• 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 method for determining the vibration of turbomachine rotor blades (1), characterized in that it comprises the steps of: measuring (E1), by one or more sensors (4), ○ the evolution of the minimum distance between each sensor (4) and the apex (10) of each blade (1) along a radial axis (R) of the rotor, between successive rotations of each blade (1) in front of each sensor (4). ), a minimum distance value being obtained at each passage of each blade (1) in front of each sensor (4), to deduce a change in length of the blades (1) along said radial axis (R), and - use (E3 ) directly as such said variation in length of the blades (1) along said radial axis (R) in a modeling of the deformation of the blades (1), to deduce (E4) characteristics of one or more vibratory modes of blades (1) in rotation. The invention also relates to a turbomachine provided with a device implementing this method.
    公开号:FR3037394A1
    申请号:FR1555262
    申请日:2015-06-09
    公开日:2016-12-16
    发明作者:Andre Pierre Jean Xavier Leroux；Romain Charles Gilles Bossart
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to a method for determining the deformation of turbomachine rotor blades, in order to determine vibratory modes of the blades, as well as a device for carrying out this method, arranged in the fixed reference system, such as the crankcase. Presentation of the Prior Art Conventionally, an aircraft turbine engine comprises rotors comprising a plurality of radial vanes to accelerate an upstream flow of air downstream in the body of the turbomachine. The performance of a blade depends mainly on the shape of the blade when it is driven in rotation with the rotor on which it is mounted. Referring to Figure 1A, a blade 1 is mounted on a turbomachine shaft 2 extending along a longitudinal axis X. The blade 1 has traditionally a three-dimensional shape which is modified according to the speed of rotation of the shaft 2 of the turbomachine. By way of example, with reference to FIG. 1B, the blade 1 can lengthen radially and / or twist when the speed of rotation of the turbomachine shaft 2 increases. In the prior art, it is known to use one or more position sensors for measuring the time of passage of the blade tip at the sensors. This passage time depends on the shape of the head of the rotating blade. This measured passage time is compared to a theoretical transit time, in order to deduce, thanks to a deformation model, the vibratory modes of the rotating blade.
    [0002] This method of measuring deformation of the blade is known to those skilled in the art under the designation "Blade Tip-Timing", or "TipTiming", or "Non-Intrusive Stress Measurement (System) (NSMS)", or "Arrival Time Analysis (ATA)" or "Blade Vibration Monitoring (BVM)" or "Blade Health Monitoring (BHM)".
    [0003] Different types of sensors can be used in this method: optical probes, capacitive sensors, eddy current sensors, pressure sensors, etc.
    [0004] 3037394 2 The optical probes have the advantage of providing a steep front signal, allowing a great precision of the timing. The capacitive, magnetic or inductive sensor provides a more progressive signal since detection begins earlier and is extended later in comparison with the optical probe. Dating the passage of dawn is therefore less precise. In return, these latter sensors are robust vis-à-vis the fouling, which is a weak point of the optical probe. The solutions of the prior art are therefore limited either by the sensitivity to fouling or by the accuracy of the measurement.
    [0005] Various Tip-Timing solutions have been proposed in the prior art. The "Noncontact Blade Vibration Measurement System for Aero Engine Application" document by Zielinski et al. Discloses the use of capacitive sensors for determining blade vibrations of a rotor.
    [0006] In this document (p. 4), the passage time of each blade before each sensor (in total, six sensors) is measured. The evolution of the passage time of the vanes between pairs of sensors is then plotted as a function of the rotor speed. This passage time varies during a resonance of the blades.
    [0007] By comparing the temporal curves obtained with known theoretical time curves corresponding to expected deformation modes of the vanes, a characterization of the vibration modes is obtained. The solution proposed in this document is therefore a "Tip-Timing" solution well known in the prior art, and based on the measurement and study of a transit time, as mentioned above. It has the particular disadvantage of requiring powerful computers and fast, able to process a large amount of information. However, these calculators are expensive and bulky.
    [0008] US 2006/0122798 discloses a solution based on the use of sensors using eddy current flow. As can be seen in FIG. 5 and FIG. 8b, the signature produced by the blade on this type of sensor is particular since the sensor produces a signal for a long time. As indicated in [0019] of this document, the entire signal is taken into account to determine the status of the blades.
    [0009] Therefore, this solution requires important processing and calculation means. Another problem with Tip-Timing methods lies in the fact that this method determines the temporal evolution of the rotor with respect to itself, so that it is not possible to detect the variations and vibrations of the blades when they move at the same time in an overall movement. It is therefore desirable to have a method which makes it possible to overcome these drawbacks and which makes it possible to determine the vibratory behavior of the blades while reducing the number, the size, the cost and the complexity of the processing means necessary for this determination. PRESENTATION OF THE INVENTION In order to overcome the drawbacks of the prior art, the invention proposes a method for determining the vibration of turbomachine rotor blades, characterized in that it comprises the steps of measuring, by one or more sensors, the evolution of the minimum distance between each sensor and the top of each blade along a radial axis of the rotor, between successive rotations of each blade before each sensor, a minimum distance value being obtained at each passage 25 each dawn in front of each sensor, to deduce a variation in length of the blades along said radial axis, and directly use as such said variation in length of the blades along said radial axis in a modeling of the deformation of the blades, to deduce therefrom characteristics of one or more vibratory modes of rotating blades.
    [0010] The invention is advantageously supplemented by the following characteristics, taken alone or in any of their technically possible combinations: the variation of the length of the vanes along said radial axis is calculated by comparing the measurement of the minimum distance between the sensor and the summit of each dawn, with a reference distance for which the dawn does not undergo vibrations; The method comprises the steps of: o measuring, by at least one sensor, a variation of the blade tip passage time at said sensor, o also using this measurement to derive characteristics of one or more vibratory modes from the 10 blades in rotation; the method comprises the step of using only the variation of the length of the vanes along said radial axis in a modeling of the deformation of the vanes, in order to deduce therefrom characteristics of one or more vibratory modes of the vanes in rotation; the method comprises the step of deducing the amplitude and / or the phase and / or the frequency of the vibratory modes of the rotating blades; the method comprises the steps of measuring, by at least one sensor, a displacement of the vanes along a longitudinal axis of the rotor, and also using this measurement to derive characteristics of one or more vibratory modes from the rotating vanes.
    [0011] The invention also relates to a device for determining the vibration of the turbomachine rotor blades, characterized in that it comprises: one or more sensors, each sensor being configured to measure the evolution of the minimum distance separating it; the apex of each blade along a radial axis of the rotor, between successive rotations of each blade in front of each sensor, a minimum distance value being obtained at each passage of each blade in front of each sensor; and a processing unit, comprising a memory storing a modeling of the deformation of the vanes, and being configured to: determine a variation in length of the vanes along said radial axis from said minimum distance measurements of the sensor, and directly using as such, said variation of blade length along said radial axis in a modeling of the deformation of the blades, to deduce from it characteristics of one or more vibratory modes of the rotating blades. This device is advantageously completed by the following features, taken alone or in any of their technically possible combination: the sensor is a sensor capable of measuring a distance at the top of the blade, such as a capacitive sensor; the device comprises at least one sensor, configured to measure a blade tip passage time at said sensor, the processing unit being configured to derive characteristics of one or more vibratory modes from the rotating blades from measuring the minimum distance between the sensor and the tip of the vanes along a radial axis of the rotor, the measurement of the passage time of the blade tips and a modeling of the deformation of the vanes. The invention also relates to a turbomachine comprising a rotor with a plurality of blades, and a device for determining the vibration of turbomachine rotor blades, as described above. The invention has many advantages.
    [0012] The invention exploits information related to the deformation of the radial length at the top of the blade in order to deduce the vibratory modes of the blades, which makes it possible to increase both the robustness and the accuracy of the measurement and the calculation of the vibration. The measurement of a passage time from the top of the blades to the right of the sensors is no longer necessary. The invention makes it possible to detect the vibrations of the blades even if all the blades present at the same time the same displacement.
    [0013] Finally, the invention makes it possible to combine several measurements, such as the variation of the radial deformation of the blade with the variation of the passage time of the top of the blade and / or the axial displacement of the blade, in order to to refine the determination of the vibratory modes of the blades in rotation.
    [0014] Other features and advantages of the invention will become apparent from the description which follows, which is purely illustrative and nonlimiting, and should be read with reference to the accompanying drawings, in which: Figure 1A is a representation of a rotating rotor blade; Figure 1B is a representation of an example of deformation of a rotating rotor blade; Figure 2 is a schematic representation of a possible embodiment of a device for determining the vibration of turbomachine rotor blades according to the invention; Figure 3 is a schematic representation of the deformation of a blade, the measurement of the variation in radial length of the blade and the measurement of the variation of the passage time of the top of the blade; FIG. 4 is a diagrammatic representation of a possible embodiment (in solid single lines) of a method for determining the vibration of rotor vanes according to the invention, and possible variants, shown with lines. different ; Figure 5 is a schematic representation of the variation of the blade length along the radial axis as a function of time, each curve corresponding to a blade, for a single sensor.
    [0015] DETAILED DESCRIPTION FIG. 2 shows a possible embodiment of a device 15 for determining the vibration of turbomachine rotor blades 1. This representation is schematic. Each blade 1 is mounted on a shaft 2 and is rotatable about a longitudinal axis X of the rotor. This longitudinal axis generally coincides with the longitudinal axis of the turbomachine. The device 15 comprises at least one sensor 4, configured to measure the distance between the sensor 4 and the top 10 of the blades 1, along a radial axis R of the rotor. The radial axis R is the axis along which the vanes 1 extend about 15 of the shaft on which they are mounted in rotation. In general, a plurality of sensors 4 is provided. The sensor 4 is a distance or position sensor. This distance is likely to vary according to the vibrations experienced by the blade (dynamic deformations), and as a function of the static deformation of the blade, which results in particular from the centrifugal force and the aerodynamic load. The sensor or sensors 4 record the variation of this distance over time. In particular, the evolution of the minimum distance between the sensor 4 and the top of each vane 1 along the radial axis R is measured between successive rotations of each vane in front of each sensor 4. plurality of successive rotations. At each passage of each blade in front of each sensor, a minimum distance value is measured by each sensor 4. The sensor 4 can in particular be programmed to measure this minimum distance at each passage of the blade in front of said sensor 4. As explained by As a result, this single minimum distance evolution value, as a single piece of information, suffices to be able to feed an algorithm for determining the modes of vibration, without wishing to transform it or process it to determine a passage time. The measurement of the minimum distance of the sensor 4 makes it possible to deduce a variation in the length of the blades 1 along said radial axis R.
    [0016] In particular, the comparison of the evolution of the minimum distance measured by the sensor 4 with a reference distance makes it possible to deduce the evolution of the deformation of the length of the blade 1 along the radial axis R. The distance reference is for example the distance for which the dawn does not undergo any vibration.
    [0017] Alternatively, or in addition, the reference distance may be determined by another method, such as the average of a number of previous measurements representative of the rotor in the absence of vibrations. The sensor 4 is for example a capacitive sensor. It may also be other sensors, such as an optical probe, a laser range finder, or an eddy current sensor, etc. In the example shown in FIG. 2, the blades 1 are surrounded by a housing 21. The sensors 4 are arranged on the internal face of the casing 21, and are turned towards the vertices 10 of the blades 1.
    [0018] In the case of a non-ducted rotor, it is possible, for example, to provide a support mast for the sensors 4 in order to arrange them close to the vertices 10 of the vanes 1. Other positions of the sensors 4 are possible according to the rotor environment. The sensors 4 are positioned in a fixed reference of the turbomachine.
    [0019] The device 15 further comprises a processing unit 11. The processing unit 11 is of the processor type, comprising at least one memory 16, and capable of executing a computer program for processing the measurements of the sensors 4. The unit 11 can communicate with the sensors 4 in order to collect the data. 30 measurements. This communication is carried out by any known means, such as for example by wire connection, or wireless, or radio or by removable storage means.
    [0020] The memory 16 stores a modeling of the deformation of the blade 1. This modeling is extracted from a 3D model of the dawn, which takes into account the different parameters of the blade (dimensions, mechanical properties, external environment , etc.).
    [0021] As explained below, the processing unit 11 is configured to determine characteristics of one or more vibratory modes of the rotating blade 1, in particular from the measurement of the minimum distance of the sensor 4, which makes it possible to back to the variation in blade length along the radial axis R, and the deformation pattern of the blade 1. This also includes the static deformation of the blade, which can be seen as a vibratory mode at zero frequency. Optionally, the device 15 comprises at least one sensor 5, configured to measure a passage time of the vertex 10 of the blades 1 at said sensor 5. The sensor 5 is a presence detection sensor, or a position sensor and / or or distance. When the dawn undergoes a deformation, the passage time to the right of the sensor 5 varies. In particular, this measured passage time is directly correlated to the amplitude of deformation of the blade. Thus, when the processing unit 11 compares this measured passage time with a theoretical transit time, the processing unit 11 deduces a deformation of the blade (knowing the speed of movement of the blade in front of the sensor, this speed of displacement being dependent on the speed of rotation), and consequently on the characteristics of the vibratory modes of the blades 1, thanks to a modeling of the deformation.
    [0022] The sensor 5 is for example a capacitive sensor. It may also be other sensors, such as an optical probe, or an eddy current sensor, or a pressure sensor, etc. The sensor 5 may have the same positioning as the sensor 4, as explained above.
    [0023] In general, a plurality of sensors 5 is provided, for example between four and eight sensors.
    [0024] The same sensor can be used for the sensor 5 and the sensor 4. In the case of a capacitive sensor, it simultaneously provides the passage time of the top 10 of the blade 1 and the minimum distance that separates it from the top of the blade at each passage of the blade (and therefore the variation in length of the blade along the radial axis). Alternatively, the sensor 4 and the sensor 5 may constitute separate sensors, for example arranged side by side. In one embodiment, the processing unit 11 is configured to determine characteristics of one or more vibratory modes of the blades 1 rotating from the evolution of the minimum distance between the sensor 4 and the top 10 of the blades 1 along a radial axis R of the rotor (this measurement makes it possible to obtain the measurement of the variation in length of the blades 1 along the radial axis), of the measurement of the passage time of the top 10 of the blade 1 (obtained by the sensor 5), and the modeling of the deformation of the blades 1. Thus, the processing unit 11 exploits both the measurements of the sensor 4 and the measurements of the sensor 5 to calculate the vibratory modes of the dawn 1. Alternatively, in one embodiment, the processing unit 20 is configured to use only a distance measurement (in particular the minimum distance measurement of the sensor 4) in the modeling of the deformation of the blades. As indicated, the processing unit calculates a variation in the length of the blades 1 along the radial axis R from the distance measurements of the sensor 4. This variation in length of the blades along the radial axis is then used directly as that such in a modeling of the deformation of the blades, to deduce characteristics of one or more vibratory modes of blades 1 in rotation. This embodiment thus eliminates measurements of the passage time of the blades to determine the vibration modes of the blades.
    [0025] Process A method of determining the vibration of turbomachine rotor blades 1 using the above-mentioned device 15 is now described.
    [0026] The method is implemented during the operation of the rotor, in order to evaluate the characteristics of the deformations of the blades 1. The method (see FIG. 4) comprises a step El consisting of measuring the evolution of the minimum distance between the sensor. 4 and the top 10 of the blades 1 along the radial axis R of the rotor. This evolution is studied from measurements of minimum distances between each sensor and each blade, between different successive passages of the blade. It is therefore a question of seeing how the minimum distance evolves for each blade (blades 1 to N) as and when the different passages in front of the sensor (or respectively in front of the sensors 1 to X).
    [0027] As mentioned above, this measurement makes it possible to obtain the temporal variation of the length of the blades 1 along the radial axis of the rotor. This variation in length AL along the radial axis is shown diagrammatically in FIG. 3. This measurement is performed at each passage of the blade 1 to the right of the sensor 4.
    [0028] The processing unit 11 (step E2) compares the minimum distance measured by the sensor 4 with each passage with a reference distance. The reference distance may in particular be the theoretical distance for which the blade does not undergo any vibration, and / or be calculated from the average of previous measurements. The theoretical distance is known because the dimensions of the blade 1 are known from its manufacture, as well as the positioning of the blade 1 in the rotor and the position of the sensor 4 vis-à-vis the blade 1. Alternatively , the reference distance can be (see arrow E2 in double lines in Figure 4), for a continuous acceleration or deceleration of the blade, the distance measured immediately before and / or immediately after the vibration mode is crossed to the speed This time is materialized by Ti, respectively T3, in FIG. 5). This method is called the zero method. This makes it possible to dispense with other drifts of the radial length of the blade, which are not due to the phenomenon sought (for example, heating of the engine, or deformation of the engine, not characteristic of the desired vibration). For this purpose, it is assumed that only the desired vibration phenomenon that interests us is rapidly changing, while the other parameters of variation are slower. This comparison makes it possible to obtain the evolution of the variation of length of the blade 1 along the radial axis, due to the vibrations experienced by the blade 1 in rotation, as a function of time. As mentioned above, the processing unit 11 has a modeling 17 of the deformation of the blade 1, stored in its memory 16. This modeling 17 is extracted from a 3D model of the dawn, 15 which takes into account the different parameters of the blade (dimensions, mechanical properties, external environment, etc.). This type of approach is already used in "Tip-Timing". In this type of modeling, the knowledge of the local deformations applied to the dawn makes it possible to go back to the vibratory modes of the dawn, and thus to the distribution of the stresses undergone by the whole dawn. In practice, the local deformation as measured at the top is compared with several possible hypotheses of deformation modes of the blade in order to identify the vibratory mode (s) undergone by the blades (step E3 in Figure 4). The processing unit 11 thus introduces directly and as such the measurement of the variation in length of the blade 1 along the radial axis, in the deformation model of the blade 1. The unit 11 deduces from this ( step E4) characteristics of one or more vibratory modes of the blades 1. In particular, the amplitude, frequency, phase, and damping of the vibratory mode or modes experienced by the blades are calculated.
    [0029] In one embodiment, the processing unit 11 uses, during step E3, only a distance measurement in a modeling of the deformation of the blades 1, in order to deduce therefrom characteristics of one or more vibratory modes. rotating blades 1, said distance measurement comprising measuring distance of said sensor 4 which makes it possible to determine the variation in length of the blades 1 along the radial axis. Thus, the raw data of minimum distance at each passage of the blade is used (or more particularly the variation of the length of the blades along the radial axis that follows) in the algorithm that models the deformation of the blades, without this measure of distance is not converted into passage time. An example of a measurement of the variation of blade length 1 as a function of time is shown in FIG. 5. Each curve represents the behavior of one of the vanes of the rotor as it passes in front of a given sensor. There are as many curves as blades. On this curve, the position seen by a single sensor 4 is shown. The abscissa represents the time or the rotational speed of the rotor, the measurement being ideally during an acceleration or a deceleration, in order to cross the vibratory modes. The ordinate represents the value AL of the game at the top of the blade when the blade passes the sensor. The variation AL of the clearance at the blade tip can be likened to the inverse of the variation in the radial length of the blade 1, with respect to the theoretical length of the blade 1 (length without deformation). The graph therefore corresponds to a discontinuous succession of values obtained at each turn, the values being represented in a continuous curve, for a given blade in front of a given sensor. In this graph, the variation AL is plotted against the time during acceleration, for each blade. When in the presence of a synchronous vibration mode, the deformation of each of the blades in front of a sensor has a pattern characteristic of the resonance of a synchronous mode (time T2 in the part surrounded on the curve). In particular, the characteristic signature of a synchronous mode is that the deformations are, at this moment, different from one blade to the other, some of the blades then having a maximum of deformation, others a minimum, and others an intermediate value. In other words, when the synchronous mode is traversed, the evolution of the deformation is reflected by an advance for some blades, a delay for other blades and a stagnation for some blades.
    [0030] The number of minima and the number of maxima are representative of the vibrational harmonic because each blade may have made several rounds of vibration in one revolution. In Figure 5, a simple harmonic is shown. At the instant T3, a new game distribution, different from that of the instant Ti, is visible, the passage of the synchronous resonance having brought about these game distribution changes. By making assumptions about the mode or modes of vibration experienced by the vanes (for example harmonic 1, or 2, etc.), the processing unit 11 compares the distribution of the deformations measured at this time with the distribution of the deformations resulting from the hypotheses, in order to validate these hypotheses and identify the mode (s) of vibration. As can be seen, the method implements a vibration calculation directly from a measurement of distance variation. Thus, the determination of a passage time or the measurement of a passage time is no longer absolutely necessary. This is advantageous and increases the accuracy of the calculation. For example, it has been mentioned that the sensor 4 could be a capacitive sensor, which is a sensor that is robust to fouling but whose measurement of the passage time (so-called "Tip-Timing" method) of the top of the blade is less accurate than other sensors. However, according to the method, it is above all a measurement of radial distance (AL) which allows to deduce the vibratory modes of the dawn. Since capacitive sensors are accurate in distance measurement, the method makes it possible to combine measurement accuracy and robustness, which was not the case with the "Tip-Timing" method of the art. previous, based on the unique measure of a time of passage from the top of the dawn.
    [0031] In addition, the method makes it possible, by this measurement and its operation, to directly identify an overall vibratory mode (ON mode) by detecting a "swelling" of the rotor blade. Indeed, a problem with the Tip-Timing method lies in the fact that this method determines the temporal evolution of the rotor with respect to itself, so that it is not possible to detect the variations and vibrations when all the blades are moving at the same time. With the device and the method according to the invention, the swelling highlighted makes it possible to simplify the detection of vibrations.
    [0032] If all vanes move at the same time, the displacement measurement is accurate, even if all vanes move in a similar manner. In addition, the vibrations are determined directly and do not require significant calculations, unlike state-of-the-art methods based on the principle of "Tip-Timing". By reducing computing requirements, the power of processing units for accurate vibration mode determination no longer needs to be oversized. Finally, for a given blade and a given sensor, one obtains as many measurements as passes, which makes it possible to quickly and responsively provide the evolution of the radial length of the blade, without it being necessary to perform measurement averages or sinusoidal modelings. In order to have additional measurements, it is possible to provide one or more measurements to complete the measure in radial deformation of the top of the blade.
    [0033] Optionally, the method comprises the additional step E1bis consisting in measuring a variation in the passage time of the tip 10 of the blades 1 at the sensor 5, with respect to a theoretical transit time (arrow E2bis in regular dotted lines). Alternatively, the measured pass time can be compared to previously measured pass times (E2bis arrow in irregular dotted lines), as explained for radial distance measurements. This variation (AT) is related to the deformation of the blade along the tangential axis, and no longer radial as before (see Figure 3).
    [0034] The processing unit 11 introduces measurement of the distance between the sensor 4 and the top 10 of the blades 1 along a radial axis R of the rotor, and the measurement of the variation of the passage time of the tip 10 of the blades 1, in the modeling of the deformation of the blades 1, to deduce the characteristics of the vibratory modes of the blades 1.
    [0035] Combining the two pieces of information in the model improves the accuracy of the calculation. It is noted that these two measurements are, as a first approximation, in phase quadrature. As a result, measurement performance and robustness are increased. According to a simplified model, the dawn is comparable to an oscillator whose amplitude, phase and, if appropriate, frequency, must be determined. The measurement of the variation of the passage time gives additional information on the knowledge of the vibration modes of the blades.
    [0036] Schematically, this modeling in a two-dimensional or two-variable space is comparable to the discrete methods of trellis coding used in telecommunications (for example, the Viterbi method), where the extraction of the transmitted signal is carried out by comparing the phase and amplitude of the signal measured at the phase and amplitude of a reconstructed clock signal. The phase and the amplitude are here replaced by the variation of the passage time AT and the variation of the clearance AL (corresponding to the variation of the radial length of the blade). Each vibratory mode has a signature combining a time of passage and a game of its own. This combination further reduces measurement noise and improves measurement robustness.
    [0037] In order to further improve the computation of the vibration mode characteristics, it is possible to take other measurements into account, such as the displacement of the vanes along a longitudinal axis (X) of the rotor. A dedicated sensor can be used (position or distance sensor), or a sensor already mentioned (sensor 4/5) can be used for this measurement.
    [0038] The sensor measures (step El t ') the distance that separates it from the blade along the longitudinal axis, in order to deduce the longitudinal displacement of the blade. Again, a minimum distance value is obtained for each blade at each pass in front of a sensor, which makes it possible to determine the longitudinal displacement of the blade over time. For example, longitudinal displacement is performed following the longitudinal position of the leading edge or the trailing edge. Again, a longitudinal position value is obtained for each passage in front of each sensor and the longitudinal displacement is deduced over time.
    [0039] This measurement can be compared to a reference distance, without vibration, to determine the longitudinal displacement of the blade, similar to what has been described with respect to the determination of the radial length variation of the blade. dawn (arrow E2t 'dashed regular). The measured distance can also be compared to an average of previously measured distances (arrow E2t 'in irregular dashed lines). In this exemplary embodiment, each vibratory mode is characterized by a signature that is specific to it and combining a transit time AT, a radial clearance AL (corresponding to the variation in radial length of the blade) and a longitudinal displacement. The theoretical model of deformation of the dawn is thus applied in a space with three variables.
    [0040] 3037394 18 The technologies mentioned for sensors 4 and 5, as well as their positioning, are applicable to this sensor. The instantaneous speed of the blade can also be measured (step E1 quater) in order to be taken into account in the dawn model. This can be compared to a reference value, such as a theoretical value (arrow E2quater in regular dashed lines), or previously measured values (arrow E2quater in irregular dashed lines). Since the instantaneous speed of the blade is also taken into account, the theoretical model of deformation of the blade is projected into a representation space which has an additional dimension, that is to say that the Theoretical model of deformation of dawn is applied in a four-variable space. The theoretical model of deformation of the blade is then projected into a representation space having at least one dimension which comprises the variation of the length of the blades.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method for determining the vibration of turbomachine rotor blades (1), characterized in that it comprises the steps of: measuring (E1), by one or more sensors (4), o the evolution of the distance between each sensor (4) and the apex (10) of each blade (1) along a radial axis (R) of the rotor, between successive rotations of each blade (1) in front of each sensor (4), a distance value minimum being obtained at each passage of each blade (1) in front of each sensor (4), to deduce a change in length of the blades (1) along said radial axis (R), and use (E3) directly as such said variation of the length of the blades (1) along said radial axis (R) in a modeling of the deformation of the blades (1), to deduce (E4) characteristics of one or more vibratory modes of the vanes (1) in rotation.
    [0002]
    2. Method according to claim 1, wherein the variation in length of the blades along said radial axis (R) is calculated (E2) by comparing the measurement of the minimum distance between the sensor (4) and the apex (10) of each blade (1), with a reference distance for which the blade (1) does not undergo vibrations.
    [0003]
    3. Method according to one of claims 1 or 2, comprising the steps of: measuring (E1bis), with at least one sensor (5), a variation of the passage time of the tip (10) of the blades (1) to level of said sensor (5), use (E3) also this measurement to derive characteristics of one or more vibratory modes of blades (1) in rotation. 3037394 20
    [0004]
    4. Method according to one of claims 1 or 2, comprising the step of using only the change in length of the blades (1) along said radial axis in a modeling of the deformation of the blades, to deduce the characteristics of the blades. one or more vibratory modes of the blades (1) in rotation.
    [0005]
    5. Method according to one of claims 1 to 4, comprising the step (E4) of deducing the amplitude and / or the phase and / or the frequency of vibration modes of blades (1) in rotation.
    [0006]
    6. Method according to one of claims 1 to 3, comprising the steps of: measuring (E1t '), with at least one sensor, a displacement of the vanes (1) along a longitudinal axis (X) of the rotor, use (E3) also this measurement to deduce (E4) characteristics of one or more vibratory modes of blades (1) in rotation. 20
    [0007]
    7. Device (15) for determining the vibration of the turbomachine rotor blades (1), characterized in that it comprises: o one or more sensors (4), each sensor being configured to measure the evolution of the distance which separates it from the apex (10) of each blade (1) along a radial axis (R) of the rotor, between successive rotations of each blade (1) in front of each sensor (4), a minimum distance value being obtained at each passage of each blade (1) in front of each sensor (4); and a processing unit (11), comprising a memory (16) storing a modeling of the deformation of the blades (1), and being configured to: o determine (E2) a variation in the length of the blades (1) according to said radial axis (R) from said minimum distance measurements of the sensor (4), and o using (E3) directly as such said variation of length of the blades (1) along said radial axis (R) in a modeling deformation of the blades (1), to deduce (E4) characteristics of one or more vibratory modes of the blades (1) in rotation. 10
    [0008]
    8. Device according to claim 7, wherein the sensor (4) is a capacitive sensor.
    [0009]
    9. Device according to one of claims 7 or 8, comprising: at least one sensor (5), configured to measure a passage time of the vertex (10) of the blades (1) at said sensor (5), processing unit (11) being configured to derive characteristics of one or more vibratory modes from rotating vanes (1) from: o measurement of the minimum distance between the sensor (4) and the apex (10) ) blades (1) along a radial axis (R) of the rotor, o measuring the passage time of the tip (10) of the blades (1), and o the modeling of the deformation of the blades (1). 25
    [0010]
    10. Turbomachine comprising: a rotor comprising a plurality of blades (1), a device (15) for determining the vibration according to one of claims 7 to 9.
    类似技术:
    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    WO2016198794A1|2016-12-15|
    US10670452B2|2020-06-02|
    FR3037394B1|2018-11-02|
    US20180164150A1|2018-06-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20060122798A1|2004-10-19|2006-06-08|Carole Teolis|Method of determining the operating status of a turbine engine utilizing an analytic representation of sensor data|
    US20080149049A1|2006-12-21|2008-06-26|Daniel Edward Mollmann|System and method for converting clearance data into vibration data|
    US20100089166A1|2006-12-21|2010-04-15|Mtu Aero Engines Gmbh|Apparatus and method for non-contacting blade oscillation measurement|
    US20140007591A1|2012-07-03|2014-01-09|Alexander I. Khibnik|Advanced tip-timing measurement blade mode identification|
    US8591188B2|2005-04-26|2013-11-26|General Electric Company|Displacement sensor system and method of operation|
    US7509862B2|2007-01-24|2009-03-31|Massachusetts Institute Of Technology|System and method for providing vibration detection in turbomachinery|
    US8606541B2|2009-06-12|2013-12-10|Mechanical Solutions, Inc.|Combined amplitude and frequency measurements for non-contacting turbomachinery blade vibration|
    GB201102542D0|2011-02-14|2011-03-30|Qinetiq Ltd|Proximity sensor|
    US20130082833A1|2011-09-30|2013-04-04|General Electric Company|System and method for monitoring health of airfoils|
    US9395270B2|2012-10-19|2016-07-19|Florida Power & Light Company|Method and system for monitoring rotor blades in combustion turbine engine|
    US20140142888A1|2012-11-19|2014-05-22|Elwha Llc|Mitigating wind turbine blade noise generation|BE1024658B1|2016-10-18|2018-05-22|Safran Aero Boosters S.A.|METHOD AND SYSTEM FOR NON-CONTACT MEASUREMENT OF CIRCULAR GEOMETRIC PARAMETERS OF TURBOMACHINE ELEMENTS|
    CN111256636B|2018-11-30|2021-11-19|上海电气电站设备有限公司|Method for measuring torsion of blade|
    CN110118108B|2019-05-12|2020-05-08|西北工业大学|Method for measuring distortion degree of blade profile of engine rotor blade in rotating state|
    CN112539829B|2020-12-09|2021-11-19|西安交通大学|Arrangement method and system of self-adaptive blade tip timing sensors|
    法律状态:
    2016-06-06| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-16| PLSC| Search report ready|Effective date: 20161216 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1555262A|FR3037394B1|2015-06-09|2015-06-09|METHOD AND DEVICE FOR DETERMINING THE VIBRATION OF ROTOR BLADES|
    FR1555262|2015-06-09|FR1555262A| FR3037394B1|2015-06-09|2015-06-09|METHOD AND DEVICE FOR DETERMINING THE VIBRATION OF ROTOR BLADES|
    US15/580,998| US10670452B2|2015-06-09|2016-06-09|Method and device for determining the vibration of rotor blades|
    PCT/FR2016/051387| WO2016198794A1|2015-06-09|2016-06-09|Method and device for determining the vibration of rotor blades|
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