• 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 turbine engine compressor blade, a thickness (EP) of which is defined in the blade section by the distance between a first point of the lower surface and a second point of the upper surface on a first segment perpendicular to the chord (AF), the thickness (EP) following a convex curve (CC) of thickness as a function of the percentage (PAF) of chord, the curve (CC) passing through a maximum thickness (Emax) for a determined value ( XEmax) of the percentage (PAF), characterized in that the thickness curve (CC) passes through an intermediate point (I) of upstream crowning, defined by the fact that: the percentage (IA) taken at the intermediate point (I) is between 5% and 25% and is less than the determined value (XEmax), the thickness (EPIA) taken at the intermediate point (I) is between 75% and 85% of the maximum thickness (Emax).
    公开号:BE1028097B1
    申请号:E20215105
    申请日:2021-02-17
    公开日:2022-01-26
    发明作者:Philippe Jacques Pierre Fessou；Michaël Franck Antoine Schvallinger；Damien Dufau
    申请人:Safran Aero Boosters；Safran Aircraft Engines；
    IPC主号:
    专利说明:

    Turbomachine Compressor Blade, Compressor and Turbomachine Fitted Therewith The invention relates to a turbomachine compressor blade, a turbomachine compressor and a turbomachine fitted with these blades.
    One field of application relates to aircraft turbojets or turboshaft engines, in particular airplanes.
    A turbomachine compressor blade comprises a plurality of blades arranged radially around a rotating central axis, forming a rotor. The compressor may be a low pressure compressor or a high pressure compressor of the turbomachine.
    Similar to aircraft wings, the compressor blades can be subjected to strong incidences and therefore undergo a phenomenon analogous to stall. At low flow, when the difference between the pressure at the inlet and that at the outlet of the compressor becomes too high, instabilities known as separations appear at the level of the blades. This aerodynamic stall causes a flow from the high pressure part to the low pressure part of the compressor and therefore a reversal of the direction of the flow. These large fluctuations in flow are called pumping because of the nature of this phenomenon of aerodynamic instability, which gives rise to longitudinal waves.
    The surge margin of the compressor is an element influencing the operability of the turbomachine. We therefore seek to have compressor blades that are robust with regard to the resistance to incidence in order to achieve the pumping margin objectives.
    On the other hand, in order to satisfy specifications of resistance to the penetration of foreign bodies into the compressor of the turbomachine, such as for example birds or hail, or specifications of sensitivity to erosion, it is sought to have robust blades with respect to these problems.
    Thus, the invention aims to obtain a turbomachine compressor blade, which makes it possible to improve the behavior at angle of attack, while controlling the performance of the blade.
    To this end, a first object of the invention is a turbomachine compressor blade, the blade comprising a blade root and a blade tip, remote from the blade root in a determined direction, at least one section blade perpendicular to the direction determined between the blade root and the blade tip,
    each blade section comprising a leading edge, a trailing edge, an underside, an upper surface, a chord defined by the distance between the leading edge and the trailing edge in the blade section, a thickness of the blade being defined in the blade section by the distance between a first point of the lower surface and a second point of the upper surface on a first segment perpendicular to the chord, the thickness of the blade following a convex curve in thickness as a function of the percentage of chord, the percentage of chord being the ratio of the length of a second segment connecting the leading edge to a point of intersection of the chord with the first segment, divided by the chord, the convex thickness curve passing through a maximum thickness for a given value of the percentage of chord, characterized in that the convex thickness curve passes through an intermediate point of upstream crowning of the blade, defined by the fact that: the percentage of chord taken at the intermediate point of bo upstream bulge is between 5% and 25% and is less than the determined value, the thickness taken at the intermediate point of upstream bulge is between 75% and 85% of the maximum thickness.
    According to one embodiment of the invention, the convex thickness curve varies according to the square root of the percentage of chord.
    According to one embodiment of the invention, the thickness taken at the intermediate point of upstream crowning is between 77% and 83% of the maximum thickness.
    According to one embodiment of the invention, the thickness taken at the intermediate point of upstream crowning is between 79% and 81% of the maximum thickness.
    According to one embodiment of the invention, the percentage of chord taken at the intermediate point of upstream crowning is between 10% and 20% of the chord.
    According to one embodiment of the invention, the percentage of chord taken at the intermediate point of upstream crowning is between 12% and 18% of the chord.
    According to one embodiment of the invention, the percentage of chord taken at the intermediate point of upstream crowning is between 14% and 16% of the chord.
    According to one embodiment of the invention, the determined value of the percentage of chord, which corresponds to the maximum thickness, is situated between 30% and 60% of the chord.
    According to one embodiment of the invention, the determined value of the percentage of chord, which corresponds to the maximum thickness, is situated between 40% and 50% of the chord.
    According to one embodiment of the invention, the determined value of the percentage of chord, which corresponds to the maximum thickness, is situated between 42% and 48% of the chord.
    According to one embodiment of the invention, the determined value of the percentage of chord, which corresponds to the maximum thickness, is situated between 44% and 46% of the chord.
    According to one embodiment of the invention, the convex thickness curve passes through a downstream point of slope discontinuity for which the percentage of chord is located between the determined value corresponding to the maximum thickness and a second value corresponding to the point intersection located more than 0.1 mm below the trailing edge.
    According to one embodiment of the invention, the convex thickness curve comprises a linear section on the chord percentage located between a third value greater than the determined value and a second value, which is less than 100% of the chord and which corresponds to the point of intersection located more than 0.1 mm below the trailing edge. A second object of the invention is a turbomachine compressor, comprising a plurality of blades as described above.
    A third object of the invention is a turbomachine, comprising at least one compressor as described above.
    The invention will be better understood on reading the following description, given solely by way of non-limiting example with reference to the figures below of the appended drawings.
    [Fig. 1] schematically represents in longitudinal section an example of a turbomachine in which the blade according to the invention can be used.
    [Fig. 2] represents the thickness of the blade according to one embodiment of the invention.
    [Fig. 3] schematically represents a partial sectional view of the blade in a blade section according to one embodiment of the invention.
    [Fig. 4] represents the compression ratio of a compressor equipped with blades according to the invention.
    [Fig. 5] represents the losses of a compressor fitted with blades according to the invention.
    [Fig. 6] represents the rate of erosion of a compressor fitted with blades according to the invention. [Fig. 7] schematically represents a sectional view of the blade in a blade section according to the invention.
    An example of a turbomachine 1 on which the compressor blade(s) 100 according to the invention can be used is described below in more detail with reference to FIG.
    As is known, the turbomachine 1 represented in FIG. 1 is intended to be installed on an aircraft, not represented, in order to propel it in the air.
    The gas turbine engine or turbomachine assembly 1 extends around an axis AX or axial direction AX oriented from upstream to downstream. Thereafter, the terms "upstream", respectively "downstream" or "front", respectively "rear", or "left" respectively "right" are taken along the general direction of the gases which flow in the turbomachine according to the AX axis. The direction going from inside to outside is the radial direction DR starting from the axis AX. The term axially designates a direction along the axis AX. An axial plane is a plane containing the axis AX. A direction located in a plane transverse to the AX axis is called the transverse direction.
    The turbomachine 1 is for example double body. The turbomachine 1 includes a first stage 2 and a central gas turbine engine 130. In Figure 1, the first stage 28 is a fan assembly. Of course, the first stage 28 could also be a fixed stage (without a fan). The central gas turbine engine 130 comprises, from upstream to downstream in the direction of gas flow, a low pressure compressor CBP1, a high pressure compressor CHP1, a combustion chamber 160, a high pressure turbine THP1 and a low pressure turbine TBP1, which delimit a primary flow of gas FPI. The fan assembly 28 includes a set of rotating fan blades 280 extending radially outward from a rotating hub 250 (or a set of fixed blades extending radially outward from a hub for a central portion in the case where the first stage 28 is fixed). The turbomachine 1 has an upstream inlet end 29 and a downstream exhaust end 31. The turbomachine 1 also comprises an inter-stream casing 36 which delimits a primary stream in which circulates the primary flow FP1 which passes through the low-pressure compressor CBP1 , the high pressure compressor CHP1, the high pressure turbine THP1 and the low pressure turbine TBP1.
    The inter-vein casing 36 comprises, from upstream to downstream, a casing 361 of the low pressure compressor CBP1, an intermediate casing 260, which is interposed between the low pressure compressor CBP1 and the high pressure compressor CHP1, a casing 362 of the high pressure compressor CHP1, a casing 363 of the high pressure turbine THP1 and a casing 19 of the low pressure turbine TBP1.
    The CBP1 low-pressure compressor and the CHP1 high-pressure compressor can each comprise one or more stages, each stage being formed by a set of fixed vanes (or stator blading) and a set of rotating vanes (or rotor blading).
    The fixed vanes 101 of the low pressure compressor CBP1 are fixed to the casing 361. The rotating vanes 102 of the low pressure compressor CBP1 are fixed to a first rotary shaft 9 of the transmission.
    The fixed blades 103 of the high pressure compressor CHP1 are fixed to the casing 362. The rotating blades 104 of the high pressure compressor CHP1 are fixed to a second rotary shaft 10 of transmission.
    The high pressure turbine THP1 and the low pressure turbine TBP1 can each comprise one or more stages, each stage being formed by a set of fixed vanes (or stator blading) and a set of rotating vanes (or rotor blading).
    The stationary blades 105 of the high pressure turbine THP1 are fixed to the casing 363.
    The rotating vanes 106 of the high pressure turbine THP1 are fixed to the second rotating shaft 10 of the transmission.
    The fixed vanes 107 of the low pressure turbine TBP1 are fixed to the casing 19. The rotating vanes 108 of the low pressure turbine TBP1 are fixed to the first rotary shaft 9 of the transmission.
    The rotating blades 108 of the low pressure turbine TBP1 drive the rotating blades 102 of the low pressure compressor CBP1 in rotation around the axis AX under the effect of the thrust of the gases coming from the combustion chamber 160. The rotating blades 106 of the high pressure turbine THP1 drive the rotating blades 104 of the high pressure compressor CHP1 in rotation around the axis AX under the effect of the thrust of the gases coming from the combustion chamber 160.
    In operation, the air flows through the first stage 28 and a first part FP1 (primary flow FP1) of the air flow is routed through the low pressure compressor CBP1 and the high pressure compressor CHP1, in which the flow of air is compressed and sent to the combustion chamber 160. The hot combustion products (not shown in the figures) coming from the combustion chamber 160 are used to drive the turbines THP1 and TBP1 and thus produce the thrust of the turbomachine 1. The turbomachine 1 also comprises a secondary stream 39 which is used to pass a secondary flow FS1 of the flow of air evacuated from the first stage 28 around the inter-vein casing 36. More precisely, the secondary stream 39 extends between an inner wall 201 of a fairing 30 or nacelle 30 and the inter-vein casing 36 surrounding the central gas turbine engine 130. Arms 34 connect the intermediate casing 260 to the inner wall 201 of the fairing 30 in the secondary 39 of the FS1 secondary stream.
    Below, the blade 100 according to the invention can be one, several or all of the rotary blades described above and/or one, several or all of the blades of one or more or all of the compressors. For example, the blade 100 according to the invention can be one, several or all of the rotary blades 102 of the low pressure compressor CBP1 and/or one, several or all of the rotary blades 104 of the high pressure compressor CHPI.
    Below, the blade 100 according to the invention is described below with reference to Figures 2 and 3. In Figures 1, 3 and 7, the blade 100 has a leading edge A and a trailing edge F , which are spaced apart at least in the axial direction AX. The leading A edge is intended to face upstream relative to the airflow, while the trailing F edge is intended to face downstream relative to the airflow. The leading edge A therefore extends at least in one direction or the other of the radial direction DR along a determined line between a blade root 109 fixed to a part of the turbomachine and a blade head 110 (Free end of the blade 100) farther from this part than the root 109 of the blade. The blade tip 110 is distant from the blade root 109 in a determined direction, for example along the radial direction DR. The blade section or sections SA are taken perpendicular to the determined direction or to the radial direction DR between the root 109 of the blade and the tip 110 of the blade. The blade 100 comprises an intrados IN (or first surface IN) and an extrados EX (or second surface EX), which are delimited by the leading edge A and the trailing edge F. When the blade 100 is rotated in the turbine engine 1, the direction of rotation of the blade 100 in normal operation is such that the blade 100 moves in the direction of its lower surface IN. The blade 100 has a thickness EP determined between its lower surface IN and its upper surface EX, as described below. The thickness EP of the blade 100 is variable in the blade section SA depending on the position on the chord AF between the leading edge A and the trailing edge F. In the following, the geometry is defined in the SA blade section.
    There may be several different blade sections SA (i.e. taken in planes distant from each other and perpendicular to the determined direction or to the direction DR) having curves CC of thickness according to the invention, for example over part of the height of the blade 100 between the root 109 of the blade and the tip 110 of the blade along this determined direction or direction DR, or over this entire height.
    One can have different thickness CC curves and different AF chords in different blade SA sections.
    The AF chord is defined by the predetermined distance between the leading edge A and the trailing edge F in the blade section SA.
    A (second) segment AH of the chord AH is defined between the leading edge A and a point H located between the leading edge A and the trailing edge F.
    The position of the H point on the AF chord is defined by a Par percentage of chord, which is equal to the distance between the leading edge A and the H point in the SA blade section, divided by the AF chord in this same section SA of dawn.
    This percentage Par of rope therefore goes from 0% (at the leading edge A) to 100% (at the trailing edge F). Thickness EP of blade 100 is perpendicular to the chord at point H in blade section SA.
    For each percentage Par of chord, the thickness EP of the blade 100 is therefore defined in the section SA of the blade by the distance between a first point C of the lower surface IN and a second point D of the upper surface EX on the first segment CD, whose extremities are these first and second points C and D, which is perpendicular to the chord AF and which passes through the point H, the point H being the point of intersection between the first segment CD and the chord AF.
    In FIG. 2, the thickness EP of the blade 100 follows a convex curve CC of thickness as a function of the percentage Par of chord ranging from 0% to 100% in the section SA of the blade.
    The thickness value 0 indicated in figure 2 corresponds to a zero thickness EP for the points C and D located respectively on the leading edge A and on the trailing edge F.
    FIG. 2 is an illustrative diagram, the scale of values of the horizontal axis of the percentage Par of chord and the scale of values of the vertical axis of the thickness EP not being respected in FIG. 2. convex curve CC of the thickness EP passes through a maximum MAX having a maximum thickness Emax taken when the percentage Par of chord has a determined value XEmax, which is situated between 0% and 100% of the chord AF.
    The maximum thickness Emax taken at the determined value XEmax OR the maximum MAX is also called master torque.
    The convex thickness curve CC passes through an intermediate point I of upstream crowning of the blade 100, which is located upstream of the maximum thickness Emax and for which the percentage Par of chord has an intermediate value IA of upstream crowning included between 5% and 25% of the chord AF and the thickness EP has an intermediate value EPia of upstream bulge thickness of between 75% and 85% of the maximum thickness Emax.
    The intermediate value IA of upstream bulge is greater than 0 and is less than the determined value XEmax.
    The intermediate value EPia of the upstream bulge thickness is greater than 0 and is less than the maximum thickness Emax.
    Due to the characteristics of the intermediate point I of upstream crowning of the blade 100, the convex curve CC of thickness has, as shown in FIG. 2, a pronounced crowning at the level of this intermediate point I upstream of the thickness maximum Emax.
    Thus, in FIG. 2, the thickness EP of the blade 100 along the curve CC has a higher value than a standard thickness curve ST in the zone located between the leading edge A and the maximum thickness Max.
    Figure 3 shows that the intrados IN and the extrados EX of the blade 100 according to the invention are more rounded than the blade Ast corresponding to the standard thickness curve ST starting from the leading edge A.
    This makes it possible to have an opening angle 92 between the first segment CA (segment CA joining points C and A) and the second segment DA (segment DA joining points D and A) of the blade 100 according to the invention , greater than the opening angle θ1 between the first segment CA and the second segment DA of the blade AST corresponding to the standard thickness curve ST, for the same percentage Par of chord (for example percentage Par of chord 5% shown in Figure 3). This makes it possible to obtain a more pronounced profile opening angle 92 of the blade 100 and thus to be more tolerant of the incidence between the leading edge A and the maximum thickness Emax.
    On the other hand, it also makes it possible to have leading edges A that are more tolerant to impacts and erosion.
    Indeed, the erosion rate is proportional to the thickness EP of the profile.
    Therefore, the thicker the profile, the less 1l is susceptible to erosion and the longer its life.
    FIG. 4 shows on the ordinate the measured curve TC100 of the compression rate of the aforementioned compressor, one or more blades of which are formed from the blades 100 according to the invention, as a function of the flow rate of this compressor on the abscissa, and the measured curve TCST of the rate compression of the aforementioned compressor, all the blades of which are formed from standard AsrT blades as a function of the flow rate of this compressor on the abscissa.
    The TC100 curve shows that thanks to the blade 100 according to the invention, the compression rate of the TC100 curve of the blades 100 according to the invention is greater at low flow rates below the pumping LP line than the compression rate of the TCST curve of the standard AsT blades, which shows that the blade 100 according to the invention has a better pumping margin than the standard Asr blade.
    FIG. 5 represents on the ordinate the measured loss curve P100 of the aforementioned compressor of FIG. 4, one or more blades of which are formed from the blades 100 according to the invention, as a function of the incidence of this compressor on the abscissa, and the curve PST measured losses of the aforementioned compressor, all the blades of which are formed from standard Asr blades as a function of the incidence of this compressor on the abscissa. FIG. 5 shows that at equal incidence, the losses of the P100 curve of the blade 100 according to the invention are reduced compared to the losses of the PST curve of the standard blade, and that for a given value of the losses, the range of incidence at losses smaller than this value is widened compared to the losses of the PST curve of the standard blade.
    FIG. 6 represents in ordinates the measured curve T100 of the rate of erosion of the aforementioned compressor of FIG. abscissa, and the measured curve TST of erosion rate of the aforementioned compressor, all the blades of which are formed from standard Asr blades as a function of the number of operating cycles of these blades in abscissa. FIG. 6 shows that the erosion rate of the T100 curve of the blade 100 according to the invention is reduced compared to the erosion rate of the TST curve of the standard blade and that consequently the service life of the blade 100 according to the invention is larger than that of the standard blade.
    In one embodiment of the invention, the intermediate value IA of upstream crowning of the percentage Par of chord, taken at the intermediate point I of upstream crowning and comprised between 5% and 25% of the chord AF, and the intermediate value EPia d the upstream crown thickness at the intermediate point I of upstream crown between 75% and 85% of the maximum thickness Emax are combined with the determined value XEmax, which corresponds to the maximum thickness Emax, located between 30% and 60% of the AF rope.
    According to one embodiment of the invention, the intermediate value EPra of upstream crown thickness at the intermediate point I of upstream crown is between 77% and 83% of the maximum thickness Emax, for example between 79% and 81% of the maximum thickness Emax. In an exemplary embodiment of the invention, the intermediate value EPia of the upstream bulge thickness at the intermediate point I of the upstream bulge is equal to 80% of the maximum thickness Emax. According to one embodiment of the invention, the intermediate value IA of upstream crowning of the percentage Par of chord, taken at the intermediate point I of upstream crowning, is between 10% and 20% of the chord AF, in particular between 12% and 18% of the AF chord, and in particular between 14% and 16% of the AF chord. In an exemplary embodiment of the invention, the intermediate value IA of chord of upstream crowning of the percentage Par of chord, taken at the intermediate point I of upstream crowning, is equal to 15% of the chord AF.
    Of course, any of the ranges indicated above of the intermediate value IA of the upstream crown can be combined with any of the ranges indicated above of the intermediate value EPra of the thickness of the upstream crown.
    According to one embodiment of the invention, both the intermediate value EPra of upstream crown thickness at the intermediate point I of upstream crown is between 77% and 83% of the maximum thickness Emax and the intermediate value IA of upstream crown of the percentage Par of chord, taken at intermediate point I of upstream crown, is between 12% and 18% of the chord AF.
    According to one embodiment of the invention, both the intermediate value EPra of upstream crown thickness at the intermediate point I of upstream crown is between 79% and 81% of the maximum thickness Emax and the intermediate value IA of upstream crown of the percentage Par of chord, taken at intermediate point I of upstream crown, is between 14% and 16% of the chord AF.
    According to one embodiment of the invention, the determined value XEmax of the percentage Par of chord, which corresponds to the maximum thickness Emax, is situated between 40% and 50% of the chord AF, in particular between 42% and 48% of the AF chord, in particular between 44% and 46% of the AF chord.
    Of course, any of the ranges indicated above of the determined value XEmax of the percentage Par of cord, which corresponds to the maximum thickness Emax, can be combined with any of the ranges indicated above of the value intermediate value IA of upstream crown and at any one of the ranges indicated above of the intermediate value EP of thickness of upstream crown.
    In a first exemplary embodiment of the invention, the intermediate value EP;A of the upstream crowning thickness at the intermediate point I of the upstream crowning is equal to 80% of the maximum thickness Emax, the intermediate value IA of the upstream crowning of the percentage Par of chord, taken at the intermediate point I of the upstream crown, is equal to 15% of the chord AF and the determined value XEmax of the percentage Par of chord A, which corresponds to the maximum thickness Emax, is equal to 45% of the AF rope. In a second embodiment of the invention, XEmax = 60% and IA = 25%. In a third embodiment of the invention, XEmax=30% and IA=5%. Thus, in FIG. 2, the thickness curve CC of the blade 100 according to the invention may be above the standard thickness curve ST in the zone located between the leading edge A and the thickness maximum Emax. Thus, the thickness EP of the blade 100 along the curve CC can present a higher value than the standard thickness curve ST in the zone located between the leading edge A and the maximum thickness Emax. Figure 3 shows that the intrados IN and the extrados EX of the blade 100 according to the invention can be more rounded than the blade Ast corresponding to the standard ST curve of thickness starting from the leading edge A. This makes it possible to have an opening angle 92 between the first straight line CA passing through the leading edge and the first point C and the second straight line DA passing through the leading edge and the second point D of the blade 100 according to the invention, greater than the angle 1 of opening between the first straight line CA and the second straight line DA of the blade Ast corresponding to the standard thickness curve ST, for the same percentage Par of chord (for example ratio of 5% represented in FIG. 3) between the leading edge A and the maximum thickness Emax.
    According to one embodiment of the invention, the convex thickness curve CC varies according to the square root of the percentage Par of chord.
    According to one embodiment of the invention, the convex thickness curve CC passes through a downstream point PINF of slope discontinuity located more than 0.1 mm below the trailing edge F. The downstream point PINF of slope discontinuity corresponds to a percentage Par of chord located between the determined value XEmax corresponding to the maximum thickness Emax and a second value corresponding to the point H of intersection located more than 0.1 mm below the edge F leak. Upstream (on the left in figure 2) of this point PINF, the thickness curve CC has an upstream slope different from the downstream slope taken downstream (on the right in figure 2) of this point PINF.
    According to one embodiment of the invention, the convex thickness curve CC comprises a linear section TL between the determined value XEmax corresponding to the maximum thickness Emax and a point located below the trailing edge F, for example between the determined value XEmax corresponding to the maximum thickness Emax and a second value, which corresponds to the point H of intersection located more than 0.1 mm below the trailing edge F or between the determined value XEmax corresponding to the maximum thickness Emax and the downstream point PINF of slope discontinuity. This has the advantage of controlling the diffusion and thus of minimizing the flux-profile deviations. This linear section of the curve CC can for example extend over a range of the percentage Par of chord making more than 50% of the downstream range going from the determined value Xemax to 100% of the chord AF.
    Of course, the embodiments, characteristics, possibilities and examples described above can be combined with each other or selected independently of each other.
    权利要求:
    Claims (14)
    [1]
    1. Turbomachine compressor blade (100), the blade (100) comprising a blade root (109) and a blade tip (110), remote from the blade root (109) in a determined direction, at least one blade section (SA) perpendicular to the direction determined between the blade root (109) and the blade tip (110), each blade section (SA) comprising an edge (A) of attack, a trailing edge (F), an intrados (IN), an extrados (EX), a chord (AF) defined by the distance between the leading edge (A) and the trailing edge (F) in the blade section (SA), a thickness (EP) of the blade (100) being defined in the blade section (SA) by the distance between a first point (C) of the lower surface (IN) and a second point (D) of the upper surface (EX) on a first segment (CD) perpendicular to the chord (AF), the thickness (EP) of the blade (100) following a convex curve (CC) of thickness as a function of the percentage (Par) of chord, the percentage (Par) of chord being the ratio of the length of a second segment (AH) connecting the leading edge (A) to a point (H) of intersection of the chord with the first segment (CD), divided by the chord (AF), the convex curve (CC) of thickness passing through a thickness maximum (Emax) for a determined value (XEmax) of the percentage (Par) of chord, characterized in that the convex thickness curve (CC) passes through an intermediate point (I) of the upstream crown of the blade (100) , defined by the fact that: the percentage (IA) of chord taken at the intermediate point (T) of upstream crowning is between 5% and 25% and is less than the determined value (XEmax), the thickness (EPia) taken at the intermediate point (I) of upstream bulge is between 75% and 85% of the maximum thickness (Emax), the convex curve (CC) of thickness varies according to the square root of the percentage (Par) of chord.
    [2]
    2. Turbomachine compressor blade (100) according to claim 1, characterized in that the thickness (EP) taken at the intermediate point (I) of upstream crowning is between 77% and 83% of the maximum thickness (Emax ).
    [3]
    3. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the thickness (EP) taken at the intermediate point (I) of upstream crowning is between 79% and 81% of the maximum thickness (Emax).
    [4]
    4. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the percentage (IA) of chord taken at the intermediate point (I) of upstream crowning is between 10% and 20% of the rope (AF).
    [5]
    5. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the percentage (IA) of chord taken at the intermediate point (I) of upstream crowning is between 12% and 18% of the rope (AF).
    [6]
    6. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the percentage (IA) of chord taken at the intermediate point (I) of upstream crowning is between 14% and 16% of the rope (AF).
    [7]
    7. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the determined value (XEmax) of the percentage (Par) of chord, which corresponds to the maximum thickness (Emax), is located between 30% and 60% of the chord (AF).
    [8]
    8. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the determined value (XEmax) of the percentage (Par) of chord, which corresponds to the maximum thickness (Emax), is located between 40% and 50% of the chord (AF).
    [9]
    9. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the determined value (XEmax) of the percentage (Par) of chord, which corresponds to the maximum thickness (Emax), is located between 42% and 48% of the chord (AF).
    [10]
    10. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the determined value (XEmax) of the percentage (Par) of chord, which corresponds to the maximum thickness (Emax), is located between 44% and 46% of the chord (AF).
    [11]
    11. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the convex thickness curve (CC) passes through a downstream point (PINF) of slope discontinuity for which the percentage (Par ) of chord is located between the determined value (XEmax) corresponding to the maximum thickness
    (Emax) and a second value corresponding to the intersection point located more than 0.1 mm below the trailing edge (F).
    [12]
    12. Turbomachine compressor blade (100) according to any one of the preceding claims, characterized in that the convex curve (CC) of thickness comprises a linear section (TL) on the percentage (Par) of chord located between a third value greater than the determined value (XEmax) and a second value, which is less than 100% of the chord and which corresponds to the point (H) of intersection located more than
    0.1 mm below the trailing edge (F).
    [13]
    13. Turbomachine compressor (CBP1, CHP1), comprising a plurality of blades (100) according to any one of the preceding claims.
    [14]
    14. Turbomachine (1), comprising at least one compressor (CBP1, CHP1) according to claim 13.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP1693572B1|2015-11-04|Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine
    FR3027053B1|2019-09-13|AIRCRAFT TURBOMACHINE STATOR
    FR3070448B1|2019-09-06|TURBOMACHINE BLOWER RECTIFIER DRAWER, TURBOMACHINE ASSEMBLY COMPRISING SUCH A BLADE AND TURBOMACHINE EQUIPPED WITH SAID DAUTH OR DUDIT TOGETHER
    EP3033530B1|2018-05-09|Turbomachine stator vane
    CA2975570A1|2016-08-18|Guide assembly with optimised aerodynamic performance
    EP2855847B1|2018-07-18|Fan blade for a turbojet of an aircraft having a cambered profile in the foot sections
    FR3032480A1|2016-08-12|AIR RECOVERY ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE
    FR2926856A1|2009-07-31|TURBOREACTOR COMPRESSOR
    FR2939852A1|2010-06-18|Stator blade stage for compressor of turboshaft engine e.g. turbopropeller engine, has intermediate blades with axial length or radial height less than that of rectifier blades and extend radially between rectifier blades
    FR2946399A1|2010-12-10|CENTRIFUGAL COMPRESSOR WHEEL.
    BE1028097B1|2022-01-26|Turbomachine compressor blade, compressor and turbomachine fitted therewith
    EP2582986B1|2016-07-13|Aerodynamic coupling between two annular rows of stationary vanes in a turbine engine
    FR3089576A1|2020-06-12|Centrifugal impeller
    FR3081185A1|2019-11-22|STATOR ELEMENT OF TURBOMACHINE
    FR3068735B1|2019-07-26|TURBOREACTOR WITH LOW NOISE OF BLOW
    FR3090033A1|2020-06-19|DAWN DIRECTION AND BIFURCATION DIRECTOR SET FOR TURBOMACHINE
    FR3027354B1|2019-09-06|AUBES WHEEL COMPRISING DRILLING BETWEEN THE INTRADOS AND THE EXTRADOS OF THE DAWN AND ASSOCIATED MOTOR
    FR3074847A1|2019-06-14|BLOWER MODULE
    FR3092868A1|2020-08-21|Turbomachine stator wheel comprising blades with different chords
    FR3104644A1|2021-06-18|Aeronautical propulsion system with improved propulsive efficiency
    WO2021116621A1|2021-06-17|Aero-propulsion system with improved propulsion efficiency
    FR3050759A1|2017-11-03|AIR FLOW AND TURBOMACHINE RECOVERY ASSEMBLY COMPRISING SUCH AN ASSEMBLY
    FR3099518A1|2021-02-05|Rectifier assembly for a turbomachine compressor
    FR3100268A1|2021-03-05|DOUBLE-FLOW TURBOMACHINE FOR AN AIRCRAFT
    WO2021250339A1|2021-12-16|Turbomachine comprising a member for separating a flow of air and a member for straightening the separated flow of air
    同族专利:
    公开号 | 公开日
    BE1028097A1|2021-09-20|
    FR3108141A1|2021-09-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1338799A1|1997-06-24|2003-08-27|Siemens Aktiengesellschaft|Compressor blade|
    EP1754859A2|2005-08-16|2007-02-21|General Electric Company|Methods and apparatus for reducing vibrations induced to airfoils|
    EP2360377A2|2010-02-24|2011-08-24|Rolls-Royce plc|A compressor aerofoil|
    EP2410130A2|2010-07-19|2012-01-25|Rolls-Royce Deutschland Ltd & Co KG|Fan outlet guide vanes of a turbofan engine|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    FR2002353A|FR3108141A1|2020-03-10|2020-03-10|Turbomachine compressor blade, compressor and turbomachine fitted therewith|
    [返回顶部]