An operating turbine non order-related blade monitor

Abstract: An operating turbine monitor is described incorporating one or more acoustic sensors (76,77) positioned next to a blade row (25) of a rotor, an analog digital converter (90), a tachometer sensor (70) at the rotor shaft (20), a memory (92), a synchronous averaging circuit (100), a subtractor circuit (108), and a comparator (114). The invention overcomes the problem of monitoring an operating turbine for order-related turbine blade vibration and for non order-related turbine blade vibration as well as for other turbine conditions.

Description: BACKGROUND OF THE INVENTION Field of the Invention This invention relates to monitoring the vibration of turbine blades in an operating turbine and more particular to detecting and locating non order-related vibrating turbine blades. Description of the Prior Art In U.S.A. Patent 4,422,333 by R.L. Leon, the inventor herein, and which issued on December 27, 1983, a method and apparatus was described for detecting and identifying one or more excessively vibrating blades of the rotating portion of a turbomachine. An acoustic sensor was positioned to receive a characteristic Doppler waveform that resulted when a blade or blade group vibrates resonately at an order of running speed. The method described in the '333 patent for constant speed turbines, involved synchronous averaging out the non order- related background noise followed by editing or blanking out the few order related components known to be contaminated with background error such as blade passing frequency and once-per-revolution and twice-per-revolution frequencies. The resulting signal is then displayed to reveal the characteristic Doppler waveform of the blade vibrations. An envelope detection technique was employed to accurately pick out the amplitude peak indicative of the location of the resonant blade. It was discovered that in some steam power turbines that the order related background error was not limited to just a few order-related components, but instead was spread broadly across all the order related components. Blanking all of the offending order-related background components would, of course, eliminate entirely the sought after Doppler waveform. SUMMARY OF THE INVENTION In accordance with the present invention, a method and apparatus is provided for detecting a non order-related vibrating blade attached to the shaft of a rotating rotor in an operating turbine as defined in claims 1 and 2. It is an object of the invention to detect non order-related or fluttering turbine blades by processing the data obtained from many revolutions with the data obtained from a few revolutions. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a pictorial and schematic diagram of a two flow tandem compound turbine. Fig. 2 is a cross section view along the lines 2-2 of Fig. 1. Figs. 3 and 4 show one turbine blade of a blade row vibrating at a first and at a fourth resonant frequency respectively. Figs. 5 and 6 show one turbine blade of a blade row vibrating at first and fourth resonant frequencies shifted in phase respectively. Fig. 7 is one embodiment of the invention. DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring to Fig. 1, a pictorial and schematic diagram of a two flow tandem compound turbine 14 is shown. Compound turbine 14, as shown in Fig. 1, has a high pressure turbine 16, an intermediate pressure turbine 17 and two low pressure turbines 18 and 19 having a common shaft 20 which is cylindrical in shape for receiving and transmitting to a load, for example an electrical generator, torsional load forces and power. Shaft 20 is supported and held in place by bearings 21-24. Bearings 21-24 are held in place by suitable support fixture for holding bearings 21-24 firmly in place and supporting the weight on shaft 20 as well as shaft 20. Attached or secured to shaft 20 in high pressure turbine 16 are blade rows 25-28. Each blade row, for example blade row 25, comprises a plurality of blades, for example, 100, extending radially from shaft 20. A housing 29 encloses blade rows 25-28 as well as providing support for turbine nozzles and vanes for controlling and directing high pressure steam through high pressure turbine 16. Similarly, intermediate pressure turbine 17 has blade rows 32-35 which are enclosed by housing 36. Steam from high pressure turbine 16 is coupled to intermediate pressure turbine 17 by duct 37. Steam from intermediate pressure turbine 17 is coupled to low pressure turbines 18 and 19 by way of duct 38. Low pressure turbine 18 has blade rows 42-47 enclosed by housing 54 and has an exhaust duct 55. Low pressure turbine 19 has blade rows 48-53 enclosed by housing 56 which has an exhaust duct 57. The number of blade rows in turbines 16-19 may vary depending upon the turbine as well as the number of fixed vanes and inlet nozzles for distributing and controlling the steam entering and passing through the respective turbine. A high pressure steam source 60 provides high pressure steam, for example, at 1000 degrees centigrade and at 155 pounds per square centimeter (1000 pounds per square inch (psi)) which may pass over duct 61 into an inlet nozzle not shown within housing 29 of turbine 16. The steam passes through turbine 16 over duct 37 through turbine 17 over duct 38 where it divides. A portion of the steam passes over duct 62 through turbine 18 and out exhaust 55. The other portion of steam passes over duct 63 through turbine 19 and out exhaust duct 57. Compound turbine 14 may operate in a power plant for producing electricity, for example, 60 hertz or 50 hertz alternating current by way of electrical generator 64. Shaft 20 may have an angular velocity of 3600 revolutions per minute or 1800 revolutions per minute (rpm) to produce 60 hertz alternating current from electrical generator 64. Alternately, shaft 20 may have an angular velocity of 3000 rpm or 1500 rpm to produce 50 hertz alternating current from electrical generator 64. The angular velocity of shaft 20 may be determined by a tachometer sensor 70 having an output over leads 71 and 72. Tachometer sensor 70 may be positioned close to shaft 20 having an optical coupling such as by light to detect each revolution made by shaft 20. Shaft 20 may have a strip of reflective tape thereon or some other suitable means to communicate the position of the shaft 20 as it completes a revolution. Tachometer sensor 70 may be supported by the same support fixture that supports bearing 21 so that the position of tachometer sensor 70 remains fixed in relation to longitudinal axis 73 of shaft 20 and of rotor 30. Referring to Fig. 2, a cross sectional view of high pressure turbine 16 is shown to illustrate blade row 25 and two acoustic sensors 76 and 77 mounted through housing 29 to be positioned downstream of blade row 25 in locations 87 and 130 respectively. As many as 150 blades may be in a blade row. The ends of the blades may be free or they may be attached to a shroud at the end of the blade by means of a tenon passing there through and riveted over to form a blade group. Alternately, wires may extend through the blades to allow movement of the blades relative to one another but to dampen their vibration. Fig. 2 shows, for example, individual blades 78-81 and a blade group 82 of four blades 74, 75, 84 and 85 having a shroud 83 attached to the ends of the blades 74, 75, 84 and 85. Acoustic sensors 76 and 77 are positioned with respect to blade row 25 so that the individual blades 78-81 or blade group 82 approaches and departs from the acoustic sensors 76 and 77 in the course of one rotation of shaft 20 about shaft axis 73 thereby imparting a Doppler effect to the received sound waves. As blade row 25 shown in Fig. 2 rotates with shaft 20 as shaft 20 rotates as shown by arrow 69 acoustic sensors 76 and 77 record certain acoustic signals which are order related which are for the most part acoustic signals which are a function of the angular position of blade row 25 and reoccur each revolution of shaft 20. Examples of order-related signals are 1. blade row nonuniformity i.e. nonuniform blade wake caused by, for example, uneven spacing of the blades about shaft 20 and blade passing frequency and 2. an individual resonantly vibrating blade or blade group. The blades may be excited into resonance by the nozzle passing frequency which occurs when a plurality of nozzles discharge steam which impact on blade row 25 as blade row 25 is rotating at the operating or running speed, or by any integer multiple of running speed due to normal nonuniformities in the spacing between nozzle blades. Acoustic sensors 76 and 77 may have a separation angle with respect to the rotation of shaft 20 of about 9 degrees for good results. Order-related acoustic signals are a function of the rpm of shaft 20 and frequency harmonics of the running speed. Non order-related acoustic signals may be due to, for example, background noise of steam passing through turbine 16 or due to nonresonant vibrations of individual blades or blade groups for example at the natural vibration frequency of the blade. Fig. 3 shows an individual blade 78 on shaft 20 without vibration. Blade 78' is shown in Fig. 3 having a vibration at the natural frequency of the blade. Fig. 4 shows blade 78 on shaft 20 without vibration. Figure 78'' shows blade 78 vibrating a natural frequency four times that of Fig. 3. Now if the natural frequency of the blade corresponded to an integral number of running speed then the vibration shown in Figs. 3 and 4 would be order-related. Every time blade 78 passed sensor 77 and 76 the respective sensor would see the blade in exactly the same physical position (tangential deflection) with respect to the shaft position as shaft 20 rotates. If the vibration of blade 78 was not an integral number of times of the running speed then blade 78 would be in a different physical position each time it passed sensors 76 and 88 respectively. Fig. 5 shows blade 78 without vibration and blade 78''' with order-related vibration phase shifted (at a different rpm or sensor) as compared with blade 78' in Fig. 3. Fig. 6 shows blade 78 without vibration and blade 78'''' with order-related vibration phase shifted (at a different rpm or sensor) as compared with blade 78''. Fig. 7 shows one embodiment of the invention which may operate by using only one acoustic sensor 76. Acoustic sensor 76 is placed in location A on housing 29 to receive acoustic signals 88 as shown in Fig. 7. Acoustic sensor 76 functions to receive acoustic energy in a frequency range from 0-25 kilohertz providing a corresponding acoustic signal. The acoustic signal is coupled over lead 89 to an input of analog to digital converter 90 which converts the acoustic signal with an accuracy of 14 bits after suitable low pass filtering to a frequency at no more than half the sample rate to prevent aliasing. The output of analog to digital converter 90 is coupled over lead 91 to an input of memory 92. Memory 92 functions to store a record consisting of a plurality of samples obtained during each revolution of shaft 20 as a function of the shaft angular velocity (rpm) given at the beginning of a record wherein a record consists of, for example, 64 samples per revolution as a function of time. Tachometer sensor 70 shown in Figs. 1 and 7 is coupled over lines 71 and 72 to an input of shaft speed detector 94 which provides an output over line 95 to an input of address generator 96. Tachometer sensor 70 functions to provide a reference signal over leads 71 and 72 indicative of shaft 20 position and of rotor 30 position at least once each time shaft 20 completes a revolution about the shaft axis 73 to provide an indication of angular velocity (rpm) of shaft 20. Shaft speed detector 94 measures the time shaft 20 makes one complete revolution to determine the angular velocity in revolutions per minute (rpm) for the next revolution. In a typical operating turbine operating at 3600 rpm the rpm may vary plus or minus one rpm. The angular velocity of shaft 20 may be subdivided into sixteen increments between plus and minus one rpm to provide each increment of .125 rpm. An accurate measure of the current angular velocity of shaft 20 in rpm is essential so that data recorded per revolution which may comprise for example 64 to 128 samples is recorded as a function of the rpm in memory 92. Address generator 96 functions to generate an address as a function of the rpm of shaft 20 which is coupled over lead 97 to memory 92 to store in memory 92 a record of a plurality of samples for one revolution of shaft 20 before a new address generated as a function of the angular velocity of shaft 20 is provided for the next record which may or not be the same angular velocity as the prior revolution of shaft 20. Address generator 96 also provides addresses over lead 97 for retrieving a record from memory 92 and coupling the record over lead 98 to an input of synchronous averaging circuit 100. Synchronous averaging circuit 100 also receives data from memory 102 over lead 104. Memory 102 may contain for example a running sum of the samples of records obtained at respective rotor positions of the rotor along with the number of times the running sum has had samples added thereto. Synchronous averaging circuit 100 may retrieve data from memory 102 on lead 104 and add the next record samples respectively received over line 98 as well as provide a count for the number of records added together which may be returned to memory 102 for storage over lead 105. A running average can be provided by also storing the average which may be obtained by dividing the running sum by the number of records added together at a respective rpm of shaft 20 and provide the average on lead 106 to an input of sample alignment 120. Synchronous averaging circuit 100 and memory 102 function to provide for averaging the amplitude and taking into account the polarity of the samples obtained at respective rotor positions within each revolution of shaft 20 revolving at a first angular velocity and a similar but separate averaging of the amplitude of the samples with shaft 20 revolving at a second angular velocity. Actually about 16 angular velocities in increments of .125 rpm are recorded or accumulatively summed in memory 102. Sample alignment 120 functions to curve fit the averaged samples at a particular rpm and resample the curve to provide averaged samples corresponding to common shaft positions at two shaft rpm's. Sample alignment 120 receives address signals generated as a function of the rpm shaft 20 at the time the record was captured over lead 99. The output of sample alignment 120 is coupled over lead 121 to an input of multiplexer 107. Address generator 96 provides addresses over lead 99 to memory 102 and address register 108. The addresses on lead 99 may correspond to respective rpm of shaft 20 and may be used for providing data to synchronous averaging circuit 100 for averaging synchronously a number of samples at respective rpm's or to provide two consecutive addresses representative of two angular velocities of shaft 20 to memory 102 for providing averaged data over lead 106 to sample alignment 120 which in turn provides the data by way of multiplexer 107 to subtractor 108. Data representative of a first angular velocity is coupled over lead 109 to an input of subtractor 108. Data representative of a second angular velocity is coupled over lead 110 to a second input of subtractor 108. Subtractor 108 functions to subtract the amplitudes and taking into the account the polarity of averaged samples obtained at respective rotor or shaft positions of shaft 20 revolving at the first and at the second angular velocity to provide a difference Doppler signal at respective rotor or shaft positions of the rotor whereby order- related background noise due to other blades having nonuniformity in angular position on the rotor is removed. The difference Doppler signal is provided at the output of subtractor 108 on lead 112 to an output terminal and to the input of comparator 114. A voltage potential representative of a voltage threshold (V TH ) is coupled over lead 115 to a second input of comparator 114. Comparator 114 functions to compare the voltage V TH with the potential on lead 112 containing the difference Doppler sample to provide an output over lead 116 at times the difference Doppler signal exceeds the threshold voltage indicating the presence of a resonantly vibrating blade or blade group within blade row 25 in high pressure turbine 16. In operation of difference Doppler circuit 86 as shown in Fig. 7, shaft 20 may have an angular velocity of 3600 rpm or 60 revolutions per second with analog to digital converter 90 taking a record of 64 samples per revolution at 14 bits per sample which would result in a sampling rate of 3840 hertz. If data was accumulated for as long as 30 minutes, then 108,000 records would be obtained. If the 108,000 records were distributed over 16 angular velocity bins of .125 rpm each from 3599 to 3601 rpm then on the average 6750 records would be in each angular velocity bin. Address generator 96 would select two angular velocities based on the largest number or records and the largest separation of angular velocities prior to sending the averaged records at these two angular velocities of shaft 20 to subtractor 108 to form the difference Doppler signal. Since over a 6750 records will have been averaged, non order-related background noise and blade flutter (non order-related blade vibration) will be reduced by averaging wherein the order-related background noise and blade vibration will accumulate and be enhanced. When the two averaged order-related records are subtracted from one another, taken at different angular velocities of shaft 20, order-related signals due to blade row nonuniformity will be cancelled out whereas order-related resonantly vibrating blades will remain due to a difference in resonant blade phase at common rotor positions. The phase difference in blade vibration is a function of the difference in rpm of shaft 20. The signals or records retrieved from memory 102 on line 106 are synchronous averaged records which may be for example averaged over 2000 to 10,000 records within a respective angular velocity bin of shaft 20 in memory 102. Address register 108 may hold the address used to access memory 102 and sample alignment 120. The address may be an indication of the rpm of shaft 20 corresponding to the record retrieved from memory 102 on lead 106 or on lead 121. The output of address register 108 may provide not only the rpm of the two records subtracted but also of the sample number in the record indicative of the location on the blade row or the blade at times comparator 114 provides an output on line 116. The output of address register 108 as shown in Fig. 7 is on lead 118. If the sampling rate is independent of the rpm of shaft 20, then prior to subtracting the records obtained at two rpm's or angular velocities of shaft 20, one of the records will need to be shifted in order that the samples subtracted will correspond to the same physical location of the moving blade row 25 passed sensor 76. The records may be lined up by curve fitting the 64 samples to a 25 order curve fit formula followed by resampling the curve corresponding to obtaining two averaged samples at respective angular position of shaft 20. Sample alignment 120 performs this function and provides an output over lead 121 to multiplexer 107. Referring to Fig.8 an alternate embodiment of the invention is described for detecting and locating fluttering blades which are self excited nonresonantly vibrating blades vibrating at a natural frequency of the blade or a harmonic thereof. Blade vibrations can be classified in one of two general categories, order-related or non order-related. Order-related vibrations occur at exact integer multiples of running speed. For example, a blade with a natural frequency very close to 4 per revolution vibrates resonantly at exactly four (4) per revolution. On the other hand, a blade may vibrate or flutter in self excited fashion right at the natural frequency, but not exactly at four per revolution and thus not order-related. An order-related vibration, or an order-related signal repeats exactly in each revolution; while a non order-related vibration or signal does not. An order-related blade vibration results in an order-related Doppler signal in a downstream acoustic sensor. A nonperfect geometric blade row (blade to blade) results in an order-related non Doppler signal in a downstream microphone. A non order-related blade vibration results in a non order-related signal in a downstream microphone or sensor, but with an order-related amplitude envelope that peaks up as the vibrating blade passes by the sensor. Non order-related background steam noise in a high pressure steam turbine results in a non order-related signal in the downstream acoustic sensor 75 shown in Fig.8, but with "straight line" amplitude envelope. Signal processor 160 shown in Fig.8 provides a means for detecting the order-related envelope associated with a blade vibrating in a non order-related manner such as in fluttering and to do so in the presence of non order-related "straight line" background noise, and in the presence of order-related noise either from blade row nonuniformity, and from other order-related sources including blade resonance. In Fig.8, like references are used for functions corresponding to the apparatus of Fig. 7. The signal on line 98 represents the acoustic signal from acoustic sensor 76 positioned downstream on a stationary member with respect to shaft rotor 30 shown in Fig. 1 to receive soundwaves or acoustic signals 88 emanating from the vibrating blade or rotor 30 as the blade rotates about the rotor axis 73. The acoustic signal from acoustic sensor 76 is digitized and sampled by analog to digital converter 90 and by address generator 96' which stores the digitized signal on line 91 in memory 92. The sampling may be at a rate such as 64 or 128 samples per revolution. The sampling may be proportional to running speed putting the samples in the revolution domain. Alternately, the samples may be evenly spaced apart from a start mark originating from the tach sensor 70. Each record consisting of 64 or 128 samples represent one revolution starting at the tach trigger from tach sensor 70 which is tagged with a label indicating the exact angular velocity of shaft 20 and rotor 30 at the time of capture of the record. As described, with respect to Fig. 7 there may be 100 speeds spanning plus or minus 1 rpm for a rotor having an angular velocity of 3600 rpm. If 64 samples were taken per record, then 1024 individual point-speed bins would be stored in memory 102. Synchronous averaging circuit 100 and memory 102 function to provide a running synchronous average over a period of time for example a half hour or an hour before being dropped out. The output of memory 106 is coupled over lead 162 to an input of subtractor circuit 164. The output of memory 92 on lead 98 is coupled to a second input of subtractor circuit 164. For each new record obtained from memory 92 corresponding to one of the sixteen speeds or angular velocities as determined by address generator 96', the corresponding 64 points of the running synchronous average from memory 102 at the respective angular velocity is first algebraicly subtracted from the new record in subtractor circuit 164. The output of subtractor circuit 164 is coupled over lead 165 to an input of memory 166 which stores in memory 166 a different signal sample at 1024 points speed bins. Address generator 96' couples an appropriate address over lead 167 to memory 166 so that different signal samples on lead 165 are stored as a function of rotor position and angular velocity. Subtractor circuit 164 functions to subtract the amplitude of averaged samples obtained at respective rotor positions of rotor 30 revolving at each angular velocity of the plurality of angular velocities or 100 speeds from individual samples obtained at respective rotor positions of rotor 30 revolving at each angular velocity of the plurality of angular velocities to provide a difference signal sample at respective rotor positions of rotor 30 revolving at the plurality of angular velocities. Memory 166 contains non order-related background noise due to flow noise and non order-related vibrating blades. Address generator 96' functions to generate addresses over leads 167 and lead 169 to provide addresses to memories 166 and 170 respectively which corresponding to the same rotor position and rotor angular velocity. The output of memory 166 is coupled over lead 171 to an input of root mean square difference circuit 172. Root mean square difference circuit 172 functions to take the square root of the sum of the squares of the difference signal sample from memory 166 and the difference signal samples obtained earlier at the same respective rotor position and at the same angular velocity which had been stored in memory 170. Memory 170 supplies a signal over lead 173 which may be for example a running sum of the squares of previous difference signal samples stored in memory 170 with respect to a rotor position and angular velocity. The output of root mean difference circuit 172 is coupled over lead 174 to memory 170. Memory 170 has 1024 root mean square difference samples stored therein corresponding to respective rotor positions and rotor angular velocity. Address generator 96' provides addresses over line 169 to read out the root mean square difference samples at respective rotor positions and at one angular velocity which is coupled over lead 175 to an input of root mean square running speed circuit 176 and to an input of subtractor circuit 180. Root mean square running speed circuit 176 functions to determine the root mean square of the root means square difference samples at respective rotor positions of rotor 30 revolving at each angular velocity of the plurality of velocities to form a root mean square running speed signal with respect to each angular velocity. The output of root mean square running speed circuit 176 is coupled over lead 182 to a second input of subtractor circuit 180. Subtractor circuit 180 functions to subtract the amplitude of the root mean square running speed signal on lead 182 at each respective angular velocity of rotor 30 from the amplitude of the root mean square difference samples on lead 175 at the same corresponding angular velocity of rotor 30 to form reduced mean square difference samples at respective rotor positions and angular velocities which are coupled over lead 184 to an input of memory 186 which stores the samples. Address generator 96' provides addresses over lead 187 to memory 186 to locate the samples received on lead 184. Memory 186 thus holds 1024 reduced root mean square difference samples corresponding to 64 rotor positions and 16 angular velocities. The output of memory 186 when provided addresses by address generator 96' over lead 187 is coupled over lead 188 to an input of synchronous averaging circuit 190. Synchronous averaging circuit 190 functions to average over several revolutions for example 128 revolutions of rotor 30 the reduced means square difference samples at respective rotor positions of the rotor revolving at respective angular velocities. Memory 192 functions to hold the averages of the reduced means square difference samples by summing the samples as a running sum and dividing by the number of records stored. Address generator 96' provides appropriate addresses over lead 194 to an address input of memory 192 and to an output indicative of rotor position. Synchronous averaging circuit provides data to memory 192 over lead 195 and receives data from memory 192 over lead 196. A non zero result from synchronous averaging circuit 190 after many averages for example 128 averages indicates an order-related envelope of a non order-related signal i.e. a fluttering blade. Memory 192 may contain 1024 averaged and reduced root mean square difference samples corresponding to 64 rotor positions and 16 angular velocities. Address generator 96' provides addresses over lead 194 to memory 192 to provide over lead 198 each averaged and reduced root mean square difference sample to comparator 200. A second input to comparator 200 is a threshold voltage V TH over lead 202. Comparator 200 functions to compare the averaged and reduced root mean square difference samples corresponding to respective rotor positions of said rotor revolving at respective angular velocities with the threshold value V TH whereby amplitudes above the threshold value V TH are indicative of a non order-related vibrating blade. The position of the vibrating blade is indicated by the address on lead 194 at the time the comparator 200 provides an output on lead 204.

Claims: An apparatus for detecting a non order-related vibrating blade (78) of a rotating rotor (30) in an operating turbine (14) comprising: an acoustic sensor (76) positioned on a stationary member (29) with respect to said rotor (30) to receive sound waves emanating from said vibrating blade (78) of said rotor (30) as said blade rotates about said rotor axis (73) and to provide an acoustic signal from said received sound waves, said acoustic sensor (76) positioned with respect to said rotor (30) so that said blade (78) approaches and departs from said acoustic sensor (76) in the course of one rotation of said rotor (30) about said rotor axis (73) thereby imparting a Doppler effect to said received sound waves, first means (70) for obtaining a reference signal indicative of rotor positions at least once each time said rotor (30) completes a revolution about said rotor axis (73) and for determining the angular velocity of said rotor (30), characterized by second means (90) for sampling said acoustic signal to obtain samples as a function of rotor position as said rotor completes a plurality of revolutions at a plurality of angular velocities of said rotor, third means (100; 102) for averaging said samples obtained at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities and for storing the averaged samples, fourth means (164) for subtracting the averaged samples obtained at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities from individual samples obtained at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities to provide a difference signal sample at respective rotor positions of said rotor revolving at said plurality of angular velocities whereby non order-related background noise due to flow noise and non order-related vibrating blades is extracted, fifth means (172) for determining the root mean square (RMS) of a plurality of difference signal samples at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities to form a root mean square difference sample at respective rotor positions of said rotor revolving at said plurality of angular velocities, sixth means (176) for determining the root means square (RMS) of said root means square difference samples at respective rotor positions of said rotor revolving at each angular velocity of said plurality of velocities to form a root mean square running speed signal, seventh means (180) for subtracting the amplitude of said root mean square running speed signal at each respective angular velocity from the amplitude of said root mean square difference samples at the same corresponding angular velocity to form reduced root mean square difference samples at respective rotor positions and angular velocities, eighth means (190) for averaging over several revolutions said reduced root mean square difference samples at respective rotor positions of said rotor revolving at respective angular velocities, and ninth means (200) for comparing said averaged and reduced root mean square difference samples at respective rotor positions of said rotor revolving at respective angular velocities with a threshold value whereby amplitudes above said threshold value are indicative of said non order-related vibrating blade. A method for detecting a non order-related vibrating blade (78) of a rotating rotor (30) in an operating turbine having an acoustic sensor (76) positioned on a stationary member (29) with respect to said rotor (30) to receive sound waves emanating from said vibrating blade (78) of said rotor (30) as said blade (78) rotates about said rotor axis (73) and to provide an acoustic signal from said received sound waves, said acoustic sensor (76) positioned with respect to said rotor (30) so that said blade (78) approaches and departs from said acoustic sensor (76) in the course of one rotation of said rotor (30) about said rotor axis (73) thereby imparting a Doppler effect to said received sound waves comprising the step of: obtaining a reference signal (70) indicative of rotor positions at least once each time said rotor completes a revolution about said rotor axis and for determining the angular velocity of said rotor, characterized by the following steps: sampling said acoustic signal (90) to obtain samples as a function of rotor position as said rotor completes a plurality of revolutions at a plurality of angular velocities of said rotor, averaging (100; 102) said samples obtained at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities and for storing the averaged samples, subtracting (164) the averaged samples obtained at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities from individual samples obtained at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities to provide a difference signal sample at respective rotor positions of said rotor revolving at said plurality of angular velocities whereby non order-related background noise due to flow noise and non order-related vibrating blades is extracted, determining the root mean square (RMS) (172) of a plurality of difference signal samples at respective rotor positions of said rotor revolving at each angular velocity of said plurality of angular velocities to form a root mean square difference sample at respective rotor positions of said rotor revolving at said plurality of angular velocities, determining the root mean square (RMS) (176) of said root mean square difference samples at respective rotor positions of said rotor revolving at each angular velocity of said plurality of velocities to form a root mean square running speed signal, subtracting (180) the amplitude of said root mean square running speed signal at each respective angular velocity from the amplitude of said root mean square difference samples at the same corresponding angular velocity to form reduced root mean square difference samples at respective rotor positions and angular velocities, averaging (190) over several revolutions said reduced root mean square difference samples at respective rotor positions of said rotor revolving at respective angular velocities, and comparing (200) said averaged and reduced root mean square difference samples at respective rotor positions of said rotor revolving at respective angular velocities with a threshold value whereby amplitudes above said threshold value are indicative of said non order-related vibrating blade.

Inventors: LEON ROBERT L, POWELL DAVID H, LEON,ROBERT L., POWELL,DAVID H.
Applicants: ELECTRIC POWER RES INST, ELECTRIC POWER RESEARCH INSTITUTE
Application year: 1990
Main classification: G01H1
IPC codes: G01H1