawn and the point of said curve which corresponds to the section at the head of the dawn, - the curve is convex between the height of section at the foot of the ube and a first section height which is strictly greater than the section height at the base of the blade, - the curve is concave between the first section height and a second section height which is strictly greater than the first section height - the curve is convex between the second section height and a third section height which is strictly greater than the second section height, 4 - the curve is concave between the third section height and a fourth section height which is strictly greater than the third section height, and - the curve is convex between the fourth section height which is strictly less than the section height at the head of the blade and the section height at the head of the blade.
    Advantageously, the tangential coordinate of the center of gravity is minimal for a fifth section height, said fifth section height being strictly greater than the second section height and strictly less than the third section height.
    Advantageously, the fifth section height substantially corresponds to the mid-height of the blade.
    Advantageously, the first, second, third and fourth section heights are distributed along the dawn between the section height at the foot of the blade and the section height at the head of the blade so as to form sections successive dawns of substantially equal height.
    According to a first aspect of the invention, the curve of the law of stacking of the sections of the blade: - is decreasing between the second height of section and a fifth height of section and increasing between the fifth height of section and the third section height, said fifth section height being strictly greater than the second section height and strictly less than the third section height, and / or - the curve is decreasing between the section height at the foot of the blade and a sixth section height and increasing between the sixth section height and the first section height, said sixth section height being strictly greater than the section height at the foot of the blade and strictly less than the first section height, and / or the curve is increasing between the first section height and a seventh section height and decreasing between the seventh section height and the first section height. a second section height, said seventh section height being strictly greater than the first section height and strictly less than the second section height, and / or - the curve is increasing between the third section height and an eighth section height and decreasing between the eighth section height and the fourth section height, said eighth section height being strictly greater than the third section height and strictly less than the fourth section height, and / or - the curve is decreasing between the fourth section height and section height and a ninth section height and increasing between the ninth section height and section height at the dawn head, said ninth section height being strictly greater than the fourth section height and strictly less than the height of section of section at the head of dawn.
    Preferably, the points of the curve corresponding to the fifth, sixth, seventh, eighth and ninth heights respectively form a third, a first, a second, a fourth and a fifth vertex of the said curve, and the shift in the tangential direction of each of the vertices of the curve with respect to a segment connecting, for each vertex, the point of the curve disposed midway between said vertex and the preceding vertex or when it is the first vertex, halfway between said first vertex vertex and the point of the curve corresponding to the section at the foot of the dawn, and the point of the curve disposed midway between said vertex and the next vertex or when it is the fifth vertex, half distance between said fifth vertex and the point of the curve corresponding to the section at the head of the blade, is substantially equal to 10% of the height at the head of the blade.
    According to a second aspect of the invention, the curve representative of the stacking law of the sections of the blade is decreasing between the section height at the foot of the blade and a fifth height of section and increasing between the fifth height of section and section height at the head of the blade, said fifth section height being strictly greater than the second section height and strictly less than the third section height. The invention also relates to a rectifier of a turbomachine comprising at least one blade as previously described. The rectifier is for example a compressor, turbine or fan rectifier of a turbomachine. The invention also relates to a turbomachine comprising at least one rectifier as previously described.
    PRESENTATION OF THE FIGURES Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings given as non-limiting examples and in which: FIG. already described) is a perspective view of a dawn of the prior art in a static state and in a deformed state according to the first band mode or 2S1 mode; - Figure 2 is a schematic view, in longitudinal section, of a turbomachine according to one embodiment of the invention; FIG. 3a is a perspective view of an example of a stator blade for a turbomachine compressor illustrated in FIG. 2, according to a first aspect of the invention; FIGS. 3b to 3d are each a perspective view of an example of a stator blade for a turbomachine compressor illustrated in FIG. 2, according to a second aspect of the invention; FIGS. 4a to 4d are graphs each illustrating a curve representative of the stacking law of a stator vane according to the invention; FIGS. 5a and 5b are graphs respectively illustrating a so-called convex curve and a so-called concave curve.
    DETAILED DESCRIPTION
    FIG. 2 illustrates a turbomachine with a double flow 10 according to one embodiment of the invention. The turbomachine 10 extends along a main axis 11 and comprises an air shaft 12 through which a flow of gas enters the turbine engine 10 and in which the flow of gas passes through a fan 13. Downstream of the fan 13, the gas flow separates into a flow of primary gas flowing in a primary stream 14 and a secondary gas stream flowing in a secondary vein 15.
    In the primary stream 14, the primary stream passes, from upstream to downstream, a low-pressure compressor 16, a high-pressure compressor 17, a combustion chamber 18, a high-pressure turbine 19, a low-pressure turbine 20, and a casing exhaust gas which is connected to an exhaust nozzle 22. In the secondary stream 15, the secondary flow passes through a fixed blade or fan rectifier 24, then mixes with the primary flow at the exhaust nozzle 22 .
    Each compressor 16, 17 of the turbomachine 10 comprises several stages, each stage being formed by a fixed blade or stator or rectifier 23, and a rotating blade or rotor around the main axis 11 of the turbomachine 10.
    A compressor rectifier 23 comprises an inner ferrule (not shown) extending around the main axis 11 of the turbomachine 10, an outer ferrule (not shown) arranged coaxially around the inner ferrule and delimiting with the outer ferrule the primary vein 14 and a plurality of blades extending radially relative to the main axis 11 of the turbomachine 10 between the inner ring and the outer ring.
    FIG. 3a shows an exemplary blade 25 for a compressor rectifier 23 according to a first aspect of the invention. Figures 3b and 3d each show an example of blade 25 for a compressor rectifier 23 according to a second aspect of the invention. In each of these figures, an example of a blade known from the prior art is also shown hatched.
    As illustrated in FIGS. 3a to 3d, the blade 25 has a spatial reference system with three orthogonal directions X, Y, Z, the direction X being parallel to the main axis 11 of the turbomachine 10 and the direction Z being radial relative to the main axis 11 of the turbomachine 10. In the remainder of the description, the direction X will be called "axial direction X", the direction Y will be called "tangential direction Y" and the direction Z will be called "radial direction Z ". The blade 25 extends along the radial direction Z between a radially inner portion 26, called the foot of the blade, at which the blade 25 is fixed to the inner shell, and a radially outer portion 27, called the dawn head, at which the blade 25 is attached to the outer shell. The blade 25 also comprises a leading edge 28 which is located axially upstream in the direction of flow of the gas with respect to the blade 25, and a trailing edge 29 which is located axially downstream in the direction of The blade 25 further has a camber defining on the one hand a generally convex face 30 called "extrados" and on the other hand a generally concave face 31 called "intrados". The blade 25 comprises a succession of five curved portions in the tangential direction Y, this succession of curved portions extending over the entire height H of the blade 25, and the convexity of the successive curved portions being alternately in one direction and in the other. the other.
    In other words, the blade 25 has, along the radial direction Z, a succession of five convex portions extending alternately towards the upper surface 30 and towards the lower surface 31 of the vane 25, and not a single convex portion towards the outside. extrados 30 as is the case of known blades.
    This succession of curved portions enables the eigenfrequency of the blade 25 to be moved away for the first mode of strip or mode 2S1 vibration (also called "stripe mode" according to the English terminology) of the biasing frequencies of said blade 25 during the operation of the turbomachine 10, thus reducing the risk of having excessive vibration amplitudes of the blade 25 which can lead to its deterioration or worse to break. The blade 25 is defined by a plurality of sections stacked in the radial direction Z between the blade root 26 and the blade head 27. Each section of the blade 25 is thus defined by a coordinate h in the radial direction Z, which will be called "height of section h" in the following description.
    Each of these sections is also defined by an axial coordinate Xg along the axial direction X and by a tangential coordinate Yg along the tangential direction Y of the center of gravity G of said section.
    The sections of the blade 25 are stacked according to a stacking law which defines the tangential coordinate Yg of the center of gravity G for each section of the blade 25 as a function of the height h of said section, between a height at the foot of the dawn ho and a height at the head of the dawn H. The law of stacking makes it possible to define the profile of the dawn 25.
    FIGS. 4a to 4d show several examples of curves Ci to C4 representative of the stacking law of the sections of a blade 25, and therefore of the profile of the blade 25, according to the invention, as well as a curve Co representative of a law for stacking sections of a blade according to the prior art. The curve Ci is representative of the stacking law of the sections of the blade 25 illustrated in FIG. 3a, while the curves C2 to C4 are respectively representative of the law of stacking of the sections of the blades 25 illustrated in FIGS. 3d. The dawn for which the curve Co is representative of the stacking law of the sections is shown hatched in FIGS. 3a to 3d. As a preliminary, it is defined that the representative curve of the stacking law of the sections of the blade 25 is convex between a height of section ha and a height of section hb, with ha <hb, when the curve is located below a segment [AB] connecting the point A of said curve corresponding to the height section ha and the point B of said curve corresponding to the height section hb. This definition is illustrated in Figure 5a.
    It is defined that the representative curve of the stacking law of the sections of the blade 25 is concave between a height of section ha and a height of section hb, with ha <hb, when the curve is situated above a segment [AB] connecting the point A of said curve corresponding to the height section ha and the point B of said curve corresponding to the height section hb. This definition is illustrated in Figure 5b.
    The curves Ci to C4 are continuous from the root 26 to the head 27 of the vane 25 and satisfy at least the following conditions: the curve Ci to C4 is situated beneath a segment [PT] connecting the point P of said curve corresponding to the foot section 26 of the blade and the point T of said curve corresponding to the section at the head 27 of the blade, - the curve Ci to C4 is convex between the section height at the foot of the blade h0 and a first section height hi (excluded), said first section height hi being strictly greater than the section height at the foot of the blade h0, - the curve Ci to C4 is concave between the first section height hi and a second height of section h2 (excluded), said second height of section h2 being strictly greater than the first height of section hi, - curve Ci to C4 is convex between the second height of section h2 and a third height of section h3 (excluded), said third high having a section h3 being strictly greater than the second height of section h2, the curve Ci to C4 is concave between the third height of section h3 and a fourth height of section ΙΊ4 (excluded), said fourth height of section ΙΊ4 being strictly greater. at the third height of section h3, and - the curve Ci to C4 is convex between the fourth height of section ΙΊ4 and the section height at the head of the blade H (excluded), said fourth height of section h4 being strictly lower at the section height at the head of dawn H.
    In this way, the blade 25 has along the radial direction Z a succession of five convex portions extending alternately towards the upper surface 30 and towards the lower surface 31 of the blade 25, thus making it possible to move the frequency of the vane 25 for the mode 2S1 of the biasing frequencies of said vane 25, during the operation of the turbomachine 10, and to reduce the risk of having too large vibration amplitudes of the vane 25 which can lead to its deterioration or worse at break.
    According to a first aspect of the invention, the curve representative of the stacking law of the sections of the blade 25 furthermore satisfies one or more of the following conditions: the curve is decreasing between the second height of section h2 and a fifth height of section h5 (excluded) and increasing between the fifth height of section hs and the third height of section h3 (excluded), said fifth height of section h5 being strictly greater than second height of section h2 and strictly lower than third height of section h3, and / or - the curve is decreasing between the section height at the foot of the blade h0 and a sixth section height h6 (excluded) and increasing between the sixth section height h0 and the first section height hi (excluded), said sixth height of section h0 being strictly greater than the section height at the foot of the blade h0 and strictly less than the first height of secti hi, and / or - the curve is increasing between the first height of section hi and a seventh height of section h7 (excluded) and decreasing between the seventh height of section h7 and the second height of section h2 (excluded), said seventh height of section h7 being strictly greater than the first height of section hi and strictly less than the second height of section h2, and / or - the curve is increasing between the third height of section h3 and an eighth height of section he (excluded) and decreasing between the eighth height of section he and the fourth height of section ΙΊ4 (excluded), said eighth height of section he being strictly greater than the third height of section h3 and strictly less than the fourth height of section h4, and / or the curve is decreasing between the fourth height of section h4 and a ninth height of section h9 (excluded) and increasing between the ninth height of sectio n h9 and the section height at the head of the blade H (excluded), said ninth height of section h9 being strictly greater than the fourth height of section h4 and strictly less than the section height at the head of the dawn H.
    The curve Ci illustrated in FIG. 4a verifies all these conditions.
    In this way, the curved portions of the blade 25 form waves whose apex is arranged perpendicular to the nodal lines of the mode 2S1 of the blade 25, which extend radially (FIG. 1), which makes it possible to move away from particularly effective manner the natural frequency of the blade 25 for the mode 2S1 of the biasing frequencies of said blade 25, during operation of the turbomachine 10.
    The points of the curve corresponding to the fifth, sixth, seventh, eighth and ninth heights h5, h6, h7, h8, h9 respectively form the third, first, second, fourth and fifth vertex S3, Si, S2, S4, S5 of said Ci curve.
    According to this first aspect of the invention, the shift δ, in the tangential direction Y of each of the vertices h,, h7, h5, h,, h9 of the curve with respect to a segment [MjNj] connecting, for each vertex Si , the point M, of the curve disposed midway between said vertex S, and the preceding vertex Sm or when it is the first vertex Si, halfway between said first vertex Si and the point P corresponding to the section at the foot of the blade 26, and the point N, of the curve disposed midway between said vertex S, and the apex Sj + i or when it is the fifth vertex S5, halfway between distance between said fifth vertex S5 and the point T corresponding to the section at the head of the blade 27, is substantially equal to 10% of the height at the top of the blade H. By "substantially equal" the fact that the offset δ, is equal to 10% of the height at the head of blade H to 5% error. For the sake of clarity, only the offset δ2 and the segment [M2N2] relative to the second vertex S2 are shown in FIG. 4a.
    According to a second aspect of the invention, the curve representative of the law of stacking sections of the blade 25 such that the curves C2, C3, C4 illustrated in FIGS. 4b and 4d, verifies the condition of which the curve is decreasing. between the section height at the foot of the blade h0 and a fifth height of section h5 (excluded) and increasing between the fifth height of section hs and the section height at the head of the blade H (excluded), said fifth section height h5 being strictly greater than the second height of section h2 and strictly less than the third height of section h3.
    The curved portions of the vane 25 according to this second aspect of the invention are particularly advantageous because they allow to distance the natural frequency of the vane 25 for the mode 2S1 of the biasing frequencies of said blade 25, during the operation of the turbomachine 10, without complicating the manufacture of the blade 25.
    It will be noted by comparing Figure 3a to Figures 3b to 3d that the curvature of the curved portions of the blade 25 are less marked according to this second aspect of the invention.
    Preferably, the fifth height of section hs corresponds substantially to the mid-height of the blade 25. The term "substantially at mid-height" means that the fifth height of section h5 corresponds to half the height of the blade. dawn 25 to 5% error.
    Preferably, the tangential coordinate Yg of the center of gravity G is minimal for the fifth height of section hs.
    Preferably, the first, second, third and fourth heights of section h-ι, h2, h3, and h4 are distributed along the blade between the section height at the foot of the blade h0 and the section height at the head of the blade H so as to form successive blade sections of substantially equal height. The term "substantially equal" means that the successive blade sections are of height equal to 5% error.
    Preferably, the tangential coordinate Yg of the center of gravity G is smaller for the height section at the foot of the blade h0 than for the section of height at the head of the blade H. The skilled person may for example obtain a curve Ci, C2, C3, C4 by implementing many well-known software for interpolating a curve from a finite number of points previously defined by the user and by which the interpolated curve must pass. These predefined points may for example be the tangential coordinate Yg of the center of gravity G at the section height at the foot of the blade h1, the first, second, third and fourth heights of section h-ι, h2, h3, h4 and the height of the section at the head of the dawn H. It is also possible to predefine the tangential coordinate Yg from the center of gravity G to the fifth height of section hs. The skilled person will know with the help of his general knowledge choose the number of points to predefine and define them so that the software interpolates a curve verifying the conditions described above. As a variant, the curve Ci, C2, C3, C4 can be interpolated by defining the tangential offset to be applied at several points of the curve Co representative of the stacking law of the sections of the blade according to the prior art.
    It will be noted that the curves Ci, C2, C3, C4 representative of the stacking law of the vane sections 25 according to the invention are defined in the description above by arbitrarily considering that the positive direction of the tangential direction Y extends from the upper surface 30 to the underside 31 of the vane 25, the curves C 1, C 2, C 3, C 4 being situated below the segment [PT]. It will therefore be understood that, conversely, considering that the direction positive of the tangential direction Y extends from the intrados 31 to the extrados 30 of the blade 25, the curves Ci, C2, C3, C4 will be located above the segment [PT] and the curvatures described below. above for the curves Ci, C2, C3, C4 will be reversed. For example, the curves Ci, C2, C3, C4 will be concave between the section height at the foot of the blade h0 and the first section height hi and no longer convex. Similarly, the tangential coordinate Yg of the center of gravity G will be maximum and no longer minimal for the fifth height of section hs and the tangential coordinate Yg of the center of gravity G will be larger and not smaller for the section of height at the foot of dawn h0 only for the section of height at the head of the dawn H. The skilled person will of course know how to adapt the content of the description according to the positive direction considered for the tangential direction Y.
    The present invention is described below with reference to a stator vane 25 of a turbine engine compressor 16, 17. However, the invention applies in the same way to stator vanes 32 of a turbine 19, 20 or fan blades 23, as these blades face the same technical problem due to the rotation of the rotor blades of the turbine 19, 20 or blades of the fan 13.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A blade (25) of turbomachine rectifier (23), of a height (H) extending between a blade root (26) and a blade head (27) in a radial direction (Z), said blade (25) being characterized in that it comprises a succession of five curved portions in a tangential direction (Y) perpendicular to the radial direction (Z), this succession of convex portions extending over the entire height (H) dawn (25), and the convexity of the successive curved portions being alternately in one direction and in the other.
    [2" id="c-fr-0002]
    2. blade (25) according to claim 1, defined by a plurality of sections stacked in the radial direction (Z), each section can be defined on the one hand by a height (h) in the radial direction (Z) from at the foot of the blade and on the other hand by a tangential coordinate (Yg) of the center of gravity (G) of said section along the tangential direction (Y), the curve of the stacking law which defines for each section, the tangential coordinate (Yg) of the center of gravity (G) of said section as a function of the height (h) thereof, being a curve (Ci, C2, C3, C4) which is continuous from the foot (26) to the head (27) of the blade (25) and which satisfies at least the following conditions: - the curve (Ci, C2, C3, C4) lies below a segment ([PT]) connecting the point ( P) of said curve which corresponds to the foot section (26) of the blade and the point (T) of said curve which corresponds to the section at the head (27) of the blade, - the curve e (Ci, C2, C3, C4) is convex between the section height at the root of the blade (h0) and a first section height (h-ι) which is strictly greater than the section height at the foot (26). ) of the dawn (h0), - the curve (Ci, C2, C3, C4) is concave between the first section height (hi) and a second section height (h2) which is strictly greater than the first height ( hi), - the curve (Ci, C2, C3, C4) is convex between the second section height (h2) and a third section height (h3), which is strictly greater than the second height (h2), - the curve (Ci, C2, C3, C4) is concave between the third section height (h3) and a fourth section height (h4), which is strictly greater than the third section height (h3), and - the curve ( Ci, C2, C3, C4) is convex between the fourth section height (h4) and the section height at the head of the blade (H), said fourth height (h4) being strictly inferior the section height to the tip of the blade (H).
    [3" id="c-fr-0003]
    3. blade (25) according to claim 2, wherein: the curve (Ci) of the law of stacking sections of the blade (25): - is decreasing between the second section height (h2) and a fifth section height (h5) and increasing between the fifth section height (h5) and the third section height (h3), said fifth section height (h5) being strictly greater than the second section height (h2) and strictly lower at the third height of section (ha), and / or - the curve (Ci) is decreasing between the section height at the foot of the blade (h0) and a sixth height of section (h6) and increasing between the sixth height of section (h6) and the first section height (h-ι), said sixth section height (h6) being strictly greater than the section height at the foot of the blade (h0) and strictly less than the first height of section (hi), and / or - the curve (Ci) is increasing between the first height of section (h-ι) and a seventh section height (h7) and decreasing between the seventh section height (h7) and the second section height (h2), said seventh section height (h7) being strictly greater than the first section height (h-ι) and strictly less than the second section height (ΙΊ2), and / or - the curve (Ci) is increasing between the third section height (ΙΊ3) and an eighth section height (h8) ) and decreasing between the eighth section height (h8) and the fourth section height (ΙΊ4), said eighth section height (h8) being strictly greater than the third section height (h3) and strictly less than the fourth height of section (ΙΊ4), and / or - the curve (Ci) is decreasing between the fourth section height (h4) and a ninth section height (h9) and increasing between the ninth section height (h9) and the section height at the head of dawn (H), the said ninth section height (h9) being strictly greater than the fourth section height (ΙΊ4) and strictly less than the section height at the head of the blade (H).
    [4" id="c-fr-0004]
    4. blade (25) according to claim 3, wherein the points of the curve corresponding to the fifth, sixth, seventh, eighth and ninth heights (h5, h6, h7, h8, h9) respectively form a third, a first, a second, a fourth and a fifth vertex (S3, Si, S2, S4, S5) of said curve, and wherein the shift (δ,) in the tangential direction (Y) of each of the vertices (S3, Si, S2, S4, S5) of the curve with respect to a segment ([MjNj]) connecting, for each vertex (Si), the point (Mj) of the curve disposed midway between said vertex (S,) and the preceding vertex (Sm) or when it is the first vertex (Si), midway between said first vertex (Si) and the point (P) of the curve corresponding to the foot section (26) of the dawn , and the point (Nj) of the curve disposed midway between said vertex (Si) and the next vertex (Sj + 1) or when it is the fifth vertex (S5), midway between said fifth ommet (S5) and the point (T) of the curve corresponding to the section at the head (27) of the blade, is substantially equal to 10% of the head height of the blade (H).
    [5" id="c-fr-0005]
    5. blade (25) according to claim 2, wherein the curve (C2, C3, C4) representative of the law of stacking sections of the blade (25) is decreasing between the height of section at the foot of the blade (h0) and a fifth section height (h5) and increasing between the fifth section height (h5) and the section height at the blade head (H), said fifth section height (h5) being strictly greater than the second section height (h2) and strictly less than the third section height (h3).
    [6" id="c-fr-0006]
    A blade (25) according to any one of claims 2 to 5, wherein the tangential coordinate (Yg) of the center of gravity (G) is minimal for a fifth section height (h5), said fifth section height ( h5) being strictly greater than the second section height (h2) and strictly less than the third section height (h3).
    [7" id="c-fr-0007]
    7. blade (25) according to any one of claims 3 to 6, wherein the fifth section height (h5) substantially corresponds to the mid-height of the blade (25).
    [8" id="c-fr-0008]
    8. blade (25) according to any one of claims 2 to 7, wherein the first, second, third and fourth section heights (h-ι, h2, h3, h4) are distributed along the blade ( 25) between the section height at the foot of the blade (h0) and the section height at the blade head (H) so as to form successive blade sections (25) of substantially equal height.
    [9" id="c-fr-0009]
    9. Rectifier (23, 24, 32) of a turbomachine comprising at least one blade (25) according to any one of claims 1 to 8.
    [10" id="c-fr-0010]
    10. Turbomachine (10) comprising at least one rectifier (23, 24, 32) according to claim 9.
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    同族专利:
    公开号 | 公开日
    GB2544414B|2020-07-08|
    GB2544414A|2017-05-17|
    US20170298746A1|2017-10-19|
    US10408070B2|2019-09-10|
    FR3043428B1|2020-05-29|
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    FR2981396A1|2011-10-13|2013-04-19|Snecma|TURBOMACHINE STATOR VANE COMPRISING A BOMBED PORTION|
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    法律状态:
    2016-11-09| PLFP| Fee payment|Year of fee payment: 2 |
    2017-05-12| PLSC| Publication of the preliminary search report|Effective date: 20170512 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1560771|2015-11-10|
    FR1560771A|FR3043428B1|2015-11-10|2015-11-10|TURBOMACHINE RECTIFIER DAWN|FR1560771A| FR3043428B1|2015-11-10|2015-11-10|TURBOMACHINE RECTIFIER DAWN|
    GB1618885.6A| GB2544414B|2015-11-10|2016-11-09|Turbine engine guide vane|
    US15/347,704| US10408070B2|2015-11-10|2016-11-09|Turbine engine guide vane|
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