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    • 专利摘要:
    Variable timing bladed wheel comprising: - a plurality of blades (2), each of variable pitch along an axis of blade rotation and each having a foot, the plurality of blades comprising at least a first blade (21) and at least one second blade (22); - a plurality of rotor connecting shafts, each shaft having a foot and a head, the foot of each blade (2) being mounted on the head of a corresponding rotor connecting shaft by intermediate a pivot so as to allow the rotation of each blade along the axis of blade rotation, the first blade (21) having a first inclination axis of rotation, such that its axis of rotation is inclined fixed relative to a radial axis passing through the foot of the corresponding shaft, and the second blade has a second inclination of axis of rotation different from the first inclination of the axis of rotation
    公开号:FR3025246A1
    申请号:FR1458125
    申请日:2014-08-29
    公开日:2016-03-04
    发明作者:Clement Marcel Maurice Dejeu；Jonathan Evert Vlastuin；Mathieu Simon Paul Gruber
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to a variable-pitch bladed wheel, and to a turbomachine comprising such a bladed wheel. State of the art Turbomachine bladed wheels comprising at least one rotor and blades with variable geometric pitch are known from the state of the art. In the case of propeller engines comprising one or more propellers, each propeller comprises a plurality of blades of a bladed wheel, the blades being arranged circumferentially at the periphery of the bladed wheel, the blades having the same geometrical configuration around the blade. axis of the turbomachine or axis of the propeller, the blades being rotated by the rotor about this axis. The variable pitch blade system makes it possible to modify the pitch of all the blades in an identical manner so as to adapt the aerodynamic operation of the blades of the propeller to the variation of the flight conditions. This variation can result either from a change of point of flight torque (z altitude, Mn Mach) or rotational speed of the propellers.
    [0002] The propeller engine is for example a turboprop engine. It may also be a motor of the fanless type (in English "open rotor" or "unducted fan"), typically non-ducted fan and contra-rotating propellers (in English "contra rotative open rotor"). A turbomachine of this type typically comprises two coaxial external helices corresponding to two bladed wheels, respectively upstream and downstream, at least one of which is rotated and which extend substantially radially outwardly of the engine nacelle. this turbomachine, so as to have different rotational speeds, for example, only one of the propellers can be driven, or the propellers can be counter-rotating.The geometric setting is typically the angle formed by the rope of the profile of the blade and the plane of rotation of the helix, defined as the plane orthogonal to the axis of rotation of the propeller of the bladed wheel.For this purpose, as illustrated in FIG. t a rotor 10 comprising for each blade 2 of the propeller a radial shaft 6, a head 601 is connected to the blade 2 by a pivot 8 in which a foot of the blade 201 is housed. The rotation of the radial shaft 6 can be controlled by the axial displacement of a rod 9. A jack (not shown) can control the axial displacement of the rods 9, and thus adjust uniformly the wedging of all blades 2 so as to systematically obtain the same setting for all the blades. The acoustic certification of an aircraft is based on the EPNL ("Effective Perceived Noise Level") criterion, which aims to evaluate the noise levels of the aircraft in the phases of flight. approach and takeoff. The EPNL also takes into account the discomfort perceived by the human ear, and caused by the different components of the measured noise spectra.
    [0003] Propeller motors, as described above, generate significant noise for the human ear during the approach and take-off phases, which limits their possibility of acoustic certification and therefore their implementation.
    [0004] SUMMARY OF THE INVENTION An objective of the invention is to propose a variable pitch bladed wheel making it possible to reduce the effective noise perceived by an observer on the ground during the take-off and approach phases at low speed and produced by the turbomachine in operation. In order to overcome the drawbacks of the state of the art, the invention proposes a variable-pitch bladed wheel comprising: a plurality of blades, each with variable pitching along a blade rotation axis and each having a foot, a plurality of blades comprising at least a first blade and at least a second blade; a plurality of rotor linkage shafts, each shaft having a foot and a head, the foot of each blade being mounted on the head of a blade; corresponding rotor connecting shaft via a pivot so as to allow the rotation of each blade along the axis of blade rotation, wherein the first blade has a first inclination of axis of rotation, such that the The axis of blade rotation of the first blade is inclined in a fixed manner with respect to a radial axis of the bladed wheel passing through the foot of the corresponding shaft, and the second blade has a second inclination of the axis of rotation. different from the first inclination of the axis of rotation. Such a bladed wheel makes it possible to reduce the noise produced by the turbomachine in operation and perceived by the human ear. Indeed, the overall noise produced by an aircraft in operation comprises a first tonal component, generated by the rotating parts of the aircraft. and / or by vortex generation mechanisms, and a second broadband component generated primarily by the interaction of turbulent structures (e.g. in the presence of vortices 3025246 or wakes, typically at boundary layers) with the surfaces. carrying the plane. The emergence of acoustic levels of lines of the first tonal component relative to the noise level of the second broadband component causes a great discomfort perceived by the human ear. Such an emergence is thus strongly penalized during the evaluation of the EPNL criterion. When all blades are uniformly distributed over the blade, as in existing engines, the clean noise of the bladed wheel thus consists of the fundamental line and its harmonics. The bladed wheel according to the invention has at its circumference a modified periodicity of distribution of the blades, so as to distribute the acoustic energy constituting the own noise on several frequencies.
    [0005] The invention thus makes it possible to reduce the emergence of the rays of the clean noise of the bladed wheel with respect to the broadband level, and thus to reduce the calculated EPNL levels as well as the perceived discomfort. The invention is advantageously completed by the following features, taken alone or in any of their technically possible combinations: the first inclination of the axis of rotation comprises a tangential inclination component in the plane of the bladed wheel; The first rotational axis inclination comprises an inclination component upstream or downstream with respect to the plane of the helix; each shaft corresponding to a first blade is inclined with respect to the radial axis, inclining the corresponding first blade 30 according to the first inclination of axis of rotation; each shaft corresponding to a first blade has a hinge inclining the head of the shaft relative to the remainder of the shaft, and thereby tilting the corresponding first blade according to the first rotational axis inclination; The first blade and the second blade have the same geometric shape; the first blade has a first blade inclination, such that the first blade is fixedly inclined relative to the axis of blade rotation of the first blade, and the second blade has a second blade inclination different from the first inclination of blade; the first blade and the second blade are configured so that the respective shims along the corresponding blade rotation axes are modified simultaneously, and so that: when the bladed wheel is locked in a high speed position, the position of the first blade relative to the corresponding radial axis is the same as the position of the second blade relative to the corresponding radial axis, 20 o when the bladed wheel is locked in a low speed position, the position of the first blade relatively to the corresponding radial axis is different from the position of the second blade relative to the corresponding radial axis.
    [0006] The invention also relates to a turbomachine comprising such a first bladed wheel. The invention is advantageously completed by the following features, taken alone or in any of their technically possible combinations: a second bladed wheel, the second bladed wheel comprising a plurality of blades, the first bladed wheel being disposed upstream or downstream of the second bladed wheel along the axis of the turbomachine, so as to allow, during the operation of the turbomachine, a temporal and / or spatial phase shift of the interaction between the first blade of the first bladed wheel and the blades of the second bladed wheel, with respect to 10 o the interaction between the second blade of the first bladed wheel and the blades of the second bladed wheel; the two blades have different speeds and / or directions of rotation.
    [0007] BRIEF DESCRIPTION OF THE FIGURES Other features and advantages of the invention will become apparent from the following description of an embodiment. In the accompanying drawings: - Figure 1 is a partial representation of a bladed wheel of the prior art; - Figure 2 is a partial representation of a turbomachine on which the bladed wheel is adapted to be integrated; FIG. 3a is a schematic representation of a first inclination of a tangential axis of rotation in the plane of the helix of a bladed wheel according to an exemplary embodiment of the invention; Figure 3b is a schematic representation of a first blade inclination of a bladed wheel according to an exemplary embodiment of the invention; Figure 3c is a schematic representation of a bladed wheel according to another exemplary embodiment of the invention; FIG. 3d is a diagrammatic representation of a bladed wheel according to yet another exemplary embodiment of the invention; FIG. 4 schematically represents the clean lines of the acoustic radiation of a bladed wheel according to the prior art with respect to the bladed wheel of FIG. 3d; FIG. 5 shows a detail of a bladed wheel comprising an inclined connecting shaft according to yet another exemplary embodiment of the invention; FIG. 6 shows a detail of a bladed wheel comprising a bellows according to yet another exemplary embodiment of the invention; FIG. 7 represents a detail of a bladed wheel comprising a cardan joint according to yet another exemplary embodiment of the invention; FIG. 8 represents a detail of a second blade of a bladed wheel according to an exemplary embodiment of the invention; FIG. 9 represents a detail of a bladed wheel comprising a blade inclination according to yet another exemplary embodiment of the invention; FIG. 10 shows a detail of a bladed wheel 25 comprising an inclination of the axis of rotation and a blade inclination according to yet another exemplary embodiment of the invention; FIG. 11 is a partial representation of a turbomachine with counter-rotating blades indicating sources of interaction noise between the vanes; FIG. 12 schematically represents bladed wheels according to the prior art and according to exemplary embodiments of the invention.
    [0008] DETAILED DESCRIPTION OF THE INVENTION Turbomachine 10 Referring to FIG. 2, a turbomachine portion 12 is shown. The turbomachine 12 is typically a turboprop engine. The turbomachine 12 typically comprises a blower 3, in which the blades or blades 2 belong to at least one bladed wheel, for example a single propeller (not shown) or two propellers, typically two counter-rotating propellers. By bladed wheel means for example a set of blades, distributed on the same ring, the ring extending around the motor axis.
    [0009] The blades are for example uniformly distributed in azimuth, for example by tangential spacing of 27t / Radian Npaies where Npaies is the number of blades of the bladed wheel. In the case of a single propeller engine, the propulsion system consists of a single propeller.
    [0010] In the case of a motor with several wheels, it is for example a turbomachine of the type with an unducted fan (in English "open rotor" or "unducted fan"), typically of such a turbomachine with blading counter. In a conventional manner, a flow of air at high pressure and temperature relative to the flow external to the motor makes it possible to drive the rotor 5 in rotation.
    [0011] The rotor 5 then has a rotational movement about a longitudinal axis A4 of the blower 3, which is transmitted to the blades 2 of the single wheel or wheels, for their rotation about a longitudinal axis A4.
    [0012] Variable setting 10 Referring to Figures 5 to 10, there are disclosed bladed wheels 1 comprising blades 2 according to the invention. As stated above, the geometric setting is for example the angle formed by the chord of the profile of a blade 2 and the plane of rotation of the corresponding helix 4. Thereafter, only the term "wedging" will be used, as is commonly used in the state of the art. We note that the calibration is an algebraic value. For example, a setting at -90 ° corresponds to a setting for which the leading edge of the blade 2 is located towards the rear.
    [0013] The pitch of the blades 2 of the bladed wheel or the propeller is adapted according to the flight conditions: for example, on the ground, the rigging is close to 10 °, at takeoff, between 35 ° and 45 °, and in climb, between 45 ° and 60 °. In cruising, the rigging is close to 65 °. The 90 ° setting is conventionally referred to as the "flag" position 25 or in English "feather" by the person skilled in the art, the setting at 0 °, "flat" position, and the setting at -30 °, "reverse" position. (This position allows braking the aircraft). The bladed wheel 1 comprises a plurality of blades 2 of bladed wheel or propeller blades. Each blade 2 has a variable pitch along an axis of rotation A1 of blade. Each blade 2 has a foot 201.
    [0014] The plurality of blades 2 comprises at least one first blade 21 and at least one second blade 22. The plurality of blades 2 thus comprises one or more first blades 21 and one or more second blades 22.
    [0015] The bladed wheel 1 comprises a plurality of rotor linkage shafts 6. Each connecting shaft 6 is typically adapted so that its rotation modifies the wedging of one of the blades 2. Each connecting shaft 6 has a foot 602 and a head 601. The shafts 6 are for example arranged at an arm of rotating housing 702, between a vein 10 from the turbine 701 and a vein directed towards the nozzle 703. The foot 201 of each blade 2 is typically mounted on the head 601 of a rotor connecting shaft 6. Conventionally, each blade 2 is connected to the corresponding connecting shaft 6 by a pivot 8 dedicated so as to allow the rotation of each blade 2 along the axis of rotation A1 of blade 2. The foot 201 of each blade 2 is for example mounted on the head 601 of a rotor connecting shaft 6 via the pivot 8. The pivot 8 may comprise counterweights 801. Thus the foot 201 of the blade 2 can be housed in the pivot 8 The pivots 8 are, for example, mounted in an axisymmetric ring 802 having a plurality of substantially cylindrical radial housings, this ring 802 being commonly referred to as a polygonal ring. Bearings 803 disposed between the polygonal ring 802 and the pivot 8 make it possible to maintain a degree of freedom of rotation of the pivot 8 with respect to the polygonal ring 802.
    [0016] The bladed wheel may further comprise mutually displaceable parts in an axial direction so as to cause rotation of the connecting shaft 6. The parts generally comprise a rod 9, one end of which is connected to the connecting shaft 6. Each rod 9 is connected to a shaft 6 connecting a blade 2.
    [0017] The device 1 may further comprise at least one jack (not shown) controlling the movement of the rod 9 in the axial direction. The wedging of the blade 2 can be modified by the axial extension of the rod of the jack, which acts on the rod 9 in axial translation. Rotation axis inclination The first blade 21 has a first rotational axis inclination, such that its axis of blade rotation A1 is fixedly inclined with respect to a radial axis A2, the radial axis A2 passing through the foot 602 of the corresponding shaft 6, that is to say the shaft 6 adapted for its rotation to change the pitch of the first blade 21. The first inclination of the axis of rotation is non-zero due to its inclination with respect to the radial axis A2.
    [0018] The second blade 22 has a second rotational axis inclination, typically with respect to the radial axis A2, which is different from the first rotational axis inclination. The axis of rotation of the second blade 22 is typically inclined in a fixed manner with respect to the corresponding radial axis A2.
    [0019] Thus, the second rotational axis inclination may be such that the corresponding axis of rotation of blade A1 has a zero inclination, that is to say that its axis of rotation of blade A1 is not inclined by relative to the radial axis A2 passing through the foot 602 of the corresponding shaft 6, that is to say the shaft 6 adapted so that its rotation modifies the wedging of the second blade 22, the second blade 22 being mounted so that this absence of inclination is maintained. Alternatively, the second blade 22 can be mounted so as to have an axis of rotation of blade A1 inclined in a fixed manner with respect to the radial axis A2 passing through the foot 602 of the corresponding shaft 6, ie that is, the shaft 6 adapted for its rotation to change the pitch of the second blade 22, the second inclination of the axis of rotation, however, decomposing into components having values different from those of the first inclination of the axis of rotation , that is to say that at least one of the components does not have the same value for the inclination of the axis of rotation of the first blade and for the inclination of the axis of rotation 5 of the second blade. A tangential inclination component and / or a tilt component upstream or downstream from the plane of the helix is thus typically different from the corresponding component of the first rotational axis inclination. This results in detuning between the at least one first blade 21 and the at least one second blade 22 for at least one wedging. By detuning means that the blades of the same bladed wheel are no longer governed by cyclic symmetry by rotation of a constant angle around the motor axis. By constant angle around the motor axis means an angle equal to 360 / N degrees where N 15 represents the number of blades of the wheel. Such a bladed wheel makes it possible to reduce the actual perceived noise produced by the operating turbomachine. Indeed, the overall noise produced by an aircraft in operation comprises a first tonal component, generated by the rotating parts of the aircraft and / or by vortex generation mechanisms, and a second broadband component generated mainly by the interaction of turbulent structures with the airfoils of the aircraft. As indicated above, the acoustic certification of an aircraft is based on the EPNL criterion, which is representative of the aircraft noise levels in the approach and take-off phases. The EPNL also takes into account the discomfort perceived by the human ear, and caused by the different components, the tonal component and the broadband component, of the measured noise spectra.
    [0020] The emergence of the acoustic levels of lines of the first tonal component relative to the noise level of the second broadband component causes a great discomfort perceived by the human ear. Such an emergence is thus strongly penalized during the evaluation of the EPNL criterion. The inherent noise of a helix radiates, for example, at rotational frequencies which are multiples of the rotational speed and the number of blades distributed evenly over the bladed wheel. Such frequencies are thus of the form k.w.N, where k is an integer, w the rotation speed, expressed for example in Hertz or revolutions / s, and N the number of blades uniformly distributed. Such frequencies are referred to as blade passing frequencies ("Blade Passing Frequency" in English terminology, BPF). Thus for the ith bladed wheel comprising Ni blades and rotating at a rotation speed in revolutions / minute RPNli, we obtain the blade passage frequency of the ith wheel BPF; by a formula of the type: BPFFNi * RPM / 60 When all the blades are uniformly distributed on the bladed wheel or propeller, as in existing engines, the own noise of the propeller can thus be composed of the fundamental line to the BPF frequency; and its harmonics.
    [0021] Thus, the acoustic contributions of each blade, on the total clean noise of the bladed wheel, add up in amplitude and in phase and the amplitude of the radiated noise is mainly proportional to the overall load of the bladed wheel and the volume moved fluid. Each blade thus contributes for example to a fraction of the overall traction according to a formula of the type: Ti = T / Ni where Ti is the traction generated by the blade j, T the overall traction and Ni the number of blades of the ith wheel bladed. When the blades are uniformly distributed in azimuth on the helix, the radiated acoustic energy is located at the frequencies n * BPFi of the rotation.
    [0022] The bladed wheel according to the invention has a modified periodicity due to the inclination of the axis of rotation of the first blade 21 or first blades 21 which is different from the inclination of the axis of rotation of the second blade 21. blade 22 or second blades 22, so as to distribute 5 for a given setting the acoustic energy constituting the own noise on several distinct frequencies and to obtain a frequency detuning. By considering, for example, loads distributed in the same way between each of the blades, the heterogeneous bladed wheel described, which has a modified bladed wheel periodicity from one blade to the other for at least one wedging, due to the inclination of the axis of rotation, preferably tangentially in azimuth, alternately or in addition upstream or downstream relative to the plane of the helix, contributes to distribute the acoustic energy constituting the own noise on several distinct frequencies . Upstream and downstream are typically defined with respect to the upstream and downstream of the engine. The invention thus makes it possible to reduce the emergence of the lines of the own propeller noise with respect to the broadband level, and thus to reduce the EPNL levels calculated as well as the perceived discomfort.
    [0023] As illustrated in FIG. 3a, the first rotational axis inclination may comprise a tangential inclination component 13 in the plane of the bladed wheel, i.e. such a non-zero component. The tangential direction is typically defined by the plane of rotation around the motor shaft.
    [0024] Alternatively or in addition, as illustrated in FIGS. 5, 6 and 7, the first rotational axis inclination may comprise an upstream or downstream inclination component with respect to the plane of the bladed wheel, that is to say, such a non-zero axial component. By plane of the bladed wheel or plane of the propeller is meant, for example, the plane orthogonal to the axis of the turbomachine at which the bladed wheel is positioned. The plane of the bladed wheel is thus, for example, the plane in which the bladed wheel extends substantially. This is the plane orthogonal to the motor axis and in which is located the center of gravity of the bladed wheel. By convention, we consider a positive for an upstream-downstream upstream and a 13-positive latch for a tangential latch in the direction defined by the rotation of the helix, typically around the motor shaft, that is to say say towards the intrados. Similarly, the second rotational axis inclination may comprise a tangential inclination component 13 in the plane of the helix, i.e., such a non-zero component, and / or a component of inclination upstream or downstream with respect to the plane of the helix, that is to say such a non-zero component. Alternatively, as indicated above, the second rotational axis inclination may comprise a tangential inclination in the plane of the zero helix, and / or an inclination upstream or downstream relative to the plane of the zero helix as shown in Figure 8. The axis of blade rotation A1 of the first blade 21, optionally the second blade 22, is typically inclined fixedly with respect to the corresponding radial axis A2. The tangential inclination component 13 and / or the upstream or downstream tilt component of the first rotational axis inclination, possibly of the second rotational axis inclination, can be fixed. with respect to the radial axis A2. In other words, the inclination of the axis of rotation of the first blade 21, possibly of the second blade 22, can be fixed with respect to the radial axis A2 so as not to allow, during operation of the blading, a rotation of the first blade 21, possibly of the second blade 22, that according to the axis of rotation A1 corresponding blade, the axis of rotation A1 is thus inclined tangentially and / or upstream or towards downstream in a fixed manner with respect to the corresponding radial axis A2. Thus, the blade 2 has only one degree of freedom of rotation, typically a degree of freedom in rotation along a single axis, that along the axis of rotation A1, no rotation along other axes of rotation. 'being possible. The tangential inclination component 13 and / or the upstream or downstream tilt component has, in other words, the tangential tilt angle and the tilt angle upstream or downstream. downstream are for example determined during the design, and can therefore be frozen by the construction of the bladed wheel. Thus, during the design process, for example, the upstream inclination component combination a and the tangential inclination component 13 are determined to satisfy particular aero-acoustic and mechanical objectives. This combination of upstream tilt component a and tangential tilt component 3, i.e. this combination of angles, is then for example applied to bearings 803. The only remaining degree of freedom is then the angle of rotation of the blade 2, for example of the first blade 21 and / or the second blade 22, about the axis which is defined by the bearing (and which is controlled by the control change of wedging via the radial shaft). The angles a and 13 are, for example, locked in the manufacture of the ring 802. As illustrated in FIG. 5, each connecting shaft 6 corresponding to a first blade 21, possibly to a second blade 22, may be inclined relative to to the radial axis A2, thus inclining the first blade 21, optionally the second blade 22, corresponding to the desired axis of rotation inclination. Such an implementation is particularly suitable for inclinations whose tangential components and upstream or downstream do not exceed 5 ° in absolute value. The inclination of the connecting shaft 6 corresponding to the first blade 21, possibly to the second blade 22, is for example a fixed inclination with respect to the corresponding radial axis A2, typically at an inclination comprising a tangential component 13 and / or the upstream or downstream tilt component a fixed with respect to the radial axis A2. Alternatively, or in addition, each rotor connection shaft 6 corresponding to a first blade 21, possibly to a second blade 22, may have a hinge tilting the head 602 of the connecting shaft relative to the rest of the shaft 6, and thus inclining the first blade 21, possibly the second blade 22, corresponding to the desired axis of rotation inclination. The hinge may hold the head 602 of the shaft at a fixed inclination to the radial axis A2, typically an inclination comprising a tangential component 3 and / or the tilt component upstream or to the downstream has fixed with respect to the radial axis A2. With reference to FIG. 6, such a joint may comprise a bellows 10, for example a metal bellows. Such a bellows 10 is adapted to implement a first rotational axis inclination, possibly a second rotational axis inclination, the components of which may have values of several degrees. With reference to FIG. 7, such a joint may comprise a cardan joint 11. Such a cardan joint 11 is adapted to implement a first inclination of the axis of rotation, possibly a second inclination of the axis of rotation, whose components may have values of several tens of degrees. The first blade and the second blade have for example the same geometric shape. Thus, the difference in rotation axis inclination 25 between the first blade 21 or the first blades 21 and the second blade 22 or the second blades 22 makes it possible to reduce the noise produced by the bladed wheel by having the same geometric shape to all the blades. This results in easier dimensioning because it is not necessary to make the bladed wheel with two different types of blades and thus a reduction in the costs of development and production of the bladed wheel.
    [0025] The mechanical performance can also be improved by a first and / or second rotational axis inclination comprising an upstream or downstream inclination component with respect to the plane of the helix.
    [0026] Furthermore, the blades are made to operate in various aerodynamic conditions according to the flight points such as takeoff, climb or cruise. It is known that these different flight points imply different bladed wheel geometries by varying the timing.
    [0027] Rotation variation by rotation of the blades 2 according to the prior art limits the possibilities of compromise on a geometry of the bladed wheel adapted for the different points of flight. The introduction of a first inclination of the axis of rotation, and possibly a second inclination of the axis of rotation, also makes it possible to improve the aerodynamic performance of the bladed wheel. The first and / or second rotational axis inclination makes it possible to improve staggering variations between the foot 201 of the blade and a head of the blade 2 and thus to possibly readjust the incidence of the flow on the profiles on the blade. the span of the blade considered.
    [0028] Inclination of blade with respect to the axis of rotation Each blade of the bladed wheel may have a fixed position relative to the axis of rotation of blade A1 of the blade considered in the rotating frame of the blade in question. This position corresponds for example to an inclination which may be zero or non-zero. All the blades can thus be inclined in a fixed manner with respect to their respective axes of rotation at respective blade inclinations. By blade inclination is typically meant the angle of algebraic value, formed between the stacking axis of the blade considered and the axis of rotation of the blade considered. Each blade is for example formed of a plurality of blade sections stacked so as to form said blade. Each section extends for example between a leading edge and a trailing edge. The stacking axis can thus be defined as the axis passing through the centers of gravity of the blade sections forming the blade considered.
    [0029] If the gravity centers can not be connected by a straight line, the stacking axis can be a stacking curve. This stacking curve has a tangent to the end located at the foot of the blade, which corresponds to the intersection of the stacking curve and a hub of the nacelle of the turbomachine. The inclination of the blade can then be defined as the angle in algebraic value, formed between said tangent of the blade considered and the axis of rotation of the blade considered. The blade inclinations of the first blade 21 and the second blade 22 may be identical, for example zero or non-zero. In this case, if the first blade 21 and the second blade 22 have identical shapes and different inclinations of axis of rotation, whatever the wedging, the bladed wheel has a detuning. Alternatively or in addition to the difference in the inclination of the axis of rotation between the first blade 21 and the second blade 22, the first blade 21 may have a first blade inclination, such that the first blade 21 is inclined in a fixed manner relative to the blade axis of rotation A1 of the first blade 21, and the second blade 22 may have a second blade inclination different from the first blade inclination. This results in a detuning between the at least one first blade 21 and the at least one second blade 22 for at least one wedging. By detuning means that the blades of the same bladed wheel are no longer governed by rotation symmetry of a constant angle around the motor axis. In the same way as for the detuning obtained by the inclination difference of the axis of rotation as described above, such a bladed wheel makes it possible to reduce the actual perceived noise produced by the operating turbomachine. In fact, the bladed wheel according to the invention has a modified periodicity due to the blade inclination of the first blade 21 or the first 5 blades 21 which is different from the blade inclination of the second blade 22 or the second blades. 22, so as to distribute for a given setting the acoustic energy constituting the own noise on several distinct frequencies and to obtain a detuning. For example, considering charges distributed in the same way between each of the blades, the heterogeneous bladed wheel described, which has a frequency of bladed wheel modified from one blade to another for at least one wedging, by the inclination of the blade axis for at least one wedging, contributes to distribute the acoustic energy constituting the own noise on several separate frequencies.
    [0030] The invention thus makes it possible to reduce the emergence of the lines of the own propeller noise with respect to the broadband level, and thus to reduce the levels of EPNL calculated as well as the perceived discomfort. As illustrated in FIG. 3b, the first blade axis inclination, that is to say the inclination of the rope A3 of the profile of the blade with respect to the axis of rotation A1 may comprise a component of tangential inclination in the plane of the bladed wheel for a given setting, that is to say, such a non-zero component. Depending on the evolution of the wedging, that is to say of the rotation of the blade relative to its axis of rotation, this component may alternatively be tangential, upstream or downstream. FIG. 9 thus illustrates for example a first blade 21, whose rope A3 is inclined with respect to the axis of rotation A1, thus tilting the first blade 21 according to the desired blade inclination. Inclination of the axis of rotation and inclination of the blade 3025246 21 The first blade 21 and the second blade 22 can be configured so that their respective shims along the axis of rotation are modified simultaneously. The first blade and the second blade may be configured to have different rotational axis inclinations and different blade inclinations. Such a combination of the two differences in inclination allows a more precise dimensioning of the bladed wheel according to the detuning to obtain. In particular, the first blade and the second blade may be configured to have different rotational axis inclinations and different blade inclinations such that in a first stall position, for example when the bladed wheel is wedged a position at high speed, the first blade and the second blade each have the same position relative to the corresponding radial axes, and so that in a second setting position, for example a low speed position, the first blade and the second The blades have different positions with respect to the corresponding radial axes. Thus it is possible, while retaining the same geometrical shape of blade 2, to obtain a vane whose noise during operation at takeoff and landing is reduced while maintaining its efficiency in operation at high altitude for which the positioning blades within the bladed wheel will be unchanged from the conventional configuration with blades having a radial pitch change axis, i.e. reproducing the tuned cyclic symmetry pattern.
    [0031] This is particularly interesting because the differences in axis of rotation inclination and / or blade between the first blade 21 and the second blade 22 can cause particularly pronounced differences at the head of blade 2, that is to say precisely in the zone where the blades are the most loaded in low speed flight condition and where the acoustic sources are the most intense.
    [0032] In fact, in this way, at high speed, the blades have the same spatial position around the bladed wheel, in particular with regard to the part of the blade that is useful during the flight at high altitude, but for the points Low speed operation, relevant for acoustics, for which the blades 2 must be recalibrated, typically of the order of 25 °, the modification of the wedging, although simultaneous for the first blade 21 and the second blade 22, typically by a single command makes it possible to obtain different spatial positions between the first blade 21 and the second blade 22 within the bladed wheel.
    [0033] According to one example, the second blade has an inclination of zero axis of rotation and zero blade inclination, the first blade having a non-zero axis of rotation inclination, typically downstream, and a non-zero blade inclination also zero, typically upstream in the low speed stall position, so that the first blade is tuned to the second blade in the low speed stall position, and detuned in a high speed stall position. FIG. 10 thus illustrates, for example, a first blade 21 in a high-speed stall position, the rope A3 of which is then not inclined with respect to the radial axis A2, so as to be tuned with a second blade 22 according to Figure 8, but whose axis of rotation A1 is however inclined. Thus, the modification of the staggering position along the inclined axis of rotation A1 makes it possible to modify the inclination of the rope A3 of the first blade 21 with respect to the second blade 22 and thus to obtain a low speed position which is detuned in relation to the second blade 22 to a second blade 22 according to FIG. 8. Distribution of the at least one first blade and the at least one second blade As indicated above, the at least one first blade 21 typically comprises one or more first blades 21 and the at least one second blade 22 typically comprises one or more second blades 22, which are differentiated by their inclination of axis of rotation and / or their inclination of blade as described above for at least one wedging . The bladed wheel may comprise at least one third blade, typically one or more third blades, typically fixedly inclined so as to have a third axis of rotation or blade axis inclination which is different from the first inclination and of the second inclination. Thus the bladed wheel may comprise several other sets of blades 10 each having a different inclination to that of the other set of blades thus defined. The first blades 21 and the second blades 22 can be placed along the bladed wheel according to a detuned spatial organization as described above, making it possible to compensate for the dissymmetry of the resulting forces and thus to prevent unbalance problems. Such a correction may for example comprise a periodic organization by sectors of the first blades 21 and possibly second blades 22 so as to compensate for the variation of the forces on the 20 detuned blades, that is to say the first blades 21, relative to each other. to the standard blades, typically the second blades 22. The blades 2 can be distributed uniformly relative to each other at the periphery of the bladed wheel. The first blades 21 may be uniformly distributed relative to one another at the periphery of the bladed wheel. With reference to FIG. 3c, there is described a bladed wheel as described above, comprising, for example, twelve blades 2, of which a portion, for example a quarter, of the blades of the plurality of blades 2 are first blades 21 which have a blade. first inclination of the axis of rotation and / or a first inclination of the blade as previously described, the first inclination being different from the second inclination of a part of the other blades, for example of all the other blades, for example three quarters of the blades of the plurality of blades 2, these other blades being second blades 22. The feet of the shafts of all the blades of the plurality of blades 25 are for example uniformly distributed along the bladed wheel. The shaft feet of all the first blades of the plurality of blades 2 are for example uniformly distributed around the motor axis. The first blades 21 and the second blades 22 have, for example, identical geometric shapes, the difference between the first blades 21 and the second blades 22 resulting from the different inclination of their axis of rotation A1 with respect to the radial axis A2. corresponding of each of the blades. With reference to FIG. 3d, there is described a bladed wheel as described above, comprising, for example, twelve blades 2, of which a portion, for example a third, of the blades of the plurality of blades 2 are first blades 21 which have a first inclination of the axis of rotation and / or a first inclination of the blade as previously described, this first inclination being different from the second inclination of a part of the other blades, for example of all the other blades, for example two thirds of the blades of the plurality of blades 2, these other blades being second blades 22. With reference to FIG. 4, a diagram representing the sound intensity (dB on the ordinate) is described as a function of the frequency of passage of GMP blade in the case of a bladed wheel according to the prior art 25 with respect to the case of a bladed wheel according to the invention, in particular a bladed wheel according to FIG. 3d. Note that the distinction of blades 2 of the bladed wheel between first blades 21 and second blades 22 reduces the level of perceived noise. Indeed, in the prior art, all identical blades arranged uniformly participate in forming a tonal component 420. With a bladed wheel according to the invention, as described in FIG. 3d, the tonal component 420 is replaced, for at least one wedging, by several distinct tonal components of lower levels, typically a first tonal component 421 for the first blades 21 which have a first inclination as described above and a second tonal component 422 for the second blades 22 having a second inclination as described above, typically a second zero inclination. This results in a decrease in the noise perceived in the calculation of the EPNL. Since the periodicity of the blades 2 along the bladed wheel is modified, the acoustic signature of the fundamental line will no longer be localized on one frequency but on at least two. The amplitude of each line of the detuned bladed wheel also tends to decrease because, because the inherent noise is proportional to the blading load, the blading of the blades on each distinct frequency decreases. This mechanism therefore makes it possible, by applying it in a relevant manner to create the heterogeneity of the bladed wheel, to reduce the value of the EPNL criterion, used for the acoustic certification of aircraft in take-off and landing phase.
    [0034] Associated Turbomachine The turbomachine can thus comprise such a variable pitch bladed wheel. The turbomachine may in particular comprise two such variable-pitched bladed wheels, the bladed wheels being, for example, counter-rotating bladed wheels. Turbomachine with two bladed wheels Arrangement of the first bladed wheel and the second bladed wheel 3025246 The turbomachine may comprise a first bladed wheel 1000 as described above. Referring to Figure 11, the turbomachine may further comprise a second bladed wheel 2000. The second bladed wheel 2000 5 typically comprises a plurality of blades 2002. The first bladed wheel 1000 may be disposed upstream or downstream of the second wheel 2000 auger along the axis of the turbomachine. The first bladed wheel 1000 and the second bladed wheel 2000 typically have different speeds and / or directions of rotation. The first bladed wheel 1000 and the second bladed wheel 2000 are typically counter-rotating. The first bladed wheel 1000 and the second bladed wheel 2000 can thus be arranged relative to each other so as to allow, during operation of the turbomachine, for example during low speed operation, a phase shift. temporal and / or spatial interaction between the first blade 21 and the blades 2002 of the second bladed wheel 2000 and the interaction between the second blade 22 and the blades 2002 of the second bladed wheel 2000. In the case of a two-bladed turbomachine arranged along the axis of the turbomachine according to the prior art, the blades of each bladed wheel having the same inclination, typically in the case of a non-ducted blower and / or counter-rotating blades, as a result of the operation of the two blades an interaction noise which is the consequence of the impact of the wakes 81 and vortices 82 from the blades of the bladed wheel arranged upstream with the blades of the bladed wheel available downstream. This interaction noise is one of the main sources of perceived noise in the approach and take-off phases. This interaction noise is very pronounced, in particular in the case of non-ducted fan turbomachines with counter-rotating bladed wheels, even more so in the particular case where all the blades are identical.
    [0035] The interaction between the upstream and downstream vanes of the turbomachine is repeated at each intersection between the blades of the bladed wheel upstream and the bladed wheel downstream. This results in an acoustic signature marked on discrete frequencies corresponding to combinations of the passage frequencies of the blades of the upstream bladed wheel and of the downstream bladed wheel of the type n * BPF1 + m * BPF2 with BPF; the frequency of passage of the blades of the bladed wheel i as described above with n and m natural numbers. This is all the more pronounced for unvented blowers, the noise of which is estimated to be substantially greater than that emitted by a conventional ducted blower. One reason is the absence of a nacelle surrounding the bladed wheels, nacelle which conventionally makes it possible to mask and / or attenuate a portion of acoustic radiation generated by the blades as well as the interaction phenomena marked between the bladed wheels. thanks to the use of acoustic treatments arranged in the duct, on the walls of the nacelle. In order to reduce this interaction noise, the possibilities conventionally offered to those skilled in the art consist, according to the prior art, of optimizing the identical aerodynamic profile for each of the blades of a bladed wheel. It is a question of playing on the intensity of the fluctuations of pressures resulting from the interactions between blades 2 by optimizing the shape of the profiles or the distribution of load on the span of the blade 2 to modify the influence of the vortex of head. For example, it is possible to avoid the impact of the headwheel of the upstream propeller with the blades of the downstream propeller by truncating them, but this is done to the detriment of aerodynamic performance at high speed. In addition, the optimization of the profiles to minimize the wakes from the upstream bladed wheel on the critical operating points with respect to the acoustic certification implies a modification of the shape of the profiles by increasing their camber to reduce the incidence of working profiles on these low-speed mission points. This adaptation of the profiles to acoustic vocation goes against the aerodynamic optimization in high speed for which the transonic behavior of the profiles requires a small camber of these. The adaptations of the profiles according to the known methods of the prior art for minimizing the interaction noise thus prove to be complex and delicate since they adversely affect the high speed performance of the propellers thereby degrading the fuel consumption on a mission. The turbomachine described here according to an exemplary embodiment of the invention with the first bladed wheel 1000 and the second bladed wheel 2000 makes it possible to reduce the intensity of the interaction noise by modifying the aerodynamic interactions between the first bladed wheel. 1000 and the second bladed wheel 2000. It is thus possible to modify spatio-temporal characteristics of the interaction of the wakes coming from the bladed wheel arranged upstream with the blades of the bladed wheel arranged downstream. This modification of the interactions is done by the introduction of the spatial and / or temporal phase shift of the interactions differentiating the influences coming or received from the first blades 21 with respect to the second blades 22 of the same first bladed wheel 1000. If the first bladed wheel 1000 is arranged upstream, it is influences from the blades because the wake comes from. These differences in inclination make it possible to create different wakes between a first blade 21 and a second blade 22 so as to generate both a different interaction when crossing with the blades of the second bladed wheel 2000 downstream but also a phase shift. spatial and / or temporal with respect to an identical interaction on all the blades 2 of the second bladed wheel 2000 downstream. If the first bladed wheel 1000 is disposed downstream, these are influences received by the blades because the wakes from the second upstream bladed wheel 2000 interact differently with the first blades 21 and with the second blades 22. These differences in inclination allow the wakes to create different interactions between a first blade 21 and a second blade 22 and a spatial and / or temporal phase shift with respect to an identical interaction on all the blades of the downstream bladed wheel. In both cases, this spatio temporal phase shift can reduce the overall acoustic signature of the helix doublet by allowing different recombinations of sound sources in the direction of observation. This can result in a noticeable reduction in the perceived noise level. The upstream bladed wheel and the downstream bladed wheel can both be first bladed wheels 1000 as described above, that is to say that each comprises at least a first blade 21 having a first inclination as described above and at least one second blade having a second inclination different from the first inclination. It is thus possible to take advantage of the differences in inclination both on the upstream bladed wheel and on the downstream bladed wheel to reduce the perceived noise coming from each bladed wheel individually as well as interactions between the two bladed wheels. Compared to the configurations of the prior art the turbomachine described here allows a spatial and temporal disruption of the interactions between the wakes from the upstream bladed wheel and the blades of the downstream bladed wheel. Such disorganization allows a potential reduction of the interaction noise at lower cost since the blades used for the same bladed wheel can remain of identical geometrical shape. Thus it is not necessary to make two different forms of blades and it is not necessary to resort to double referencing during assembly of the turbomachine.
    [0036] In addition, as described above, this detuning may be substantially active only for flight configurations requiring special attention for acoustics, typically at low speeds. In addition, such a modification of the vanes is easy to implement because the modification of the spatial positioning of the blades within the bladed wheel at low speed is simply produced by the rotation around the shifting axis having a tangential component. and / or a component upstream or downstream. This modification of the spatial positioning takes place, however, without substantially modifying the setting of the profiles with constant radius, which ensures a minor modification of the aerodynamic operation. EXAMPLES OF EMBODIMENT With reference to FIG. 12, counter-rotating bladed wheels 15 according to the prior art and according to exemplary embodiments of the invention are described, in the case where the upstream bladed wheel is the first bladed wheel. 1000 comprising at least a first blade 21 and at least a second blade 22, the first blade 21 being for example disposed between two second blades 22.
    [0037] The first bladed wheel 1000 upstream rotates at a first speed and in a first direction (Di. The second bladed wheel 2000 rotates at a second speed and in a second direction (02 opposite the first direction (01. The first blade has two possible positions corresponding to two examples of detuning by the first inclination of the axis of rotation Al. The blade 210 represents the location for a bladed wheel of the prior art of the blade disposed between the two second blades 22, at a distance equal to both and without its axis of rotation A1 is inclined relative to the corresponding radial axis A2.
    [0038] According to the first example, the first blade 211 has a first inclination comprising a tangential component 13 so as to be inclined rearwardly with respect to the direction of rotation of the first bladed wheel 1000. According to the second example, the first blade 212 has a first inclination comprising a tangential component 13 so as to be inclined forwardly with respect to the direction of rotation of the first bladed wheel 1000. Two consecutive blades 2010 and 2020 of the second bladed wheel 2000 downstream are also represented. The blades of the bladed wheel 2000 are for example identical in shape and inclination and uniformly distributed azimuthally for the bladed wheel 2000, that is to say without detuning. The blade 2020 is represented at three times t, t + At and t - At 'in the engine reference. Thus the blade referenced 2020 represents the blade 2020 at time t, the blade 2010 and the first bladed wheel are also represented at time t. At this instant t, the wake coming from the non-detuned blade 210 of the upstream bladed wheel of the prior art would cross the blade 2020. The blade referenced 2021 represents the blade 2020 at the instant t + At. At, the wake coming from the first blade 211 of the first bladed wheel 1000 of the first example, which has a first inclination of the blade rotation axis comprising a tangential component 13 towards the rear, crosses the blade 2020. Blade referenced 2022 represents the blade 2020 at time t - nt '. At this moment t - At ', the wake coming from the first blade 212 of the first bladed wheel 1000 of the second example, which has a first inclination of the blade rotation axis comprising a tangential component 13 towards the front, The blade 2020 of the second bladed wheel 2000 arranged downstream thus crosses the wakes of the first detuned blades 21 of the first bladed wheel 1000 arranged upstream either earlier (second example with the first blade 212) or more. later (first example with the first blade 211) with respect to crossing a wake from a blade 21 not detuned. There is therefore a temporal phase shift of the interaction between the first blades 21 of the first bladed wheel 1000 arranged upstream and the blades of the second bladed wheel 2000 5 arranged downstream, which results in a frequency of interaction different. The wakes from the blade 210 of the prior art, the first blade 211 and the first blade 212 are different because although these blades retain a close bearing due to their identical setting, on the one hand the volumes of these will be different because of the inclination, the stack presented is different, and secondly the path of the wake before impact on the upstream blade will be more or less long because of the first inclination which has a component tangential and / or a component upstream or downstream.
    [0039] The pressure fluctuation resulting from the crossing of the blades of the first bladed wheel 1000 and the second bladed wheel 2000 is different according to the detuning of the first blades 21 and therefore has a temporal phase shift also different. In addition, the crossing of the wake with the blades of the bladed wheel 20 downstream occurring at different times (t; t + At, t - nt '), the pressure fluctuation will arise spatially at different positions of the wheel downhill blast. A phase shift of the acoustic sources from one blade to the other, on the same bladed wheel, thus ensures a potential reduction in the level of the interaction noise.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A variable-pitch bladed wheel comprising: a plurality of blades (2), each of variable pitch along an axis of rotation (A1) of blade and each having a foot (201), the plurality of blades comprising at least a first blade (21). ) and at least one second blade (22), a plurality of rotor linkage shafts (6), each shaft (6) having a foot (602) and a head (601), the foot (201) of each blade (2) being mounted on the head (601) of a corresponding rotor connecting shaft (6) via a pivot (8) so as to allow rotation of each blade (2) along the axis blade rotation (A1), characterized in that the first blade (21) has a first rotational axis inclination, such that the blade axis of rotation (A1) of the first blade (21) is inclined fixed way with respect to a radial axis (A2) of the bladed wheel passing through the foot (602) of the corresponding shaft (6), and the second blade (22) has a second rotation axis inclination different from the first rotational axis inclination.
    [0002]
    2. A bladed wheel according to claim 1, characterized in that the first rotational axis inclination comprises a tangential inclination component ((3) in the plane of the bladed wheel.
    [0003]
    3. Bladed wheel according to any one of claims 1 or 2, characterized in that the first rotational axis inclination comprises a component inclination upstream or downstream (a) relative to the plane of the 'propeller. 3025246 34
    [0004]
    4. Bladed wheel according to any one of claims 1 to 3, characterized in that each shaft (6) corresponding to a first blade (21) is inclined relative to the radial axis (A2), inclining the first blade ( 21) corresponding to the first inclination of the axis of rotation. 5
    [0005]
    5. A bladed wheel according to any one of claims 1 to 4, characterized in that each shaft (6) corresponding to a first blade (21) has a hinge (10, 11) inclining the head (601) of the shaft relative to the remainder of the shaft (6), and thus tilting the corresponding first blade (21) 10 according to the first rotational axis inclination.
    [0006]
    6. Bladed wheel according to any one of claims 1 to 5, characterized in that the first blade (21) and the second blade (22) have the same geometric shape. 15
    [0007]
    7. A bladed wheel according to any one of claims 1 to 6, wherein the first blade (21) has a first blade inclination, such that the first blade (21) is inclined fixedly with respect to the axis of the blade. blade rotation (A1) of the first blade (21), and the second blade (22) has a second blade inclination different from the first blade inclination.
    [0008]
    8. Bladed wheel according to claim 7, characterized in that the first blade (21) and the second blade (22) are configured so that the respective shims along the corresponding axes of rotation (Al) of blade are modified simultaneously, and so that: when the bladed wheel is locked in a high speed position, the position of the first blade (21) relative to the corresponding radial axis (A2) is the same as the position of the second blade (22) relative to the corresponding radial axis (A2), 3025246 when the bladed wheel is locked in a low speed position, the position of the first blade (21) relative to the corresponding radial axis (A2) is different from the position of the second blade (22) relative to the corresponding radial axis (A2) 5.
    [0009]
    9. A turbomachine comprising a first bladed wheel (1000) according to any one of claims 1 to 6. 10
    [0010]
    10. A turbomachine according to the preceding claim, further comprising a second bladed wheel (2000), the second bladed wheel (2000) comprising a plurality of blades (2), the first bladed wheel (1000) being disposed upstream or downstream of the second bladed wheel (2000) along the axis of the turbomachine, so as to allow, during operation of the turbomachine, a temporal and / or spatial phase shift of the interaction between the first blade (21) of the turbine engine; first bladed wheel (1000) and the blades of the second bladed wheel (2000), with respect to the interaction between the second blade (22) of the first bladed wheel (1000) and the blades of the second bladed wheel (2000) ).
    [0011]
    11. Turbomachine according to the preceding claim, characterized in that the two blades (1000, 2000) have different speeds and / or directions of rotation.
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    同族专利:
    公开号 | 公开日
    GB2543725B|2020-05-20|
    FR3025246B1|2016-12-09|
    US20170274980A1|2017-09-28|
    US11046424B2|2021-06-29|
    GB201703239D0|2017-04-12|
    WO2016030645A1|2016-03-03|
    US20210291962A1|2021-09-23|
    GB2543725A|2017-04-26|
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    法律状态:
    2015-08-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-04| PLSC| Search report ready|Effective date: 20160304 |
    2016-08-01| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458125A|FR3025246B1|2014-08-29|2014-08-29|AUBAGEE WHEEL WITH VARIABLE CALIBRATIONS|FR1458125A| FR3025246B1|2014-08-29|2014-08-29|AUBAGEE WHEEL WITH VARIABLE CALIBRATIONS|
    US15/506,937| US11046424B2|2014-08-29|2015-08-28|Variable pitch bladed disc|
    PCT/FR2015/052296| WO2016030645A1|2014-08-29|2015-08-28|Variable pitch bladed disc|
    GB1703239.2A| GB2543725B|2014-08-29|2015-08-28|Variable pitch bladed disc|
    US17/341,277| US20210291962A1|2014-08-29|2021-06-07|Variable pitch bladed disc|
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