• 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:
    According to the invention, there is provided a blade vibration measuring apparatus comprising a non-contact displacement sensor (3) which outputs a displacement measurement signal by measuring a displacement of a moving blade (1) of a turbine in a rotational axis direction, and a blade tip position identification device (4) based on a interpolated curve outputs a blade tip position identification signal, and a blade vibration calculating device (5) which determines a vibration amplitude and a vibration frequency of the moving turbine blade (2) based on the time variation of the distance between the non-contact displacement sensor (3) and the tip position of the moving turbine blade (2) calculated after having obtained the blade tip position identification signal outputted from the blade tip position identifying device (4).
    公开号:CH705536B1
    申请号:CH01644/12
    申请日:2012-09-10
    公开日:2017-09-29
    发明作者:Nakayama Kohichi；Osaki Kenji；Matsuda Hisashi；Sakakida Hitoshi；Hirano Toshio；Hirate Toshiaki；Mizuno Sueyoshi；Saito Ikuo
    申请人:Toshiba Kk；
    IPC主号:
    专利说明:

    description
    FIELD [0001] The present invention relates to a blade vibration measuring device for measuring the vibration occurring on a moving blade of a variety of turbines and the like.
    Background of the Invention In the design, development and manufacture of a variety of turbines, such as a steam turbine and a gas turbine, it is necessary to measure vibration that occurs on a moving turbine blade in order to increase reliability with respect to the invention To prevent an accident as well as to improve performance.
    A conventional blade vibration measuring apparatus employs a method of measuring the passage time of a blade using a proximity sensor and obtaining vibration based on the time difference of the passage time.
    In the conventional blade vibration measuring apparatus, it is necessary to accurately measure the blade passage time with a high sampling frequency of several hundreds MHz or higher. Accordingly, it is necessary to prepare a data acquisition apparatus having a high sampling frequency and a high time resolution capability.
    Furthermore, in order to obtain a high timing accuracy, attention must be paid not only to the performance of the detection device but also to the transmission time of a measurement signal. In addition, the measured phase difference (time difference) must be converted into a shift. Accordingly, there is a problem that much time and cost are required for preparing the measurement and analyzing the measured data.
    On the other hand, there is a method of directly measuring the blade vibration using a non-contact displacement sensor instead of a proximity sensor.
    Since the measurement in this method is performed at a sampling frequency on the order of several hundred kHz, the resolution capability required for a data acquisition device is relatively low, and preparation of a measurement system and data analysis are relatively easy.
    However, when a large rotary blade such as an output stage blade of a steam turbine or the like is to be measured, displacements at a constant position can not be detected due to the inability of the sample to equalize with the rotational speed of the blade. Accordingly, it is difficult to perform a measurement of the blade vibration with high accuracy.
    The measurement signal of the displacement sensor is evaluated as a distance directly and the subsequent vibration analysis is based on the change over time of the measured distance.
    Brief description of the drawings [0010]
    FIG. 1 is an explanatory view illustrating an arrangement and a block structure of a vane vibration measuring device according to a first embodiment; FIG.
    2A and 2B are an explanatory view of a method for identifying the tip position of a blade in the blade vibration measuring apparatus according to the first embodiment, and a graph showing the time variation of an output voltage waveform from a non-contact displacement sensor;
    3A and 3B are an explanatory view and a graph illustrating the change in distance between tip positions of a moving blade of a turbine and the non-contact displacement sensor of the blade vibration measuring apparatus according to the first embodiment;
    4 is an explanatory view illustrating an arrangement and a block structure of a vane vibration measuring device according to a second embodiment;
    Figs. 5A and 5B are a front view and a side view illustrating an arrangement and a block structure of a vane vibration measuring apparatus according to a third embodiment;
    6A and 6B are a front view and a side view illustrating an arrangement and a block structure of a vane vibration measuring apparatus according to a fourth embodiment;
    Fig. 7 is a graph illustrating a displacement curve showing a shift in a
    Rotation axis direction obtained by a vane vibration measuring apparatus according to a fifth embodiment;
    8 is an explanatory view illustrating an arrangement and a block structure of a vane vibration measuring device according to a sixth embodiment;
    Fig. 9 is a graph showing a method for obtaining a resonance frequency from the output obtained by a vane vibration measuring device according to a seventh embodiment;
    10 is an explanatory view illustrating an arrangement and a block structure of a vane vibration measuring device according to an eighth embodiment;
    11 is an explanatory view and curves showing a method of obtaining a vibration mode number from the output obtained by the vane vibration measuring apparatus according to the eighth embodiment;
    FIG. 12 is an explanatory view illustrating an arrangement and a block structure of a vane vibration measuring apparatus according to a ninth embodiment; FIG.
    13A to 13C are explanatory views showing a method that makes it possible to obtain an output value of a desired size by using a relative angle of a non-contact displacement sensor with respect to a moving blade of a turbine using an angle regulating device in the blade vibration measuring device is regulated according to the ninth embodiment;
    14 is an explanatory view illustrating an arrangement and a block structure of a vane vibration measuring device according to a tenth embodiment;
    Fig. 15 is a block diagram and a front view illustrating a structure of a blade vibration measuring device according to an eleventh embodiment;
    Fig. 16 is a block diagram and a side view illustrating a structure of a blade vibration measuring device according to the eleventh embodiment;
    17A and 17B are explanatory views showing a method for identifying the tip position of a blade according to the eleventh embodiment;
    Figs. 18A and 18B are explanatory views showing a method of calculating a blade vibration amplitude and a vibration frequency according to the eleventh embodiment;
    Figs. 19A and 19B are explanatory views showing a method of performing curve fitting on multiple measurement points of an output signal of a non-contact displacement sensor according to the eleventh embodiment;
    Fig. 20 is a block diagram and a front view illustrating a structure of a vane vibration measuring device according to a twelfth embodiment;
    Fig. 21 is a block diagram and a side view illustrating a structure of a vane vibration measuring device according to the twelfth embodiment;
    Fig. 22 is an explanatory view showing a method of performing curve fitting according to the twelfth embodiment by sorting the peak positions for each blade;
    FIG. 23 is an explanatory view illustrating a structure of a vane vibration measuring apparatus according to a thirteenth embodiment; FIG.
    Figs. 24A and 24B are explanatory views showing a method of measuring displacements of identical points of a moving blade of a turbine using rotation-synchronization pulses according to the thirteenth embodiment;
    Fig. 25 is a graph showing the relationship of the vibration amplitude with respect to frequencies obtained by performing fast Fourier transform on displacement signals at the identical points of the moving turbine blade according to the thirteenth embodiment;
    FIG. 26 is a block diagram showing the result of FIG. 13 according to the thirteenth embodiment
    Fig. 25 is obtained for each revolution speed of the moving turbine blade and is shown with the revolution speed as a horizontal axis and the oscillation frequency as a vertical axis;
    FIG. 27 is an explanatory view illustrating a structure of a vane vibration measuring apparatus according to a fourteenth embodiment; FIG.
    FIG. 28 is a graph showing a shift at the time of occurrence of the resonance mode of the second. FIG
    Shows order, which can be measured by the vane vibration measuring apparatus according to the fourteenth embodiment;
    FIG. 29 is a graph showing a shift at the time of occurrence of the resonance mode of the fourth
    Shows order, which can be measured by the vane vibration measuring apparatus according to the fourteenth embodiment; and
    FIG. 30 is a graph showing a shift at the time of occurrence of the resonance mode of FIG
    Shows order, which can be measured by the vane vibration measuring apparatus according to the fourteenth embodiment;
    Detailed Description Embodiments will now be explained with reference to the accompanying drawings.
    According to the present invention, there is provided a blade vibration measuring apparatus comprising the features of claim 1.
    Shovel vibration measuring apparatuses according to embodiments of the present invention will be described below with reference to the drawings.
    First Embodiment Fig. 1 illustrates a structure of a blade vibration measuring apparatus according to a first embodiment of the present invention: The apparatus is provided with a non-contact displacement sensor 3, a blade tip position identifying device 4, and a blade vibration calculating device 5.
    A single contactless displacement sensor 3 is mounted so as to be close to a moving blade 2 of a turbine in a direction parallel to a rotary shaft 1, and outputs a displacement measurement signal by causing a displacement in the turbine Rotary axis direction of the moving turbine blade 2, which is rotated in a direction which is perpendicular to the paper surface, directly measures.
    The blade tip position identification device 4 obtains the displacement measurement signal output from the non-contact displacement sensor 3, and outputs a blade tip position identification signal indicative of an identification result by performing the identification of a tip position of the blade.
    The blade vibration calculating device 5 calculates a vibration amplitude and a vibration frequency of the moving turbine blade 2 by obtaining the blade tip position identifying signal.
    By using Figs. 2A and 2B, a description can be made of the process of identifying the tip position of the moving turbine blade 2 in the case of using an eddy current displacement sensor 11 as the non-contact displacement sensor 3.
    Since a blade row of the moving turbine blade 2 passes through the area at the front of the eddy current displacement sensor 11 while being rotated and moved in a direction illustrated by an arrow in FIG. 2A, it is possible to move from FIG the eddy current displacement sensor 11 to obtain an output voltage waveform as illustrated in FIG. 2B. Here, a detection position of the moving turbine blade 2 by the eddy current displacement sensor 11 indicated by a square in FIG. 2A corresponds to a position indicated by a square in the output voltage waveform in FIG. 2B.
    Further, peak positions of the moving turbine blade 2 indicated by points 2a1, 2a2, 2a3 in Fig. 2A correspond to lowest peak values of the output voltage waveform indicated by dots 101, 102, 103 in Fig. 2B.
    The blade tip position identification device 4 makes the identification of the tip position of the blade from the peak value of the output voltage waveforms provided by the eddy current displacement sensor 11, and outputs the blade tip position identification signal to provide it to the blade vibration calculation device 5.
    Using FIGS. 3A and 3B, a method of calculating the blade vibration with the blade vibration calculating apparatus 5 will be described.
    As illustrated in FIG. 3A, the distance X from the tip positions of the moving turbine blade 2 indicated by the points 2a1, 2a2, 2a3, 2a4, 2a5, 2a6, 2a7 to the eddy current displacement sensor 11 fluctuates when at the moving turbine blade 2 a vibration occurs. This fluctuation becomes a fluctuation of the lowest peak of the output voltage waveform indicated by the points 101, 102, 103, 104, 105, 106, 107 as described using FIG. 2B. Accordingly, the stress corresponding to the peak position of the blade output from the blade tip position identifying device 4 is converted to a relative distance between the tip position of the blade and the eddy current displacement sensor 11 in the blade vibration calculating device 5, and the obtained relative distance is chronological as illustrated in FIG. 3B Sequence recorded. From the chronological data recorded as described above, the vibration amplitude and vibration frequency of the moving turbine blade 2 can be calculated.
    According to the first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the eddy current displacement sensor.
    In the first embodiment, the eddy current displacement sensor 11 is used as an example of the non-contact displacement sensor 3. However, there is no limitation to the above; only the ability to measure a displacement of the moving turbine blade 2 in a non-contact manner is required. For example, an optical fiber or the like may be used. In the case of using an optical fiber, in contrast to an eddy current displacement sensor, such a relationship occurs that the output becomes larger as the distance to the moving turbine blade decreases.
    Second Embodiment Fig. 4 illustrates a structure of a vane vibration measuring apparatus according to a second embodiment of the present invention. Here, the same structural components as in the above-mentioned first embodiment are given the same reference numerals and their description will not be repeated.
    In the above-mentioned first embodiment, only the non-contact displacement sensor 3 is used. The second embodiment differs from the point that a plurality of non-contact displacement sensors 3 are arranged along a circumferential direction of the moving turbine blade 2.
    Here, as illustrated in FIG. 4, four non-contact displacement sensors 3a, 3b, 3c, 3d are arranged along the circumferential direction of the moving turbine blade 2. In accordance with the device of the four non-contact displacement sensors 3a, 3b, 3c, 3d, four blade tip position identification devices 4a, 4b, 4c, 4d and four blade vibration calculation devices 5a, 5b, 5c, 5d are each arranged in a separate manner. Further, there is provided a vibration mode identification device 6 which identifies a vibration mode number by obtaining blade vibration signals indicative of the vibration amplitude and the vibration frequency of the moving turbine blade 2 from the blade vibration calculation devices 5a, 5b, 5c, 5d.
    The contactless displacement sensors 3a, 3b, 3c, 3d each measure the distance to the rotating moving turbine blade 2, and the obtained displacement measurement signals are respectively input to the corresponding blade tip position identification devices 4a, 4b, 4c, 4d. The blade tip position identification devices 4a, 4b, 4c, 4d respectively output blade tip position identification signals indicating the tip positions of the blade identified respectively based on the voltage waveform of the displacement measurement signal to the corresponding blade vibration calculating devices 5a, 5b, 5c, 5d.
    The blade vibration calculating devices 5a, 5b, 5c, 5d calculate the vibration amplitude and the vibration frequency of the moving turbine blade 2 on the basis of the obtained blade tip position identification signals showing the respective tip positions of the blade, and the obtained result is output to the vibration mode identifying device.
    The vibration mode identification device 6 identifies the vibration mode number of the moving turbine blade based on the vibration amplitude and the vibration frequency detected at the circumferential positions of the moving turbine blade 2 on which the non-contact displacement sensors 3a, 3b, 3c, 3d are arranged second
    According to the second embodiment, similarly to the first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensors. In addition, by using the plurality of non-contact displacement sensors, the vibration mode number can be identified.
    There must be twice as many contactless displacement sensors as the vibration mode number that must be observed. For example, four pieces of non-contact displacement sensors are required to observe a second order mode. Here, the increase in the number of contactless displacement sensors causes an increase in cost because it is necessary to set up the blade tip position identification devices and the blade vibration calculation devices each in the same number as the above. Accordingly, it is necessary to evaluate these costs when setting the vibration mode number whose observation is required.
    Third Embodiment A third embodiment of the present invention will be described using Fig. 5A, which is a front view and a block diagram, and Fig. 5B, which is a side view showing its construction.
    In the first embodiment and the second embodiment described above, the non-contact displacement sensor 3 is mounted so as to be parallel to the rotating shaft 1 of the moving turbine blade 2. In contrast, a third embodiment is characterized in that a single non-contact displacement sensor 3 is arranged on a rotary tool 7 which is perpendicular to the rotary shaft 1 and is capable of being driven so as to rotate coaxially with the rotary shaft 1. Here, the same structural components as in the above-mentioned first and second embodiments are given the same reference numerals and their description will not be repeated.
    Due to the fact that the non-contact displacement sensor 3 is moved while the rotating tool 7 is rotationally driven, vibration of the moving turbine blade 2 can be transmitted through the non-contact displacement sensor 3 at different positions of the moving turbine blade 2 having the same radius to be measured. Specifically, the measurement is performed so that the non-contact displacement sensor 3 is moved to a desired position using the rotary tool 7 while the moving turbine blade 2 is rotating. By the above, the single contactless displacement sensor 3 can provide operations and effects similar to those in the case of measuring vibration at a plurality of positions of the moving turbine blade 2 using a plurality of non-contact displacement sensors 3.
    Similar to the above-mentioned first embodiment, the displacement measurement signal output is provided from the non-contact displacement sensor 3 of the blade tip position identification device 4, and the tip position of the moving turbine blade 2 is identified. Then, the result thereof is provided to the blade vibration calculating device 5 as the blade tip position identifying signal, and the vibration amplitude and vibration frequency of the moving turbine blade 2 are calculated. Further, similarly to the above-mentioned second embodiment, the blade tip position identifying device 4 identifies the tip position of the moving turbine blade 2 by the displacement measuring signal output from the non-contact displacement sensor 3 which is moved to different positions of the moving turbine blade 2 having the same radius. Then, the blade vibration calculating device 5 calculates the vibration amplitude and the vibration frequency, and identifies the vibration mode identification device 6 thereon based on the vibration mode number of the moving turbine blade 2.
    According to the third embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the contactless displacement sensor. And since, similarly to the case of using the plurality of non-contact displacement sensors, it is possible to identify the vibration mode number with the single non-contact displacement sensor, a cost reduction can be achieved.
    Fourth Embodiment A fourth embodiment of the present invention will be described using FIG. 6 showing its structure.
    In the above-mentioned third embodiment, the single non-contact displacement sensor 3 is arranged on the rotary tool 7, which is perpendicular to the rotary shaft 1 and is capable of being driven so as to rotate coaxially with the rotary shaft 1. In contrast, the fourth embodiment is characterized in that on the rotary tool 7, which is perpendicular to the rotary shaft 1 and is capable of being driven so as to rotate coaxially with the rotary shaft 1, a plurality of contactless displacement sensors 3a, 3b, 3c , 3d, 3e, 3f, 3g, 3h are set up. According to the above, the eight non-contact displacement sensors 3a, 3b, 3c, 3d, 3e, 3f, 3g, 3h are respectively provided with eight blade tip position identification devices 4a, 4b, 4c, 4d, 4e, 4f, 4g, 4h and eight blade vibration calculation devices 5a, 5b, 5c , 5d, 5e, 5f, 5g, 5h. In addition, the vibration mode identification device 6 is set up. Here, the same structural components as in the above-mentioned first to third embodiments are given the same reference numerals and their description will not be repeated.
    Of the eight contactless displacement sensors 3a to 3h, displacement signals are outputted at corresponding positions, and blade tip positions are identified by the corresponding blade tip position identification devices 4a to 4h. The result thereof is provided to the blade vibration calculating devices 5a to 5h, and the vibration amplitude and the vibration frequency of the moving turbine blade 2 are calculated; and then by the vibration mode identification device 6, the vibration mode number is identified.
    According to the fourth embodiment, similar to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensors. And, due to the fact that the vibration of the moving turbine blade 2 is measured by the non-contact displacement sensors 3a to 3h at different positions with the same radius while the rotary tool 7 is driven to rotate, effects similar to those in the case of increasing the number of the non-contact displacement sensors 3, while reducing the number of contactless displacement sensors 3 reduces costs.
    In the fourth embodiment, the eight contactless displacement sensors 3a to 3h are set, the respective positions of which are further moved by the rotary tool 7. Accordingly, the vibration mode number which is a fourth-order mode or higher can be detected. Fifth Embodiment A fifth embodiment of the present invention will be described by using Fig. 7 showing its construction.
    The fifth embodiment is configured to include at least two of the non-contact displacement sensors 3 arranged in the structure of the above-mentioned fourth embodiment so as to be juxtaposed along the circumferential direction of the moving turbine blade 2. The rest of the construction is the same as in the above-mentioned fourth embodiment, and its description will not be repeated.
    Due to the fact that at least two of the contactless displacement sensors 3 are located next to each other, in each case measurement signals of shifts are output at two adjacent measuring points to the subsequent corresponding blade tip position identification devices. In a displacement curve showing the displacement in the rotation axis direction indicated by the displacement measurement signal, the two adjacent positions indicated by points 111, 112 are determined as illustrated in FIG. 7. Accordingly, it is possible to identify a displacement curve corresponding to the vibration mode number of the moving turbine blade 2.
    That is, due to the fact that at least two of the non-contact displacement sensors 3 are arranged at a distance on the moving turbine blade 2, which corresponds to a half-cycle of the displacement curve corresponding to a vibration mode number to be measured, it is possible to determine the displacement curve. which corresponds to the vibration mode number of the moving turbine blade 2.
    According to the fifth embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensors. In addition, by juxtaposing at least two of the non-contact displacement sensors 3, the displacement curve corresponding to the vibration mode number can be identified.
    Sixth Embodiment A sixth embodiment of the present invention will be described using FIG. 8 showing its structure.
    A sixth embodiment is characterized in that a rotational speed regulating device 8 is arranged on the rotary shaft 1, and that, in addition to the structure of the above-mentioned first embodiment, a resonance frequency detecting device 12 based on the vibration amplitude and the vibration frequency provided by the blade vibration calculating device 5 be issued, a resonant frequency finds, is set up. The rest of the construction is the same as in the above-mentioned first embodiment, and its description will not be repeated because the same structural components are given the same reference numerals.
    Due to the fact that the resonance frequency detecting device 12 detects the vibration amplitude of the moving turbine blade 2 at the time when the vibration amplitude correspondingly measured and calculated by the blade vibration calculating device 5 becomes maximum, while the rotational speed of the rotary shaft 1 is gradually changed by the rotation speed regulating device 8 is, it is possible to obtain the resonance frequency at the time when a resonance phenomenon occurs on the moving turbine blade 2.
    According to the sixth embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensor. In addition, by setting the revolution speed regulating device on the rotating shaft, the resonance frequency can be obtained.
    Seventh Embodiment Using Fig. 9, a seventh embodiment of the present invention will be described.
    The seventh embodiment has a similar structure to the above-mentioned sixth embodiment illustrated in Fig. 8, and therefore the redundant description will not be repeated.
    In the construction illustrated in Fig. 8, first, the vibration amplitude measured and calculated at the time when the moving turbine blade 2 is rotated at a predetermined revolution speed is stored in the resonance frequency detecting device 12 as a reference vibration amplitude.
    Next, the rotational speed of the rotary shaft 1 is changed by the rotational speed regulating device 8, and the resonance frequency detecting device 12 calculates an amplitude difference value between the reference vibration amplitude and the vibration amplitude measured and calculated at that time. Each time the revolution speed is changed, the amplitude difference value between the reference vibration amplitude and the vibration amplitude at that time must be calculated by the above-mentioned operation. Fig. 9 is a graph showing the amplitude difference values obtained with respect to the rotational speed by points 121, 122, 123, ... as obtained above.
    The resonance frequency of the moving turbine blade 2 can be calculated by the resonance frequency detecting device 12 based on a maximum value indicated in the curve by the point 124 or a minimum value (not illustrated).
    Here, due to the execution of the process for obtaining the above-mentioned amplitude difference value for each turbine blade 2, measurement errors caused by an attachment error and a geometrical error of each turbine blade 2 are canceled out.
    Further, each time the rotational speed of the rotary shaft 1 is changed, the process of obtaining the above-mentioned amplitude difference value is performed in order. Accordingly, measurement errors caused by influences such as thermal expansion of the moving turbine blade 2 that occurs when the revolution speed is changed, expansion due to the centrifugal force, and bending of the moving turbine blade 2 due to the rotation are also canceled out.
    According to the seventh embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensor. In addition, by obtaining amplitude difference values while changing the rotational speed of the rotary shaft 1, the resonance frequency can be obtained.
    Eighth Embodiment An eighth embodiment of the present invention will be described using FIG. 10 showing its structure.
    In an eighth embodiment, in addition to the structure of the second embodiment illustrated in FIG. 4, the revolution speed regulating device 8 is further arranged on the rotating shaft 1.
    Fig. 11 illustrates a state in which a resonance phenomenon occurs on the moving turbine blade 2 while the rotational speed of the rotary shaft 1 is changed by the rotational speed regulating device 8. Here, FIG. 11 schematically illustrates a state of detecting displacements of the moving turbine blade 2 in the rotation axis direction in a third-order resonance mode indicated by a broken line 131 using four non-contact displacement sensors 3a to 3d. At positions where the non-contact sensors 3a and 3c are arranged, the amplitude is almost zero because it corresponds to nodes of vibration. At a position where the non-contact displacement sensor 3b is disposed, the amplitude reaches a maximum value since it corresponds to a vibration antinode. At a position where the non-contact displacement sensor 3d is arranged, the amplitude reaches a minimum value.
    According to the eighth embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensors. In addition, it is possible to identify the resonance mode by disposing the plurality of non-contact displacement sensors at appropriate intervals in the circumferential direction of the moving turbine blade 2, and further to obtain the vibration amplitude at the time when the resonance phenomenon is generated by the rotation speed regulation device 8.
    Ninth Embodiment A ninth embodiment of the present invention will be described using Figs. 12 and 13 which show their construction.
    As illustrated in FIG. 12, a ninth embodiment, in addition to the structure of the first embodiment illustrated in FIG. 1, includes an angle regulating device 9 that regulates an angle of the non-contact displacement sensor 3. The same structural components as in the above-mentioned first embodiment are given the same reference numerals, and their description will not be repeated.
    In general, a non-contact displacement sensor is used to measure a distance to a parallel flat plate, and its output voltage reaches its maximum when a relative angle with respect to a target plane is perpendicular.
    The output voltage obtained when the non-contact displacement sensor 3 has an angle θ1 different from 90 ° with respect to a plane of the moving turbine blade 2 as illustrated in Fig. 13A is shown by the line 131 in Fig. 13C , Further, the output voltage obtained when the non-contact displacement sensor 3 has an angle of 90 ° with respect to the plane of the moving turbine blade 3 as illustrated in FIG. 13B is shown by the line 132 in FIG. 13C. In order to obtain the maximum output voltage as line 132, the non-contact displacement sensor 3 must be arranged at 90 ° with respect to the plane of the moving turbine blade 2.
    For example, in a case where the non-contact displacement sensor 3 is disposed so as to be parallel to the rotation shaft 1, the non-contact displacement sensor 3 is in a state of not being at 90 ° with respect to the plane the moving turbine blade 2 is arranged when the plane of the moving turbine blade 2 is inclined by about 10 ° with respect to the rotary shaft 1.
    Accordingly, the relative angle with respect to the moving turbine blade 2 is set to be 90 degrees by previously regulating the angle of the non-contact displacement sensor 3 using the angle regulating device 9 before the measurement is started.
    According to the ninth embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the non-contact displacement sensor. In addition, the output of the non-contact displacement sensor can be maximized.
    In the ninth embodiment, the angle regulating device 9 can be added not only to the structure of the above-mentioned embodiment but also to the structures of the above-mentioned second to eighth embodiments.
    Tenth Embodiment A tenth embodiment of the present invention will be described by using Fig. 14 showing its structure.
    A tenth embodiment is characterized in that, in addition to the structure of the above-mentioned first embodiment, a distance regulating device 10 is attached to the non-contact displacement sensor 3. Here, the same structural components are given the same reference numerals and their description will not be repeated.
    In general, in a contactless displacement sensor, the magnitude of the output is proportional to a distance with respect to an object, and the measurable distance is determined in advance. Accordingly, as illustrated by an arrow in Fig. 14, the distance X is regulated by moving the non-contact displacement sensor 3 in the rotational axis direction of the moving turbine blade 2 before the measurement is started, so that the desired size of the output can be obtained.
    According to the tenth embodiment, similarly to the above-mentioned first embodiment, the time and the cost necessary for the measurement can be reduced by directly measuring the displacement of the moving turbine blade in the rotation axis direction with the contactless displacement sensor. In addition, it is possible to regulate the distance between the moving turbine blade 2 and the non-contact displacement sensor 3 so that the desired size of the output can be obtained from the non-contact displacement sensor 3.
    In the tenth embodiment, the gap adjusting device 10 may be added not only to the structure of the above-mentioned embodiment but also to the structures of the above-mentioned second to ninth embodiments.
    Eleventh Embodiment Fig. 15 is a. 16 is a side view of a moving turbine blade 202 illustrating a structure of an eleventh embodiment of the present invention.
    In order to measure displacements in a rotational axis direction of the moving turbine blade 202 attached to a rotating shaft 201, a plurality of non-contact displacement sensors 203a, 203b, 203c, 203d are arranged at predetermined intervals in a circumferential direction of the moving turbine blade 202 at the same radius.
    Shift measurement signals output from the respective contactless displacement sensors 203a, 203b, 203c, 203d are input to corresponding blade tip position identification devices 204a, 204b, 204c, 204d. Then, the identification of the tip positions of the turbine blade 202 is performed, and blade tip position identification signals indicating their result are output.
    The peak position identification signals are provided to corresponding blade vibration calculating devices 205a, 205b, 205c, 205d, and the vibration amplitude and a vibration frequency of the moving turbine blade 202 are calculated and output to a vibration mode identifying device 206.
    In the vibration mode identification device 206, a vibration mode number is obtained based on the vibration amplitude and the vibration frequency at each arrangement position of the non-contact displacement sensors 203a, 203b, 203c, 203d.
    Here, a method of identifying the blade tip positions in the blade tip position identification devices 204a, 204b, 204c, 204d will be described using FIGS. 17A and 17B.
    As illustrated in FIG. 17A, a blade row of the moving turbine blade 202 is rotated and moved in a direction shown by an arrow. Due to the fact that the blade row of the moving turbine blade 202 passes through the front-side area of, for example, the non-contact displacement sensor 203a below the non-contact displacement sensors 203a, 203b, 203c, 203d, a non-contact displacement sensor 203a transmits a displacement measurement signal having a position as shown in FIG. 17B illustrated voltage waveform. Here, a detection position of the moving turbine blade 202 indicated by a square in FIG. 17A by the non-contact displacement sensor 203a corresponds to a position indicated by a square in the output voltage waveform in FIG. 17B.
    Further, peak positions of the moving turbine blade 202 indicated by points 202a1,202a2, 202a3 in Fig. 17A correspond to lowest peak values of the output voltage waveform indicated by dots 301, 302, 303 in Fig. 17B.
    Using FIGS. 18A and 18B, a method for calculating the vibration amplitude and the vibration frequency of the turbine blade 202 with the blade vibration calculating device 205 will be described.
    As illustrated in FIG. 18A, the distance X from the tip positions of the moving turbine blade 202 indicated by the points 202a1,202a2, 202a3, 202a4, 202a5, 202a6, 202a7 to the contactless displacement sensor 203a varies when on the moving turbine blade 202 a vibration occurs. This oscillation becomes the oscillation of the lowest peak value of the output voltage waveform described by using FIG. 17B indicated by the points 301, 302, 303, 304, 305, 306, 307. Accordingly, the tension corresponding to the blade tip position output from the blade tip position identifying device 204a in the blade vibration calculating device 205a is converted into a relative distance between the blade tip position and the non-contact displacement sensor 203a, and the resulting relative distance is recorded in chronological order as shown in Fig. 18B. From the chronological data recorded as described above, the vibration amplitude and vibration frequency of the moving turbine blade 202 can be calculated.
    Further, the eleventh embodiment is characterized in that curve fitting is performed at the time of identifying tip positions of the moving turbine blade 202 in the blade tip position identification devices 204a, 204b, 204c, 204d, respectively.
    In Fig. 19A, the distance to the moving turbine blade 202 (for example, by the non-contact displacement sensor 203a) is measured below the non-contact displacement sensors 203a, 203b, 203c, 203d. Distances to non-continuous vane measurement positions 202a11,202a12, 202a13, 202a15 corresponding to the sampling timing at the moving turbine bucket 202 are measured when the moving turbine bucket 202 passes through the area at the front of the non-contact displacement sensor 203a, and displacement measurement signals are output ,
    When the displacement measurement signals are input to the blade tip position identifying device 204a, measured values at the non-continuous measuring positions 202a11, 202a12, 202a13, 202a15 are sampled and stored.
    Then, due to the fact that, for example, using the least-squares method or the like to curve-interpolate between these positions by means of measurement values at the respective blade-measuring positions 202a11, 202a12, 202a13, 202a15, a curve fitting is made, such as by obtained a dashed line illustrated curve S. From the peak of the curve S, a calculated blade tip identification position 202a14 is obtained.
    When the rotational speed of the moving turbine blade 202 becomes high, it becomes difficult to perform blade tip position identification using a non-contact displacement sensor. Accordingly, voltage values of displacement measurement signals are obtained by being scanned by the non-contact displacement sensor at a plurality of measurement positions near the blade tip, and curve fitting is made at these values. It is possible to improve the accuracy of the blade tip position identification by identifying the peak value of the curve S obtained as described above as the blade tip position. Although the accuracy of the blade tip position identification is improved with an increase in the sampling frequency, the sampling frequency can be set to be on the order of several hundred kHz, for example, in consideration of the processing time and the cost of increasing the processing amount.
    According to the eleventh embodiment, the time and the cost necessary for the measurement can be reduced by accurately measuring the displacement of the blade in the rotation axis direction instead of measuring the blade passage timing at a response frequency of the order of several hundred kHz ,
    Here, for performing the curve-fitting on measured values, data indicating a profile of the moving turbine blade 202 is stored in advance in a memory unit (not shown) or the like, and the curve fitting is performed using the data, so that the curve profile the moving turbine blade 202 can be accurately preserved. And although the shape of the moving turbine blade 202 changes according to the operating state, the identification of the blade tip position can be further performed by storing profile data in each operating state so that the curve profile is obtained more accurately.
    Twelfth Embodiment Fig. 20 is a front view, and Fig. 21 is a side view of the moving turbine blade 202 in illustrating a structure of a twelfth embodiment of the present invention.
    The twelfth embodiment differs from the above-mentioned structure of the eleventh embodiment in the point that a rotation speed regulating device 208 is further arranged to change the rotational speed of the rotary shaft 201. The same structural components as in the above-mentioned eleventh embodiment are given the same reference numerals, and their description will not be repeated.
    When the rotation shaft 201 is rotated at a predetermined revolution speed, the identification of the blade tip position of the moving turbine blade 202 is performed in each of the blade tip position identification devices 204a, 204b, 204c, 204d, and the blade tip position identification signals are output. Similar to the above-mentioned eleventh embodiment, the blade tip position identifying signals are provided to the corresponding blade vibration calculating devices 205a, 205b, 205c, 205d, and the vibration amplitude and vibration frequency of the moving turbine blade 202 are calculated and output to the vibration mode identifying device 206.
    The vibration mode identification device 206 obtains the vibration amplitude and the vibration frequency from the blade vibration calculation devices 205a, 205b, 205c, 205d, and obtains the displacement measurement signals output from the non-contact displacement sensors 203a, 203b, 203c, 203d.
    In the vibration mode identification device 206, data indicating the blade tip positions contained in the displacement measurement signals is sorted for each blade of the moving turbine blade 202, and a determination of the resonance mode number is performed. Specifically, for each blade, displacement measurement values obtained while the blades are sequentially passed through the area at the front of the respective non-contact displacement sensors 203a, 203b, 203c, 203d are collected.
    When a resonance phenomenon occurs while the rotational speed of the rotary shaft 201 is changed by the rotational speed regulating device 208, as shown in Fig. 22, a curve is obtained in which the displacement regularly changes while a certain blade makes one revolution. A curve of the displacement change is approximated to a sinusoid. In the vibration mode identification device 206, curve fitting is performed on the non-continuous displacement measurement values obtained by sampling, and the resonance mode is identified.
    In this way, the cost required for the measurement can be reduced since the number of non-contact displacement sensors 203 can be reduced by performing curve fitting to a sinusoid in a resonance state on the non-continuous measurement values.
    According to the twelfth embodiment, similarly to the above-mentioned eleventh embodiment, the time and the cost necessary for the measurement can be reduced by shifting the blade in the rotational axis direction instead of measuring the blade passage timing at a response frequency in FIG of the order of a few hundred kHz is measured accurately. In addition, performing curve fitting on the non-continuous displacement measurements into a sine curve in a resonant state may contribute to cost reduction by reducing the number of contactless displacement sensors 203.
    Thirteenth Embodiment Using Fig. 23, a thirteenth embodiment of the present invention will be described. Sixteen contactless displacement sensors 203a, 203b, 203c, ..., 203p are disposed along the circumferential direction of the moving turbine blade 202.
    Further, a rotation synchronization pulse generating device 211 is set at a predetermined position of the moving turbine blade 202. Each time any blade of the moving turbine blade 202 passes through the predetermined position, a rotational synchronization pulse is generated and provided to the respective non-contact displacement sensors 203a, 203b, 203c, ... m 203p.
    According to the above, in the non-contact displacement sensors 203a, 203b, 203c, 203p, the displacement measurement signals indicative of a distance (displacement) to the rotary moving turbine blade at the time of receiving the rotation-synchronization signal are generated and output.
    The output displacement measurement signals are respectively provided to the same number of blades 212a, 212b, 212c, ..., 212p for measuring an identical point of the blade, which correspond to the non-contact displacement sensors 203a, 203b, 203c, ..., 203p , In the devices 212a, 212b, 212c, ..., 212p for measuring an identical point of the blade, distances to identical points of the rotating moving turbine blade 202 are measured based on the displacement measurement signals, and signals of the displacement of the identical point are output. In this way, the signals of the displacement of the identical point are respectively output from the apparatuses 212a, 212b, 212c, ..., 212p for measuring an identical point of the bucket and provided to a bucket reference sorter 213.
    In the bucket elevator sorter 213, the provided sixteen identical point shift signals for each bucket of the moving turbine bucket 202 are sorted and output as a chronological shift signal to be provided to an FET calculator 214.
    The FET calculator 214 performs a fast Fourier transform on the chronological shift signal sorted according to each blade. The obtained result is provided as a fast Fourier transform result signal of a Campbell chart generator 215.
    The Campbell diagram generator 26 generates a Campbell diagram described below using FIG. 26 based on the signal of the fast Fourier transform result signal, and evaluates vibration characteristics of the moving turbine blade 202. The result thereof becomes output as evaluation result signal to the outside.
    As illustrated in FIG. 24A, displacements of identical points 202a1, 202a2, 202a3 of the respective blades of the moving turbine blade 202 must be measured. Accordingly, displacements of the points 301, 302, 303 corresponding to the identical points 202a1, 202a2, 202a3 of the respective blades in the displacement measurement signals outputted from the non-contact displacement sensors 203a, 203b, 203c, ..., 203p, as in FIG Fig. 24A illustrates using rotation sync pulses. According to the above, displacements of the identical points of the respective blades in the devices 212a to 212p for measuring an identical point of the blade are measured.
    Then, the measurement is performed while the revolution speed is gradually increased by the revolution speed regulation device 208, and a resonance point and a resonance mode are to be obtained.
    In general, 2 x N pieces of sensors are needed to measure an N-th order resonance mode (N is a positive integer). In the thirteenth embodiment, since the sixteen non-contact displacement sensors 203a to 203p are used, resonance modes up to the eighth order can be detected.
    Fig. 25 shows the relationship of the vibration amplitude with respect to frequencies obtained by performing fast Fourier transform with the FET calculator 214 on the displacement measurement signals generated by the bucket reference sorter 213 at the identical points of the moving turbine bucket 202. The resonance point is designated by a time with the maximum vibration amplitude, and the frequency at this point is the resonance frequency.
    The fast Fourier transform described above must be performed for each revolution speed of the moving turbine blade 202. The result obtained is illustrated in Fig. 26 as a Campbell diagram represented in a curve with the rotational speed as a horizontal axis and the vibration frequency as a vertical axis.
    The Campbell diagram illustrates lines each connecting a predetermined one of the respective rotation frequencies. For example, the line 201Η (H is a positive integer) denotes a line connecting simple frequencies of the rotation frequencies, the line 202H denotes a line connecting two times frequencies of the rotation frequencies, ... the line 208H denotes a line that eight times the frequencies of rotation frequencies connects.
    Further, the sizes of white circles illustrated in the Campbell diagram are proportional to the magnitude of the vibration amplitude. Accordingly, the magnitudes of a set of white circles perpendicularly aligned in FIG. 26 correspond respectively to the vibration amplitude of 201H to 208H at a predetermined rotational speed, and corresponds to a set of the vibration amplitude illustrated in the graph of FIG. 25 at the predetermined rotational speed ,
    In the Campbell diagram generated by the Campbell diagram generator 215 as described above, the oscillation frequency at which the oscillation amplitude becomes large irrespective of the revolution speed is set as the resonance frequency at the resonance point.
    According to the thirteenth embodiment, similarly to the above-mentioned eleventh embodiment, the time and cost necessary for the measurement can be reduced by shifting the blade in the rotation axis direction instead of measuring the blade passage timing at a response frequency in the rotational axis direction Of the order of a few hundred kHz is measured accurately. In addition, by generating a Campbeil diagram, the resonance frequency can be obtained.
    Fourteenth Embodiment Using Figs. 27 to 30, a fourteenth embodiment of the present invention will be described.
    A fourteenth embodiment has a structure illustrated in FIG. 27. Along the circumferential direction of the moving turbine blade 202, a first non-contact displacement sensor 203a is disposed, and when a second non-contact displacement sensor 203b is disposed at an angular interval of 22.5 ° from the first non-contact displacement sensor 203a, a third non-contact displacement sensor 203c is spaced 45 degrees apart Further, a fourth non-contact displacement sensor 203d is disposed at a distance of 90 ° from the first non-contact displacement sensor 203a.
    The displacement measurement signals outputted from the non-contact displacement sensors 203a, 203b, 203c, 203d are provided to the blade tip position identification devices 204a, 204b, 204c, 204d respectively adapted thereto where each identification of a blade tip position is performed. The result thereof is output as the blade tip position signals to the blade vibration calculating devices 205a, 205b, 205c, 205d, respectively.
    In the blade vibration calculating devices 205a, 205b, 205c, 205d, the vibration amplitude and the vibration frequency of the moving turbine blade 202 are calculated based on the blade tip position identifying signals. The result thereof is provided to the vibration mode identification device 206 as the blade vibration signal.
    The vibration mode identification device 206 identifies the vibration mode based on the vibration amplitude and the vibration frequency at positions where the non-contact displacement sensors 203a to 203d are located.
    In Fig. 28, black circles indicate displacements which, in the case of occurrence of a second-order resonance mode, are respectively arranged by the contactless displacement sensors 203a to 203d disposed at the above-mentioned angular intervals in the circumferential direction of the moving turbine blade 202 are to be measured. Also, displacements respectively measured by the contactless displacement sensors 203a to 203d are indicated in Fig. 29 in the case of occurrence of a fourth order resonance mode and Fig. 30 in the case of occurrence of an eighth order resonance mode.
    In the second order resonance mode shown in FIG. 28, the positions of the contactless displacement sensors 203a to 203d are correspondingly displaced from the measurement points 401, 402, 403 at the positive side and the measurement point 404 is at the negative side.
    In the fourth-order resonance mode shown in FIG. 29, according to the disposition positions of the contactless displacement sensors 203a to 203d, according to displacements of the measuring points 401, 402 on the positive side, there is a displacement of the measuring point 403 on the negative side, and further a shift of the measuring point 404 on the positive side.
    In the eighth-order resonance mode shown in FIG. 30, according to the arrangement positions of the non-contact displacement sensors 203a to 203d, a displacement of the measuring point 401 on the positive side, a displacement of the measuring point 402 on the negative side, a displacement of the measuring point 403 on the positive side and a displacement of the measuring point 404 on the positive side.
    权利要求:
    Claims (14)
    [1]
    In this way, it is possible to easily determine which resonance mode occurs. Here, in order to detect a resonance mode up to the eighth order, the minimum distance of the arrangement of the non-contact displacement sensors 203a to 203d is set to 22.5 °, that is, a half cycle of the eighth order resonance mode. Due to this arrangement with the above intervals, a vibration node can be stably detected in the eighth order vibration mode. Further, due to the fact that the non-contact displacement sensors 203a to 203d are arranged at intervals which are equal multiples of the minimum distance of 22.5 °, a vibration node of a vibration mode of a lower order can be detected. According to the fourteenth embodiment, the resonance mode number can be effectively detected while reducing the number of non-contact displacement sensors as compared with a case where the non-contact displacement sensors are arranged at regular intervals in the circumferential direction. Accordingly, it is possible to contribute to a cost reduction. Although particular embodiments have been described, these embodiments have been shown by way of example only and are not intended to limit the scope of the inventions. claims
    A vane vibration measuring apparatus comprising: at least one non-contact displacement sensor that outputs a displacement measurement signal by measuring a displacement of a moving turbine blade in a rotation axis direction; at least one blade tip position identification device that outputs a blade tip position identification signal based on a distance between the non-contact displacement sensor and the moving tip of the turbine blade to identify that position by obtaining the displacement measurement signal output from the non-contact displacement sensor; and at least one blade vibration calculating device that can calculate a vibration amplitude and a vibration frequency of the moving turbine blade based on the variation of the distance between the non-contact displacement sensor and the tip position of the moving turbine blade with time by registering the blade tip position identification signal output from the blade tip position identifying device able, wherein at least one blade tip position identification device is able to create a curve by means of interpolation with the aid of at least one blade calculating device.
    [2]
    2. The blade vibration measuring device according to claim 1, wherein a plurality of non-contact displacement sensors are arranged along a circumferential direction of the moving turbine blade; a plurality of blade tip position identification devices and blade vibration calculation devices are linked so as to correspond with the respective non-contact displacement sensors; and further provided is a vibration mode identification device that is capable of identifying a vibration mode number of the moving turbine blade based on the vibration amplitude and vibration frequency of the moving turbine blade calculated by each of the blade vibration calculation devices.
    [3]
    3. The blade vibration measuring apparatus according to claim 1, wherein a single non-contact displacement sensor is disposed, further comprising: a holding device that guides the non-contact displacement sensor of constant radius in the circumferential direction of the moving turbine blade; and a vibration mode identification device that is capable of determining a vibration mode number of the moving turbine blade based on the vibration amplitude and the vibration frequency of the moving turbine blade calculated by the blade vibration calculation device for each position of the rotationally moving non-contact displacement sensor.
    [4]
    4. The blade vibration measuring device according to claim 1, wherein a plurality of non-contact displacement sensors are arranged along a circumferential direction of the moving turbine blade, further comprising: a holding device that moves the non-contact displacement sensors each rotating with a uniform radius in the circumferential direction of the moving turbine blade; and a vibration mode identification device that is capable of determining a vibration mode number of the moving turbine blade based on the vibration amplitude and vibration frequency of the moving turbine blade calculated by the blade vibration calculation device for each position of the plurality of non-contact displacement sensors rotatably moved by the holding device.
    [5]
    5. The blade vibration measuring device according to claim 4, wherein at least two of the plurality of non-contact displacement sensors are arranged to be adjacent in the circumferential direction of the moving turbine blade; and based on the displacement measurement signals output from the at least two non-contact displacement sensors, a displacement curve of the moving turbine blade in the rotation axis direction is determinable.
    [6]
    A blade vibration measuring apparatus according to claim 1, further comprising: a revolution speed regulating device by means of which the rotational speed of the moving turbine blade is changeable; and a resonance frequency detecting device, by which a resonance frequency is obtainable in a resonance state in which the vibration amplitude of the moving turbine blade calculable by the blade vibration calculation device becomes maximum while the rotational speed of the moving turbine blade is changeable by the rotation speed regulation device.
    [7]
    The bucket vibration measuring apparatus according to claim 6, wherein the vibration amplitude calculated by the blade vibration calculating device when the moving turbine blade is rotated by the revolution speed regulating device at a predetermined revolution speed is stored in the resonance frequency determining device as a reference vibration amplitude; and by the resonance frequency detecting device based on an amplitude difference value between the reference vibration amplitude and the vibration amplitude calculable by the blade vibration calculating device when the moving turbine blade is rotated by the revolution speed regulating device at a rotational speed different from the predetermined rotational speed, a resonance frequency is obtainable.
    [8]
    8. The blade vibration measuring apparatus according to claim 2, further comprising a rotational speed regulating device capable of varying the rotational speed of the moving turbine blade, wherein by the vibration mode identifying device, the vibration mode number in a resonant condition of the moving turbine blade based on the one in the resonant state in which the blade computationally calculable by the blade vibration calculating devices Oscillation amplitude of the moving turbine blade is maximum while the rotational speed of the moving turbine blade is changeable by the rotational speed regulating device identifiable by each vibration amplitude of the moving turbine blade calculated by the blade vibration calculating devices and displacement of the moving turbine blade in the rotational axis direction detected by each of the non-contact displacement sensors is ficable.
    [9]
    The bucket vibration measuring apparatus according to any one of claims 1 to 8, further comprising an angle regulating device capable of regulating a relative angle of the non-contact displacement sensor with respect to the moving turbine bucket.
    [10]
    The vane vibration measuring apparatus according to any one of claims 1 to 9, further comprising a distance regulating device capable of regulating a relative distance of the non-contact displacement sensor with respect to the moving turbine blade.
    [11]
    11. The blade vibration measuring device according to claim 1, comprising: a plurality of non-contact displacement sensors arranged along a circumferential direction of a moving turbine blade and outputting displacement measurement signals by measuring each displacement of the moving turbine blade in a rotation axis direction; a plurality of blade tip position identification devices arranged corresponding to the non-contact displacement sensors and outputting the displacement measurement signals based on each distance between the non-contact displacement sensors and the tip position of the moving turbine blade to identify a tip position by obtaining the corresponding displacement measurement signals output from the non-contact displacement sensors; a plurality of blade vibration calculating apparatuses arranged corresponding to the non-contact displacement sensors and calculating a vibration amplitude and a vibration frequency of the moving turbine blade based on the time variation of the distance between the non-contact displacement sensors and the tip position of the moving turbine blade by detecting the blade tip position identification signals output from the blade tip position identifying devices receive; and a vibration mode identification device that identifies a vibration mode number of the moving turbine blade based on the vibration amplitude and vibration frequency of the moving turbine blade output from each of the blade vibration calculation devices, each of the blade tip position identification devices being given a curve by intercepting a curve fitting shifts at the plurality of measurement points by mutual interpolation; which are included in the received displacement measurement signal, and identifies a peak position of the moving turbine blade from a peak position of the curve.
    [12]
    12. The blade vibration measuring apparatus according to claim 11, further comprising a revolution speed regulating device that varies the revolution speed of the moving turbine blade, wherein the vibration mode identifying device collects the blade tip position identifying signals identified by the blade tip position identifying devices by sorting them for each blade of the moving turbine blade and identifies a resonance mode number a resonance phenomenon occurs on the moving turbine blade while the rotational speed of the moving turbine blade is changed by the revolution speed regulating device.
    [13]
    13. The blade vibration measuring device according to claim 11, wherein the plurality of non-contact displacement sensors arranged along the circumferential direction of the moving turbine blade comprises at least a first, second, third and fourth non-contact displacement sensor; the second non-contact displacement sensor is disposed at a position having a predetermined distance to the extent of a half cycle of a predetermined order resonance mode with respect to the first non-contact displacement sensor, the third non-contact displacement sensor is disposed at a position relative to the first non-contact displacement sensor has twice the pitch, and the fourth non-contact displacement sensor is disposed at a position four times as long with respect to the first non-contact displacement sensor.
    [14]
    A bucket vibration measuring apparatus according to claims 6 and 7, comprising a rotation speed regulating device capable of changing the rotational speed of a moving turbine bucket, a rotation synchronizing pulse generating device capable of outputting a rotation synchronizing pulse each time each bucket of the moving turbine bucket passes through a predetermined position; a plurality of non-contact displacement sensors disposed along a circumferential direction of the moving turbine blade and outputting the displacement detection signals by being capable of measuring displacement of the moving turbine blade in a rotation axis direction at the time the rotation synchronization pulse is provided, respectively; a plurality of turbine blade identical point measurement devices aligned with the non-contact displacement sensors and outputting the identical point shift signals corresponding to the rotation synchronizing pulses indicating respective distances between the non-contact displacement sensors and identical points of the moving turbine blade; by having received the corresponding displacement measurement signals output from the non-contact displacement sensors; a bucket reference sorting device which obtains the signals of the displacement of the identical point output from the identical point measuring means, respectively, and which outputs a chronological shift signal sorted correspondingly for each blade of the moving turbine bucket; an FFT calculating device which obtains the chronological shift signal output from the bucket reference sorter, and outputs a fast Fourier transform result signal after having performed a fast Fourier transform; and a Campbell diagram generating device which obtains the fast Fourier transform result signal output from the FFT calculating device, and which is capable of evaluating the vibration characteristics of the moving turbine blade by generating a Campbeil diagram.
    类似技术:
    公开号 | 公开日 | 专利标题
    CH705536B1|2017-09-29|Blade vibration measuring device.
    DE69924609T2|2006-03-02|METHOD AND SYSTEM FOR PERFORMANCE TESTING OF ROTATING MACHINES
    DE112009002248T5|2011-09-29|Synthesized synchronous sampling and acceleration envelope formation for a differential storage damage signature
    DE102008057556A1|2010-05-20|Method and device for crack detection on compressor blades
    DE102008010916A1|2009-08-27|Method and device for determining an orientation of two rotatably mounted machine parts, an alignment of two hollow cylindrical machine parts or for testing a component for straightness along a longitudinal side
    EP2526429A1|2012-11-28|Method for detecting the rotation and direction of rotation of a rotor
    DE19828498C2|2001-07-05|Method for measuring unbalance of rotating bodies and device for carrying out the method
    DE3209435A1|1982-10-07|DEVICE FOR DETERMINING POINTAL SHIFTINGS ON APPROPRIATE STRUCTURES
    EP2728128A1|2014-05-07|Measuring method for detecting damage to a turbine blade and turbine
    EP3296715B1|2019-09-04|Method for generating data for a rotor blade for a wind turbine
    EP2203730A2|2010-07-07|Measuring device for detecting the operating state of a shaft, method and shaft arrangement comprising said measuring device
    DE102011083858A1|2013-04-04|Method and arrangement for monitoring gears in operation
    DE102016204269B3|2017-06-22|Method for equalizing torque outputs of at least two cylinders of an internal combustion engine
    EP3581328B1|2020-04-15|Machine-tool unit with runout error control and testing method of the tensioning state
    DE102019106903A1|2019-10-10|Determination of the engine speed on the basis of vibration spectral diagrams
    DE102008057508B4|2018-11-29|Method for detecting misfiring in an internal combustion engine
    DE102009009714A1|2010-12-02|Device for determining torque at turbine shaft in e.g. aircraft engine, has sensors producing alternating signals, which enable measurement of phase positions and/or processing time, where signal form of signals enable distance measurement
    DE102014103829A1|2014-10-02|Calculating device, calculating method and calculating program for a position of a driving element
    DE102017104414B3|2018-07-19|Method and apparatus for determining an indicator for predicting instability in a compressor and use
    DE102016200690A1|2017-07-20|Method for non-destructive surface testing of a component with an eddy current probe
    DE102017112776A1|2018-12-13|Method and apparatus for dynamic load testing
    DE10122135A1|2002-11-14|Process for balancing rotors
    DE102021200210A1|2021-07-22|Early Sign Detection Apparatus and Early Sign Detection Method
    DE102019105233A1|2020-09-03|Method and device for calibrating strain gauges
    DE10218332B4|2005-06-16|Method for analyzing vibrations of rotating or oscillating parts
    同族专利:
    公开号 | 公开日
    US20130247671A1|2013-09-26|
    DE102012216160A1|2013-03-14|
    US9057682B2|2015-06-16|
    CH705536A2|2013-03-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3929008A|1974-12-31|1975-12-30|Boris Nikolaevich Zlotin|Apparatus for measuring amplitude of vibration of rotating machine parts|
    JPH068752B2|1986-06-04|1994-02-02|株式会社日立製作所|Method of analyzing and processing vibration data during rotation of blade|
    FR2695205B1|1992-09-03|1994-11-18|Europ Propulsion|Method and device for measuring vibration of turbine blades in operation.|
    JPH0727601A|1993-07-12|1995-01-31|Mitsubishi Heavy Ind Ltd|Method and apparatus for measuring vibration in non-contact|
    JP2941613B2|1993-08-23|1999-08-25|三菱重工業株式会社|Rotor blade vibration measurement device|
    JPH0882547A|1994-09-12|1996-03-26|Mitsubishi Heavy Ind Ltd|Wing-vibration measuring apparatus|
    JPH1068654A|1996-08-27|1998-03-10|Mitsubishi Heavy Ind Ltd|Measuring device of vibration of rotor|
    JP3137589B2|1996-11-19|2001-02-26|三菱重工業株式会社|Rotor blade vibration measurement detector mounting jig|
    JP3129406B2|1997-07-11|2001-01-29|三菱重工業株式会社|Wing vibration measurement device|
    JP3038382B1|1999-05-12|2000-05-08|科学技術庁航空宇宙技術研究所長|Rotating blade vibration measurement device|
    JP3530474B2|2000-09-22|2004-05-24|三菱重工業株式会社|Wing vibration measurement method and wing vibration monitoring system using the same|
    GB2374670B|2001-04-17|2004-11-10|Rolls Royce Plc|Analysing vibration of rotating blades|
    JP2003177059A|2001-12-12|2003-06-27|Toshiba Corp|Method and apparatus for measuring vibration|
    JP4105692B2|2002-08-12|2008-06-25|新川センサテクノロジ株式会社|Vibration information transmitting apparatus and vibration monitoring analysis system|
    US8096184B2|2004-06-30|2012-01-17|Siemens Energy, Inc.|Turbine blade for monitoring blade vibration|
    DE102006060650A1|2006-12-21|2008-06-26|Mtu Aero Engines Gmbh|Device and method for contactless blade vibration measurement|
    US9557210B2|2007-02-02|2017-01-31|The Secretary, Department Of Atomic Energy, Govt. Of India|Method for non-intrusive on-line detection of turbine blade condition|
    GB0712926D0|2007-07-04|2007-08-15|Qinetiq Ltd|Eddy current sensors|
    GB0822859D0|2008-12-16|2009-01-21|Rolls Royce Plc|Timing analysis|
    GB2466817B|2009-01-09|2010-12-08|Rolls Royce Plc|Determination of blade vibration frequencies and/or amplitudes|
    JP2011199452A|2010-03-18|2011-10-06|Fuji Xerox Co Ltd|Processor and control program|
    JP2011224050A|2010-04-16|2011-11-10|Maruhon Industry Co Ltd|Pachinko machine|FR3015671B1|2013-12-23|2020-03-20|Safran Helicopter Engines|ASSEMBLY FOR A TURBOMACHINE FOR MEASURING VIBRATIONS SUBJECT TO A ROTATING BLADE|
    FR3015673B1|2013-12-23|2015-12-18|Turbomeca|TURBOMACHINE ASSEMBLY FOR MEASURING VIBRATIONS SUBJECTED BY A ROTATING BLADE|
    US10416306B2|2015-08-17|2019-09-17|Texas Instruments Incorporated|Methods and apparatus to measure and analyze vibration signatures|
    US10480535B2|2017-03-22|2019-11-19|Pratt & Whitney Canada Corp.|Fan rotor with flow induced resonance control|
    US10458436B2|2017-03-22|2019-10-29|Pratt & Whitney Canada Corp.|Fan rotor with flow induced resonance control|
    US10823203B2|2017-03-22|2020-11-03|Pratt & Whitney Canada Corp.|Fan rotor with flow induced resonance control|
    CZ2017665A3|2017-10-18|2019-01-02|Ăšstav termomechaniky AV ÄŚR, v. v. i.|Method of identification of ferromagnetic blades of a machine under rotation|
    法律状态:
    2017-06-30| PK| Correction|Free format text: BERICHTIGUNG ERFINDER |
    2020-10-15| PFA| Name/firm changed|Owner name: KABUSHIKI KAISHA TOSHIBA, JP Free format text: FORMER OWNER: KABUSHIKI KAISHA TOSHIBA, JP |
    优先权:
    申请号 | 申请日 | 专利标题
    JP2011199452A|JP5701723B2|2011-09-13|2011-09-13|Wing vibration measuring device|
    JP2011224050A|JP2013083568A|2011-10-11|2011-10-11|Blade vibration measuring device|
    [返回顶部]