US20090082976A1 - Methods of Analysing Apparatus - Google Patents
Methods of Analysing Apparatus Download PDFInfo
- Publication number
- US20090082976A1 US20090082976A1 US12/085,943 US8594306A US2009082976A1 US 20090082976 A1 US20090082976 A1 US 20090082976A1 US 8594306 A US8594306 A US 8594306A US 2009082976 A1 US2009082976 A1 US 2009082976A1
- Authority
- US
- United States
- Prior art keywords
- shaft
- blade
- window
- component
- peaks
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
- G01H1/003—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
- G01H1/006—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines of the rotor of turbo machines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0066—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by exciting or detecting vibration or acceleration
Definitions
- This invention concerns a method and apparatus for monitoring rotating and reciprocating apparatus and particularly a method and apparatus for monitoring rotating blades mounted on a shaft in a gas turbine engine.
- Apparatus with rotary components such as gas turbine engines, generate signals which are periodic with respect to shaft rotation.
- the frequency of the signals is related to the angular velocity of the respective shaft and hence the engine speed.
- These rotation-periodic signals are conventionally known as order components. As the angular speed of rotation increases typically the order components similarly increase in frequency.
- each vibration response generally has the same frequency as the engine order forcing frequency that generated it.
- FIG. 1 represents a Campbell diagram for a shaft within a gas turbine engine.
- the y-axis represents frequency of the rotating shaft in Hertz and the x-axis represents shaft speed in revolutions per minute (rpm).
- Each shaft has a number of orders, which represent the first vibration harmonic and subsequent harmonics of the rotating shaft.
- the first, eighth and eleventh and thirteenth harmonic of the shaft are indicated as lines 2 , 4 , 6 and 8 respectively on FIG. 1 .
- the blades can be induced to vibrate at their natural frequency where frequencies of their modes intersect the engine order lines.
- a typical plot of blade modes is depicted on FIG. 1 as lines 10 , 12 , 14 , 16 , 20 , 22 .
- a near perfect frequency match of engine order and blade mode is required to produce the highest amplitude vibrations.
- Certain combinations of blade mode and engine order will produce higher amplitude vibrations than other combinations of blade mode and engine order.
- prudent design practice dictates that the blades be constructed such that the frequencies of the lower modes fall between harmonics of the operating frequency of the turbine. At high amplitude resonant vibrations there is an increased chance of fatigue, cracking and crack propagation within the turbine blades that may give rise to such a failure.
- the vibrations may be measured using, for example, strain gauges, laser transmitters or capacitance and eddy probes. Where a crack, or some other fault is detected in a component it is possible to replace the faulty component before it fails and causes additional damage. Such a replacement results in reduced downtime of the engine and thus an improved cost per hour operation.
- Each row of blades requires its own microphone to sense the acoustic energy from its respective row.
- a complex gas turbine engine which may have about 20 rows of blades split between the fan, compressor and turbine, significant numbers of sensors are required.
- the method is capable of identifying defects such as, for example, cracks, or other artifacts that may not be defects.
- a method of sampling data from a rotatable shaft comprising the steps: determining at least one order related component of the shaft; determining at least one vibration mode of articles functionally mounted to the shaft; selecting one of the vibration modes; selecting one of the order related components that has an instantaneous frequency which intersects the natural frequency range of the selected mode; rotating the shaft and sampling the data where the instantaneous frequency of the selected order and natural frequency range of the selected vibration mode intersect.
- the shaft is rotated with an increasing or decreasing speed of rotation.
- the sampling of the data begins immediately before the selected order and selected vibration mode intersect.
- the sampling of the data ends immediately after the selected order and selected vibration mode intersect.
- the selected order may be the first engine order.
- a method of isolating a selected periodic response from a plurality of periodic responses comprising the steps: operating a shaft at a varying rotational velocity to provide a signal that comprises a plurality of periodic responses; transforming the signal using a short-time chirp Fourier transform, thereby isolating the selected periodic response and characterised in that the chirp rate of the short-time chirp Fourier transform is a function of the rate of change of the shaft velocity.
- the shaft may be one of a plurality of shafts in a gas turbine engine.
- the varying rotational velocity occurs during acceleration or deceleration of the engine.
- the periodic responses may be resonance oscillations of vibration modes of articles functionally mounted to the shaft.
- the method further comprises the step of determining the order related component of the shaft, selecting one of the vibration modes of the articles transforming the signal where the order and natural frequency range of selected vibration mode intersect.
- the articles may be blades.
- the signal is a vibro-acoustic signal.
- the vibro-acoustic signal is captured by an appropriate transducer, for example, a microphone, accelerometer, strain gauge, pressure transducer, etc.
- a method of determining true collections of peaks in an envelope of vibro-acoustic response data comprising the steps: a) providing two sample windows each enclosing a portion of the vibro-acoustic response data, b) calculating the mean value of the envelope of the vibro-acoustic response within each window, c) calculating the ratio of mean value in the first window to the mean value in the second window; the second window lagging the first window d) comparing the ratio against a threshold, e) indicating a single peak where the compared ratio equals or exceeds the threshold, f) moving the sample windows along the envelope of the vibro-acoustic response data and repeating steps b) to e) at least once, g) calculating the spacing between adjacent single peaks, h) grouping adjacent single peaks into a collection of peaks, each single peak in the collection being separated from an adjacent single peak by a spacing that is less than a threshold value, adjacent
- the method further comprising the step of providing a further sample window, the further sample window leads the first window with respect to the envelope of vibro-acoustic response data; step c) being modified in that ratio of mean value in the first window to the mean value in the second window and the ratio of the mean value in the first window to the mean value in the further window is calculated; step e) being modified in that a single peak in indicated when both calculated ratios are above the threshold.
- a method of determining an artifact in a component comprising the steps: a) exciting the component to induce a resonance response; b) detecting higher harmonics in the averaged power spectral density of resonance response; c) calculating the normalised amplitude of two or more higher harmonics, d) comparing the sum of the normalised amplitude of the two or more higher harmonics with a threshold value thereby determining the presence of an artifact.
- the component may be a blade.
- the blade may be mounted on a shaft.
- the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
- a method for determining an artifact in a component comprising the steps: a) exciting the component to induce a resonance response, b) detecting fundamental and higher harmonics in the averaged power spectral density of resonance response, c) calculating the normalised amplitude of two or more harmonics, at least one of the harmonics being the fundamental harmonic, d) calculating the ratio of the sum of the normalised amplitude of the, or each, higher harmonic and the normalised amplitude of the fundamental harmonic; e) comparing the value of the ratio with a threshold, an artifact being determined by comparing the value with the threshold.
- the component may be a blade.
- the blade may be mounted on a shaft.
- the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
- a method for determining an artifact in a component comprising the steps: a) exciting the component to induce a resonance response, b) calculating the real and imaginary components of bicoherence b of a resonance response at pk 0 and qk 0 wherein p and q are integers and k 0 is the component resonant frequency, c) determining a location of a point related to calculated components in real and imaginary two dimensional space; the location of the point determining the presence of the artifact.
- the location of the point is compared with a discriminant function.
- the discriminant function is linear.
- the component may be a blade.
- the blade may be mounted on a shaft.
- the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
- FIG. 1 is a representative Campbell diagram for a shaft in a gas turbine engine having a row of blades.
- FIG. 2 is a schematic of a three shaft engine.
- FIG. 4 shows the amplitude-time-frequency distribution of envelope for a LP, IP and HP shaft after extraction from a vibro-acoustic signal, using short time chirp Fourier transform.
- FIG. 5 is a typical amplitude response of a blade in the time domain under excitation from order related components with changing rotational velocity.
- FIG. 6 is a typical amplitude envelope of a blade in the frequency domain under excitation from order related components with changing rotational velocity (high signal/noise ratio)
- FIG. 7 is a typical amplitude envelope of a blade in the time domain under excitation from order related components with changing rotational velocity (low signal/noise ratio).
- FIG. 8 depicts detected single peaks within the envelope of vibro-acoustic signal
- FIG. 9 depicts the collections of single peaks, the collections being separated by gaps greater than a pre-determined size, here there are 6 collections depicted
- FIG. 10 depicts collections of single peaks that have a duration greater than a pre-determined value, 4 collections are depicted
- FIG. 11 depicts collections of single peaks that have a density greater than a pre-determined value, 1 collection is depicted
- FIG. 12 depicts the power spectral density of resonance response of an un-cracked blade.
- FIG. 13 depicts the power spectral density of resonance response of a cracked blade.
- FIG. 14 depicts the sum of the normalised amplitude of two or more higher harmonics against sample number of cracked and un-cracked blade.
- FIG. 15 is a graphical representation of the calculated real and imaginary components of bicoherence for cracked and un-cracked blades.
- FIG. 1 represents a Campbell diagram for an intermediate pressure (IP) compressor, the IP compressor being driven by an IP shaft within a Rolls-Royce multi shaft gas turbine engine.
- IP intermediate pressure
- FIG. 2 shows a schematic longitudinal section of the three coaxial shafts.
- Low pressure (LP) shaft 30 occupies the central position and is surrounded in turn by the IP shaft 32 and the high pressure (HP) shaft 34 .
- the LP shaft connects the fan and the LP turbine (not shown)
- the IP shaft connects the IP compressor and IP turbine (not shown)
- the HP shaft connects the HP compressor and the HP turbine.
- LP shaft 30 carries a single pole tachometer 36 which is conveniently used for shaft balancing operations.
- IP shaft 32 carries a 60 pole tachometer 38 which is conventionally used for standard shaft speed measurements for engine control purposes.
- HP shaft 34 is connected via bevel gear 40 and step aside gearbox 42 to main (external) gearbox 44 , with a tachometer 46 connected to the output of the main gear box.
- Tachometer 36 produces a signal pulse for each rotation of the LP shaft, and hence the rotational frequency (i.e. shaft speed) of the LP shaft can be determined from the inverse of the period between signal pulses.
- Tachometer 38 produces 60 signal pulses for each rotation of the IP shaft 32 , and hence the rotational frequency of the IP shaft can be determined from the inverse of 60 times the period between the signal pulses.
- Tachometer 46 measures the rotational frequency of the output of the main gearbox 44 . However, as the gearing ratios of the main and step aside gearboxes 44 , 42 and bevel gear 40 are known, the rotational frequency of the HP shaft can be inferred from tachometer 46 .
- the rotational frequencies measured by the tachometers provide the engine orders (e.g. fundamental and harmonic components) for each shaft.
- the Campbell diagram of FIG. 1 depicts a plot of frequency against the speed of rotation of the IP shaft. Four shaft orders are shown representing the first 2 , eighth 4 , eleventh 6 and thirteenth 8 engine order.
- Each stage comprises a single row of multiple blades.
- Each blade within a stage will vibrate at its natural frequency and each blade within a stage may have slight manufacturing variations, meaning that the natural frequency of blades within a stage may slightly vary across a narrow range.
- the natural frequencies of a set of blades for different modes are represented graphically on FIG. 1 as lines 10 , 12 , 14 , 16 , 18 , 20 and 22 . These frequencies are commonly known as frequencies of blade modes and represent mode 1 , 2 , 4 , 12 , 15 , 18 and 21 respectively. Where the engine orders, for example lines 4 , 6 and 8 , intersect the blade modes, then resonance will be induced.
- the fundamental frequencies of engine orders are calculated from the tachometer signals.
- the frequency of the second order is twice the fundamental frequency at the rotational velocity and so on.
- the base-line mean and variance of the natural frequencies of blade modes are measured from experimental data taken during engine development.
- the data is typically obtained during bench tests, where the blade is clamped and then excited by either shaking or passing an air-jet past over the blade. The obtained data is retained.
- a transducer for example, an accelerometer or microphone, capable of sensing a vibro-acoustic signal, is placed at a position where it can capture the signal of the rotating system of interest. The captured vibro-acoustic data is retained for analysis.
- the vibro-acoustic data obtained has a large amount of background interference that hides the vibro-acoustic response (signal) of the components of whose health is to be monitored it is necessary to process the vibro-acoustic data. In particular it is necessary to separate the desired response from responses of other components, which are similarly order related and serve to mask the desired signal.
- All the vibro-acoustic responses typically have a low signal to noise ratio.
- the method analyses the frequency responses of the blades mounted within the IP compressor at the points where a natural frequency range of blades intersects a selected engine order and the amplitudes of the blade modal responses are highest.
- the natural frequency ranges of blade modes of the first set of blades on the IP compressor cross one or more of the shaft orders; blade resonance responses are generated during these crossings.
- the natural frequency ranges of blade modes of the second, third and fourth sets of blades also cross the shaft orders; blade resonance responses are also generated during these crossings.
- the natural frequency ranges of modes of blades attached to the LP and HP shaft will also cross their respective shaft orders; blade resonance responses are also generated during these crossings.
- the captured vibro-acoustic data includes all these resonant responses in addition to other interference. Consequently it is necessary to isolate the desired signal.
- the signal obtained during acceleration and deceleration is obtained during nonlinear variation of the shaft frequency in time.
- This signal may conveniently be called a “piece-wise engine order” and is processed using a short-time chirp-Fourier transform.
- This transform has the form:
- h(t) is a time window
- x 1 (t) is a “piece-wise engine order”
- T is the centre of the window
- c 2 (t) is the variable frequency speed of the transform
- f is frequency.
- frequency speed it is meant the speed of frequency change or, to put it another way, the rate of change of the frequency, or “chirp rate”.
- the short-time chirp-Fourier transform could be used with different windows, e.g. a rectangular window, a Gaussian window, Hamming window etc. It selectively detects the piece-wise shaft orders whilst the shaft speed is varied.
- the recorded vibro-acoustic data comprises order related components from the LP, IP and HP shafts.
- the selected order related components from the IP shaft is isolated from the order related components of the other shafts by evaluating the piece-wise frequency-time dependency of the selected order related components and frequency speed for each part of the dependency and processing the acoustic or vibration data by the short-time chirp-Fourier transform with appropriate durations and frequency speed.
- appropriate durations it is meant durations of the selected order related components with constant frequency speed.
- the frequency speed of engine order 1 of the IP shaft is 0.027 Hz/s. Consequently, the frequency speed of the transform for detecting the blade resonances excited by IP engine order 4 is 4 times that value i.e. 0.108 Hz/s.
- the frequency/time/magnitude plot of the IP shaft it is possible to see that the magnitude varies both with time and frequency. Peaks are observed where the instantaneous frequency of 4 th shaft order of the IP shaft intersects with the natural frequency range of the blade modes of the blades connected to the IP shaft.
- Other peaks along the order may relate to resonant oscillations of higher modes of the blade rows. It is possible to determine which row and which mode is excited at a given frequency by referring to the Campbell diagram for the relevant shaft.
- the envelope of magnitude of chirp Fourier transform of the selected nth engine order of the IP shaft can be
- the envelope may be displayed in both the time and frequency domain as shown in FIG. 5 and FIG. 6 .
- the blade resonant peaks may be detected from either of these envelopes using similar methods, but for the purpose of this description the detection method using the envelope in the time domain will be described.
- the signal is still relatively noisy and it is necessary to distinguish true blade resonance peaks from false peaks.
- a first method is described with reference to FIG. 7-11 .
- Two data windows are used to analyse amplitude of envelope against time. The windows are scanned through the data range with their size and spacing being maintained, the right window leading the left window. The mean value within each window is calculated and if the ratio of the mean value in the first window compared with the mean value in the second window is above a threshold then a “single peak” is said to be detected at the time corresponding to the centre of the first window.
- the second window being located to the left of, or lagging the first window
- the time duration of each collection of peaks is then calculated and, if the duration is less than a threshold value, the collection of peaks is determined not to be related to blade resonance and is discounted from further consideration.
- the collection of peaks are grouped within hatched lines 100 .
- the density of these collections of peaks is then calculated and compared with a threshold value. Any collection of peaks that is above the threshold is considered to be related to blade resonance, all other collections of peaks are considered to be false peaks. The result of applying this threshold value is depicted in FIG. 11 , where a single collection of peaks related to blade resonance is detected.
- the threshold values used can be determined empirically based on blade parameters and by analysis of the blade resonance oscillations.
- the gap duration threshold is 2 seconds
- the collection duration is 3 seconds
- the collection density is 65%.
- the second method of determining the presence of true peaks from false peaks is to use a three window method. This is substantially the same method as the two window method except that the “single peak” detection is based on the following equation:
- S i , S l and S r are mean values of envelope in the central, left and right windows respectively.
- the size and separation of the windows is selected empirically primarily based on the blade parameters and by analysis of the blade resonance oscillations.
- the amplitudes of resonance peaks corresponding to the frequency of the first and higher blade modes may be found. These values can be used to determine the health of the blades.
- the nonlinearity level of a blade increases with the appearance of a fatigue crack.
- FIG. 12 depicts the power spectral density response of an un-cracked blade at resonance over a 3 second duration. Applying the Fourier transform it is possible to generate a plot of the Fourier magnitude of the signal in the frequency domain.
- the frequency response is taken from a bench shaker test and the data relates to the fourth shaft order.
- Fundamental and higher harmonics of blade resonance oscillations are identified in the data using the moving window method in the frequency domain using three windows as described above.
- the fundamental frequency and a number of higher harmonics are detected as depicted by numerals 102 - 110 .
- a cracked blade having an 8% crack size provided a resonance response as depicted in FIG. 13 .
- the Fourier transform After applying the Fourier transform the Fourier magnitude in the frequency domain can be plotted. This is substantially of the same form as the plot for the un-cracked blade.
- a number of higher harmonics are detected that were not able to be detected for the blade in its un-cracked condition.
- the harmonics detected are indicated as numerals 102 to 124 .
- X i represents the normalised harmonic amplitude of blade resonance oscillations, and can be represented as:
- X i is the un-normalised harmonic amplitude of blade resonance oscillations
- X L and X R are averaged spectral amplitudes (i.e. interference amplitudes) of left and right windows.
- the value for F may be compared against a threshold value to determine the cracked condition. Since each test can give slightly different values for F an alternative is to average F over a number of tests and to compare the average with the threshold.
- the presence of a crack is determined using bicoherence.
- the bicoherence depends on two frequencies and is defined by the Fourier transforms of blade resonance at three frequencies and can be represented by the equation:
- Bicoherence contains phase information between harmonics of blade resonance oscillations.
- k 0 is the blade fundamental resonant frequency and (p, q) is an integer pair.
- p and q may be any integers.
- Bicoherence is a measure of coupling between two selected harmonics of the blade resonance oscillations.
- the real and imaginary components of the bicoherence of the two selected harmonics p and q are compared with a discriminant function 101 to determine the presence of a crack.
- the plot is made in two dimensional space for the blade in an uncracked condition and additionally in the cracked condition—with an 8% crack.
- the position and area of real and imaginary components of bicoherence value of the fundamental and second harmonics for cracked blades is notably different from the area of real and imaginary components of bicoherence value of the fundamental and second harmonics for un-cracked blades.
- time-frequency transforms may be used e.g. wavelet, Wigner-Ville in place of the short-time chirp-Fourier transform, though with a reduced accuracy.
- the method may be realised by programming a computer to run the method steps described in this invention.
- the computer program may be stored on a recording media.
- the invention will also have application in reciprocating apparatus, such as spark ignition engines, where periodic signals are generated in response to the movement of a piston or such like.
- reciprocating apparatus such as spark ignition engines
- periodic signals are generated in response to the movement of a piston or such like.
- pressure vessels such as a ship or other container are pressure tested by cycling through a series of pressure or temperature values, if a frequency response is induced it is possible to adapt the invention as described herein, with routine skill and experimentation, to such apparatus and thereby determine if there is a change to the apparatus.
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited. The shaft has an order related component that varies with the rotational velocity of the shaft. Modal responses are increased when the natural frequency range of the selected blade mode intersects with one of the order related components. By applying a short time chirp-Fourier transform with a frequency speed that is a function of a rate of change in the rotational velocity of the shaft a selected signal can be isolated. Cracks in the blades can be detected from the isolated signal.
Description
- This invention concerns a method and apparatus for monitoring rotating and reciprocating apparatus and particularly a method and apparatus for monitoring rotating blades mounted on a shaft in a gas turbine engine.
- Apparatus with rotary components, such as gas turbine engines, generate signals which are periodic with respect to shaft rotation. The frequency of the signals is related to the angular velocity of the respective shaft and hence the engine speed. These rotation-periodic signals are conventionally known as order components. As the angular speed of rotation increases typically the order components similarly increase in frequency.
- At a given engine speed, a number of these engine orders are generally active and result in corresponding vibration responses in the engine which are measurable e.g. as stress or acceleration. Each vibration response generally has the same frequency as the engine order forcing frequency that generated it.
- These orders may be represented graphically.
FIG. 1 represents a Campbell diagram for a shaft within a gas turbine engine. The y-axis represents frequency of the rotating shaft in Hertz and the x-axis represents shaft speed in revolutions per minute (rpm). - Each shaft has a number of orders, which represent the first vibration harmonic and subsequent harmonics of the rotating shaft. The first, eighth and eleventh and thirteenth harmonic of the shaft are indicated as
lines FIG. 1 . - When components, such as blades, are mounted to the shaft these are subject to vibration excitation, the amplitude of which is at its greatest when the vibration is at a frequency that corresponds to natural frequency of the blade. Each natural frequency is associated with a particular mode, each of which is a different combination of blade deflections.
- The blades can be induced to vibrate at their natural frequency where frequencies of their modes intersect the engine order lines. A typical plot of blade modes is depicted on
FIG. 1 aslines - It is known to measure the vibrations of the blade to determine the operation and health of the blade. Health monitoring of the blades is important to prevent failure of a component within the engine that may result in significant damage to the engine around and downstream of the failed component.
- The vibrations may be measured using, for example, strain gauges, laser transmitters or capacitance and eddy probes. Where a crack, or some other fault is detected in a component it is possible to replace the faulty component before it fails and causes additional damage. Such a replacement results in reduced downtime of the engine and thus an improved cost per hour operation.
- In U.S. Pat. No. 4,422,333 it is proposed to use acoustic data to monitor the health of a blade. A microphone is placed adjacent a row of blades and the acoustic energy in the vicinity of the rotating portion sensed to generate a composite representative of the broadband acoustic spectrum. After signal processing the characteristic Doppler waveform of the blade vibrations is displayed and analysed to indicate the location of excessive vibrations.
- Each row of blades requires its own microphone to sense the acoustic energy from its respective row. For a complex gas turbine engine, which may have about 20 rows of blades split between the fan, compressor and turbine, significant numbers of sensors are required.
- It is an object of the present invention to seek to provide an improved method and apparatus for sampling vibration data from a device that produces an order related response. The method is capable of identifying defects such as, for example, cracks, or other artifacts that may not be defects.
- According to a first aspect of the present invention there is provided a method of sampling data from a rotatable shaft comprising the steps: determining at least one order related component of the shaft; determining at least one vibration mode of articles functionally mounted to the shaft; selecting one of the vibration modes; selecting one of the order related components that has an instantaneous frequency which intersects the natural frequency range of the selected mode; rotating the shaft and sampling the data where the instantaneous frequency of the selected order and natural frequency range of the selected vibration mode intersect.
- Preferably the shaft is rotated with an increasing or decreasing speed of rotation. Preferably the sampling of the data begins immediately before the selected order and selected vibration mode intersect. Preferably the sampling of the data ends immediately after the selected order and selected vibration mode intersect.
- The selected order may be the first engine order.
- One of the further problems with the teaching in the prior art document U.S. Pat. No. 4,422,333 is that it fails to provide an effective mechanism to separate the required signal from the background noise of the engine.
- Therefore, according to a second aspect of the present invention there is provided a method of isolating a selected periodic response from a plurality of periodic responses, the method comprising the steps: operating a shaft at a varying rotational velocity to provide a signal that comprises a plurality of periodic responses; transforming the signal using a short-time chirp Fourier transform, thereby isolating the selected periodic response and characterised in that the chirp rate of the short-time chirp Fourier transform is a function of the rate of change of the shaft velocity.
- The shaft may be one of a plurality of shafts in a gas turbine engine. The varying rotational velocity occurs during acceleration or deceleration of the engine.
- The periodic responses may be resonance oscillations of vibration modes of articles functionally mounted to the shaft. Preferably the method further comprises the step of determining the order related component of the shaft, selecting one of the vibration modes of the articles transforming the signal where the order and natural frequency range of selected vibration mode intersect.
- The articles may be blades. The signal is a vibro-acoustic signal. Preferably the vibro-acoustic signal is captured by an appropriate transducer, for example, a microphone, accelerometer, strain gauge, pressure transducer, etc.
- According to a third aspect of the present invention there is provided a method of determining true collections of peaks in an envelope of vibro-acoustic response data, comprising the steps: a) providing two sample windows each enclosing a portion of the vibro-acoustic response data, b) calculating the mean value of the envelope of the vibro-acoustic response within each window, c) calculating the ratio of mean value in the first window to the mean value in the second window; the second window lagging the first window d) comparing the ratio against a threshold, e) indicating a single peak where the compared ratio equals or exceeds the threshold, f) moving the sample windows along the envelope of the vibro-acoustic response data and repeating steps b) to e) at least once, g) calculating the spacing between adjacent single peaks, h) grouping adjacent single peaks into a collection of peaks, each single peak in the collection being separated from an adjacent single peak by a spacing that is less than a threshold value, adjacent collections being separated by a spacing that is greater than the threshold value, i) removing collections of peaks that have a length less than a threshold, j) calculating the density of the remaining collections of peaks, k) comparing the calculated density of each collection of peaks with a threshold value, wherein the true collections have a calculated density greater than the threshold value.
- Preferably the method further comprising the step of providing a further sample window, the further sample window leads the first window with respect to the envelope of vibro-acoustic response data; step c) being modified in that ratio of mean value in the first window to the mean value in the second window and the ratio of the mean value in the first window to the mean value in the further window is calculated; step e) being modified in that a single peak in indicated when both calculated ratios are above the threshold.
- According to a fourth aspect of the present invention there is provided a method of determining an artifact in a component comprising the steps: a) exciting the component to induce a resonance response; b) detecting higher harmonics in the averaged power spectral density of resonance response; c) calculating the normalised amplitude of two or more higher harmonics, d) comparing the sum of the normalised amplitude of the two or more higher harmonics with a threshold value thereby determining the presence of an artifact.
- The component may be a blade. The blade may be mounted on a shaft. Preferably the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
- According to a fifth aspect of the present invention there is provided a method for determining an artifact in a component comprising the steps: a) exciting the component to induce a resonance response, b) detecting fundamental and higher harmonics in the averaged power spectral density of resonance response, c) calculating the normalised amplitude of two or more harmonics, at least one of the harmonics being the fundamental harmonic, d) calculating the ratio of the sum of the normalised amplitude of the, or each, higher harmonic and the normalised amplitude of the fundamental harmonic; e) comparing the value of the ratio with a threshold, an artifact being determined by comparing the value with the threshold.
- The component may be a blade. The blade may be mounted on a shaft. Preferably the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
- According to a sixth aspect of the present invention there is provided a method for determining an artifact in a component comprising the steps: a) exciting the component to induce a resonance response, b) calculating the real and imaginary components of bicoherence b of a resonance response at pk0 and qk0 wherein p and q are integers and k0 is the component resonant frequency, c) determining a location of a point related to calculated components in real and imaginary two dimensional space; the location of the point determining the presence of the artifact.
- Preferably the location of the point is compared with a discriminant function. Preferably the discriminant function is linear.
- The component may be a blade. The blade may be mounted on a shaft. Preferably the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
- Embodiments of the present invention will now be described by way of example only and with reference to the accompanying drawings, in which:—
-
FIG. 1 is a representative Campbell diagram for a shaft in a gas turbine engine having a row of blades. -
FIG. 2 is a schematic of a three shaft engine. -
FIG. 4 shows the amplitude-time-frequency distribution of envelope for a LP, IP and HP shaft after extraction from a vibro-acoustic signal, using short time chirp Fourier transform. -
FIG. 5 is a typical amplitude response of a blade in the time domain under excitation from order related components with changing rotational velocity. -
FIG. 6 is a typical amplitude envelope of a blade in the frequency domain under excitation from order related components with changing rotational velocity (high signal/noise ratio) -
FIG. 7 is a typical amplitude envelope of a blade in the time domain under excitation from order related components with changing rotational velocity (low signal/noise ratio). -
FIG. 8 depicts detected single peaks within the envelope of vibro-acoustic signal -
FIG. 9 depicts the collections of single peaks, the collections being separated by gaps greater than a pre-determined size, here there are 6 collections depicted -
FIG. 10 depicts collections of single peaks that have a duration greater than a pre-determined value, 4 collections are depicted -
FIG. 11 depicts collections of single peaks that have a density greater than a pre-determined value, 1 collection is depicted -
FIG. 12 depicts the power spectral density of resonance response of an un-cracked blade. -
FIG. 13 depicts the power spectral density of resonance response of a cracked blade. -
FIG. 14 depicts the sum of the normalised amplitude of two or more higher harmonics against sample number of cracked and un-cracked blade. -
FIG. 15 is a graphical representation of the calculated real and imaginary components of bicoherence for cracked and un-cracked blades. - As discussed earlier,
FIG. 1 represents a Campbell diagram for an intermediate pressure (IP) compressor, the IP compressor being driven by an IP shaft within a Rolls-Royce multi shaft gas turbine engine. -
FIG. 2 shows a schematic longitudinal section of the three coaxial shafts. Low pressure (LP)shaft 30 occupies the central position and is surrounded in turn by theIP shaft 32 and the high pressure (HP)shaft 34. The LP shaft connects the fan and the LP turbine (not shown), the IP shaft connects the IP compressor and IP turbine (not shown) and the HP shaft connects the HP compressor and the HP turbine. -
LP shaft 30 carries asingle pole tachometer 36 which is conveniently used for shaft balancing operations.IP shaft 32 carries a 60pole tachometer 38 which is conventionally used for standard shaft speed measurements for engine control purposes.HP shaft 34 is connected viabevel gear 40 and step asidegearbox 42 to main (external)gearbox 44, with atachometer 46 connected to the output of the main gear box. -
Tachometer 36 produces a signal pulse for each rotation of the LP shaft, and hence the rotational frequency (i.e. shaft speed) of the LP shaft can be determined from the inverse of the period between signal pulses.Tachometer 38 produces 60 signal pulses for each rotation of theIP shaft 32, and hence the rotational frequency of the IP shaft can be determined from the inverse of 60 times the period between the signal pulses.Tachometer 46 measures the rotational frequency of the output of themain gearbox 44. However, as the gearing ratios of the main and step aside gearboxes 44, 42 andbevel gear 40 are known, the rotational frequency of the HP shaft can be inferred fromtachometer 46. The rotational frequencies measured by the tachometers provide the engine orders (e.g. fundamental and harmonic components) for each shaft. - It will be appreciated that though a Campbell diagram can be obtained for each shaft, it is a Campbell diagram of the IP shaft that will be considered for the purposes of this description.
- The Campbell diagram of
FIG. 1 depicts a plot of frequency against the speed of rotation of the IP shaft. Four shaft orders are shown representing the first 2, eighth 4, eleventh 6 and thirteenth 8 engine order. - Connected to the IP shaft is a single stage IP turbine (not shown) and a multi stage IP compressor (not shown). Each stage comprises a single row of multiple blades. Each blade within a stage will vibrate at its natural frequency and each blade within a stage may have slight manufacturing variations, meaning that the natural frequency of blades within a stage may slightly vary across a narrow range.
- The natural frequencies of a set of blades for different modes are represented graphically on
FIG. 1 aslines mode example lines - Certain combinations of blade mode and engine order will produce a higher resonance response than other combinations of blade mode and engine order. It is a matter of selecting the engine order and blade mode to best facilitate the blade resonance detection.
- The fundamental frequencies of engine orders are calculated from the tachometer signals. The frequency of the second order is twice the fundamental frequency at the rotational velocity and so on.
- The base-line mean and variance of the natural frequencies of blade modes are measured from experimental data taken during engine development. The data is typically obtained during bench tests, where the blade is clamped and then excited by either shaking or passing an air-jet past over the blade. The obtained data is retained.
- A transducer, for example, an accelerometer or microphone, capable of sensing a vibro-acoustic signal, is placed at a position where it can capture the signal of the rotating system of interest. The captured vibro-acoustic data is retained for analysis.
- Because the vibro-acoustic data obtained has a large amount of background interference that hides the vibro-acoustic response (signal) of the components of whose health is to be monitored it is necessary to process the vibro-acoustic data. In particular it is necessary to separate the desired response from responses of other components, which are similarly order related and serve to mask the desired signal.
- All the vibro-acoustic responses typically have a low signal to noise ratio. To improve the signal to noise ratio the method analyses the frequency responses of the blades mounted within the IP compressor at the points where a natural frequency range of blades intersects a selected engine order and the amplitudes of the blade modal responses are highest.
- As the rotational speed of the IP shaft is varied, either by accelerating or decelerating, the natural frequency ranges of blade modes of the first set of blades on the IP compressor cross one or more of the shaft orders; blade resonance responses are generated during these crossings. Similarly, the natural frequency ranges of blade modes of the second, third and fourth sets of blades also cross the shaft orders; blade resonance responses are also generated during these crossings. Correspondingly, the natural frequency ranges of modes of blades attached to the LP and HP shaft will also cross their respective shaft orders; blade resonance responses are also generated during these crossings. The captured vibro-acoustic data includes all these resonant responses in addition to other interference. Consequently it is necessary to isolate the desired signal.
- It is important to note that whilst advanced time-frequency techniques, such as Wigner-Ville or wavelet transforms, can be used for processing non-stationary vibro-acoustical shaft orders having a linear and non-linear variation of the shaft frequency in time; however, these forms of processing lose accuracy in comparison with short-time chirp-Fourier transform.
- The signal obtained during acceleration and deceleration is obtained during nonlinear variation of the shaft frequency in time. This signal may conveniently be called a “piece-wise engine order” and is processed using a short-time chirp-Fourier transform. This transform has the form:
-
- where h(t) is a time window, x1(t) is a “piece-wise engine order”, T is the centre of the window and c2(t) is the variable frequency speed of the transform, f is frequency.
- The frequency speed of the transform is constant throughout the duration τi of constant frequency speed of a “piece-wise engine order” i=1, 2, . . . N, N is a number of linear parts in the piece-wise frequency-time dependency of a “piece-wise engine order”.
- By frequency speed it is meant the speed of frequency change or, to put it another way, the rate of change of the frequency, or “chirp rate”.
- The short-time chirp-Fourier transform could be used with different windows, e.g. a rectangular window, a Gaussian window, Hamming window etc. It selectively detects the piece-wise shaft orders whilst the shaft speed is varied.
- As discussed above, the recorded vibro-acoustic data comprises order related components from the LP, IP and HP shafts. The selected order related components from the IP shaft is isolated from the order related components of the other shafts by evaluating the piece-wise frequency-time dependency of the selected order related components and frequency speed for each part of the dependency and processing the acoustic or vibration data by the short-time chirp-Fourier transform with appropriate durations and frequency speed. By appropriate durations it is meant durations of the selected order related components with constant frequency speed.
- In this example the frequency speed of
engine order 1 of the IP shaft is 0.027 Hz/s. Consequently, the frequency speed of the transform for detecting the blade resonances excited byIP engine order 4 is 4 times that value i.e. 0.108 Hz/s. - After transform it is possible to graphically represent the frequency responses for the IP, LP and HP shafts on 3D plot of amplitude vs instantaneous frequency and time; such a plot is depicted in
FIG. 4 . - In
FIG. 4 , as the engine accelerates i.e. time increases, the value of instantaneous frequency of the engine orders similarly increases. Separated out from the data obtained by the transducer and processed by the short-time chirp-Fourier transform is a frequency/time/magnitude plot of two shaft orders of theHP shaft IP shaft 54, and plots of two shaft orders of theLP shaft - Looking at the frequency/time/magnitude plot of the IP shaft it is possible to see that the magnitude varies both with time and frequency. Peaks are observed where the instantaneous frequency of 4th shaft order of the IP shaft intersects with the natural frequency range of the blade modes of the blades connected to the IP shaft. The
first peak 60 related to the resonant oscillations of a first row of blades and thesecond peak 62 related to the resonance oscillations of a second row of blades. Other peaks along the order may relate to resonant oscillations of higher modes of the blade rows. It is possible to determine which row and which mode is excited at a given frequency by referring to the Campbell diagram for the relevant shaft. - As it is possible to separate out the frequency response of each order for each shaft it is possible, with further signal processing, to detect peaks in the data and identify their timing, duration, frequency and amplitude. Beneficially, because the engine accelerates and decelerates through the range of natural frequencies of the blades mounted to each shaft in an engine it is possible to obtain and isolate data on each row of blades from one set of vibro-acoustic data and to then signal process these separately.
- After applying the short-time chirp-Fourier transform as described above it is possible to determine the magnitude of the short-time chirp-Fourier transform vs. time and instantaneous frequency for each order of the IP
-
CTx(t,f) - shaft.
- From the tachometer signal it is possible to obtain the piece-wise time-frequency variation fIP(t) of the first engine order of the IP shaft.
- The envelope of magnitude of chirp Fourier transform of the selected nth engine order of the IP shaft can
-
S(T,fIP,c2) - therefore be:
- The envelope may be displayed in both the time and frequency domain as shown in
FIG. 5 andFIG. 6 . The blade resonant peaks may be detected from either of these envelopes using similar methods, but for the purpose of this description the detection method using the envelope in the time domain will be described. - The signal is still relatively noisy and it is necessary to distinguish true blade resonance peaks from false peaks.
- A first method, conveniently known as a two moving window method, is described with reference to
FIG. 7-11 . Two data windows are used to analyse amplitude of envelope against time. The windows are scanned through the data range with their size and spacing being maintained, the right window leading the left window. The mean value within each window is calculated and if the ratio of the mean value in the first window compared with the mean value in the second window is above a threshold then a “single peak” is said to be detected at the time corresponding to the centre of the first window. The second window being located to the left of, or lagging the first window - After scanning the windows through the envelope data a series of “single peaks” have been detected. These are shown in
FIG. 8 , where the Y axis is the calculated ratio and the X axis is the time. To estimate whether detected single peaks are true resonance peaks or false peaks, firstly the gap durations between adjacent peaks is calculated and the single peaks grouped into collections of peaks, each collection being separated by gap duration above or equal to a threshold value. This is depicted inFIG. 9 . Thus, within each collection the peaks are separated from adjacent peaks by a gap duration that is less than the threshold value. - The time duration of each collection of peaks is then calculated and, if the duration is less than a threshold value, the collection of peaks is determined not to be related to blade resonance and is discounted from further consideration. In
FIG. 10 , the collection of peaks are grouped within hatchedlines 100. - The density of these collections of peaks is then calculated and compared with a threshold value. Any collection of peaks that is above the threshold is considered to be related to blade resonance, all other collections of peaks are considered to be false peaks. The result of applying this threshold value is depicted in
FIG. 11 , where a single collection of peaks related to blade resonance is detected. - It will be appreciated that the threshold values used can be determined empirically based on blade parameters and by analysis of the blade resonance oscillations. For the example given above, the gap duration threshold is 2 seconds, the collection duration is 3 seconds and the collection density is 65%.
- The second method of determining the presence of true peaks from false peaks is to use a three window method. This is substantially the same method as the two window method except that the “single peak” detection is based on the following equation:
-
- where Si, Sl and Sr are mean values of envelope in the central, left and right windows respectively.
- Thus, if ratios of the “signal mean” in the central window to the “interference mean” in the left and right windows are simultaneously more than threshold, then the “single peak” detection is true.
- The size and separation of the windows is selected empirically primarily based on the blade parameters and by analysis of the blade resonance oscillations.
- By this method the amplitudes of resonance peaks corresponding to the frequency of the first and higher blade modes may be found. These values can be used to determine the health of the blades.
- The nonlinearity level of a blade increases with the appearance of a fatigue crack.
-
FIG. 12 depicts the power spectral density response of an un-cracked blade at resonance over a 3 second duration. Applying the Fourier transform it is possible to generate a plot of the Fourier magnitude of the signal in the frequency domain. In the example described inFIGS. 12-14 the frequency response is taken from a bench shaker test and the data relates to the fourth shaft order. - Fundamental and higher harmonics of blade resonance oscillations are identified in the data using the moving window method in the frequency domain using three windows as described above. For the un-cracked blade the fundamental frequency and a number of higher harmonics are detected as depicted by numerals 102-110.
- A cracked blade having an 8% crack size provided a resonance response as depicted in
FIG. 13 . After applying the Fourier transform the Fourier magnitude in the frequency domain can be plotted. This is substantially of the same form as the plot for the un-cracked blade. However, upon application of the peak detection method in the frequency domain a number of higher harmonics are detected that were not able to be detected for the blade in its un-cracked condition. The harmonics detected are indicated asnumerals 102 to 124. - The sum of the normalised spectral amplitudes of higher harmonics of the blade resonant oscillations for each of the cracked and un-cracked situations can be calculated using the formula:
-
- where
X i represents the normalised harmonic amplitude of blade resonance oscillations, and can be represented as: -
- Xi is the un-normalised harmonic amplitude of blade resonance oscillations, XL and XR are averaged spectral amplitudes (i.e. interference amplitudes) of left and right windows.
- The ratio of this sum to the normalised amplitude
X 1 of the fundamental harmonic is then calculated from: -
- From
FIG. 14 it will be apparent that this value for F is indicative of a cracked blade. This figure, on the right hand side the value of F calculated after four tests of the un-cracked blade. On the left hand side are six values of F calculated after six tests of the cracked blade. - The value for F may be compared against a threshold value to determine the cracked condition. Since each test can give slightly different values for F an alternative is to average F over a number of tests and to compare the average with the threshold.
- In an alternative method it is the sum of the amplitudes of the normalized higher harmonics that is compared with a threshold value to determine the presence of a crack.
- In a further method the presence of a crack is determined using bicoherence. The bicoherence depends on two frequencies and is defined by the Fourier transforms of blade resonance at three frequencies and can be represented by the equation:
-
- where Xm(k) is the discrete Fourier transform of the mth segment of the blade resonance oscillations at discrete frequency k, * is complex conjugate operator.
- Bicoherence contains phase information between harmonics of blade resonance oscillations.
- When diagnosing a crack it is the real and imaginary components of bicoherence at frequencies that are integer multiples of the resonant frequency of the blade:
-
b(pk0, qk0) - where k0 is the blade fundamental resonant frequency and (p, q) is an integer pair. p and q may be any integers.
- Bicoherence is a measure of coupling between two selected harmonics of the blade resonance oscillations. The real and imaginary components of the bicoherence of the two selected harmonics p and q are compared with a
discriminant function 101 to determine the presence of a crack. -
FIG. 15 depicts a complex plot of the calculated real and imaginary components of the bicoherence for fundamental and second harmonics of blade resonance oscillations i.e. p=1 and q=2. The plot is made in two dimensional space for the blade in an uncracked condition and additionally in the cracked condition—with an 8% crack. The position and area of real and imaginary components of bicoherence value of the fundamental and second harmonics for cracked blades is notably different from the area of real and imaginary components of bicoherence value of the fundamental and second harmonics for un-cracked blades. - Once a crack is detected it is possible to repair or replace the blade in which it is located. This may be done as part of a special service, or at the next scheduled service if the blade will survive till that point.
- Various modifications may be made without departing from the scope of the invention.
- For example, other time-frequency transforms may be used e.g. wavelet, Wigner-Ville in place of the short-time chirp-Fourier transform, though with a reduced accuracy.
- The technology finds application in marine, industrial gas turbines engines and for other rotating machinery, such as diesel engines or compressors. It can be used to detect other order related responses from bladed disks, gears or other components where a resonant response may be initiated through rotation of the component.
- It will be appreciated that whilst the invention has been described with respect to using a single transducer to record the vibro-acoustic data, multiple transducers may equally be used. The multiple microphones, which may be directional, may record data from single components or stages. Other forms of device (e.g. beamforming system, etc.) that record vibro-acoustic data may replace the single transducer.
- It will also be appreciated that the method may be realised by programming a computer to run the method steps described in this invention. The computer program may be stored on a recording media.
- The invention will also have application in reciprocating apparatus, such as spark ignition engines, where periodic signals are generated in response to the movement of a piston or such like. Similarly, where pressure vessels such as a ship or other container are pressure tested by cycling through a series of pressure or temperature values, if a frequency response is induced it is possible to adapt the invention as described herein, with routine skill and experimentation, to such apparatus and thereby determine if there is a change to the apparatus.
- Whilst endeavouring in the foregoing specification to draw attention to those features of the invention believed to be of particular importance it should be understood that the Applicant claims protection in respect of any patentable feature or combination of features hereinbefore referred to and/or shown in the drawings whether or not particular emphasis has been placed thereon.
Claims (29)
1. A method of isolating a selected periodic response from a plurality of periodic responses, the method comprising:
operating a shaft at a varying rotational velocity to provide a signal that comprises a plurality of periodic responses; and
transforming the signal using a short-time chirp Fourier transform, thereby isolating the selected periodic responses and wherein the frequency speed of the short-time chirp Fourier transform is a function of the rate of change of the shaft velocity.
2. A method according to claim 1 , wherein the shaft is one of a plurality of shafts in a gas turbine engine.
3. A method according to claim 1 , wherein the varying rotational velocity occurs during acceleration of the engine.
4. A method according to claim 1 , wherein the periodic responses are resonant oscillations of vibration modes of articles functionally mounted to the shaft.
5. A method according to claim 4 , further comprising:
determining an order related component of the shaft; and
selecting a vibration mode of articles functionally mounted to the shaft transforming the signal where the order and natural frequency range of the selected vibration mode intersect.
6. A method according to claim 4 , wherein the articles are blades.
7. A method according to claim 1 , wherein the signal is a vibro-acoustic signal.
8. A method according to claim 7 , wherein the vibro-acoustic signal is captured by a transducer
9. A method of sampling data from a rotatable shaft comprising the steps:
a) determining at least one order related component of the shaft;
b) determining at least one vibration mode of articles functionally mounted to the shaft;
c) selecting one of the at least one vibration mode;
d) selecting one of the at least one order related component that has an instantaneous frequency which intersects the natural frequency range of the selected mode;
e) rotating the shaft and sampling the data where the instantaneous frequency of the selected order and natural frequency range of the selected vibration mode intersect.
10. A method according to claim 9 , wherein the shaft is rotated with an increasing or decreasing speed of rotation.
11. A method according to claim 10 , wherein the sampling of the data begins immediately before the instantaneous frequency of the selected order and natural frequency range of the selected vibration mode intersect.
12. A method according to claim 10 , wherein the sampling of the data ends immediately after the instantaneous frequency of the selected order and natural frequency range of the selected vibration mode intersect.
13. A method according to claim 9 , wherein the selected order is the lowest order having an instantaneous frequency that intersects with the natural frequency range of the selected vibration mode.
14. A method of determining true collections of peaks in an envelope of vibro-acoustic response data, comprising:
a) providing two sample windows each enclosing a portion of the vibro-acoustic response data, the second window lagging the first window,
b) calculating the mean value of the envelope of the vibro-acoustic response within each window,
c) calculating the ratio of mean value in the first window to the mean value in the second window,
d) comparing the ratio against a thresholds
e) indicating a single peak where the compared ratio differs by a predetermined amount from the thresholds
f) moving the sample windows along the envelope of the vibro-acoustic response data and repeating steps b) to e) at least once,
g) calculating the spacing between adjacent single peaks,
h) grouping adjacent single peaks into a collection of peaks, each single peak in the collection being separated from an adjacent single peak by a spacing that is less than a threshold value, adjacent collections being separated by a spacing that is greater than the threshold value,
i) removing collections of peaks that have a length less than a threshold,
j) calculating the density of the remaining collections of peaks, and
k) comparing the calculated density of each collection of peaks with a threshold value, wherein the true peaks have a calculated density greater than the threshold value.
15. A method according to claim 14 , further comprising providing a further sample window, the further sample window leading the first window with respect to the envelope of vibro-acoustic response data; step c) being modified in that the ratio of the mean value in the first window to the mean value in the second window and the ratio of the mean value in the first window to the mean value in the further window are calculated; and step e) being modified in that a single peak in indicated when both calculated ratios are above the threshold.
16. A method of determining an artifact in a component comprising:
a) exciting the component to induce a resonance response,
b) detecting higher harmonics in the averaged power spectral density of resonance response,
c) calculating the normalised amplitude of two or more higher harmonics of component resonance oscillations and
d) comparing the sum of the normalised amplitude of the two or more higher harmonics with a threshold value thereby determining the presence of an artifact.
17. A method according to claim 16 , wherein the component is a blade.
18. A method according to claim 17 , wherein the blade is mounted on a shaft.
19. A method according to claim 17 , wherein the blade is excited by rotating the shaft at a selected rotational velocity such that a frequency of an order related component of the shaft intersects with the natural frequency range of the fundamental harmonic of the selected blade mode.
20. A method for determining an artifact in a component comprising:
a) exciting the component to induce a resonance responses
b) detecting higher harmonics in the averaged power spectral density of resonance response,
c) calculating the normalised amplitude of two or more harmonics, at least one of the harmonics being the fundamental harmonic,
d) calculating the ratio of the sum of the normalised amplitude of the higher harmonic or each higher harmonic and the normalised amplitude of the fundamental harmonic, and
e) comparing the value of the ratio with a threshold, an artifact being determined by comparing the value with the threshold.
21. A method according to claim 20 , wherein the component is a blade.
22. A method according to claim 21 , wherein the blade is mounted on a shaft.
23. A method according to claim 22 , wherein the blade is excited by rotating the shaft at a selected rotational velocity such that an instantaneous frequency of an order related component of the shaft intersects with the frequency of the fundamental harmonic of the selected blade mode.
24. A method for determining an artifact in a component comprising:
a) exciting the component to induce a resonance response,
b) calculating the real and imaginary components of bi-coherence b of a resonance response at pk0 and qk0 wherein p and q are integers and k0 is the component resonant frequency, and
c) determining a location of a point related to calculated components in real and imaginary two-dimensional space, the location of the point determining the presence of an artifact.
25. A method according to claim 24 , wherein the location of the point is compared with a discriminate function.
26. A method according to claim 25 , wherein the discriminate function is linear.
27. A method according to claim 24 , wherein the component is a blade.
28. A method according to claim 27 , wherein the blade is mounted on a shaft.
29. A method according to claim 28 , wherein the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0525936.1 | 2005-12-21 | ||
GBGB0525936.1A GB0525936D0 (en) | 2005-12-21 | 2005-12-21 | Methods of analysing apparatus |
PCT/GB2006/004546 WO2007071912A2 (en) | 2005-12-21 | 2006-12-06 | Method of monitoring blades mounted on a shaft in a gas turbine engine |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/GB2006/004546 A-371-Of-International WO2007071912A2 (en) | 2005-12-21 | 2006-12-06 | Method of monitoring blades mounted on a shaft in a gas turbine engine |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/935,924 Division US10352823B2 (en) | 2005-12-21 | 2013-07-05 | Methods of analysing apparatus |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090082976A1 true US20090082976A1 (en) | 2009-03-26 |
Family
ID=35840811
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/085,943 Abandoned US20090082976A1 (en) | 2005-12-21 | 2006-12-06 | Methods of Analysing Apparatus |
US13/935,924 Active 2030-05-15 US10352823B2 (en) | 2005-12-21 | 2013-07-05 | Methods of analysing apparatus |
US15/018,899 Abandoned US20160187227A1 (en) | 2005-12-21 | 2016-02-09 | Methods of analysing apparatus |
Family Applications After (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/935,924 Active 2030-05-15 US10352823B2 (en) | 2005-12-21 | 2013-07-05 | Methods of analysing apparatus |
US15/018,899 Abandoned US20160187227A1 (en) | 2005-12-21 | 2016-02-09 | Methods of analysing apparatus |
Country Status (4)
Country | Link |
---|---|
US (3) | US20090082976A1 (en) |
EP (1) | EP1966571A2 (en) |
GB (1) | GB0525936D0 (en) |
WO (1) | WO2007071912A2 (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110054822A1 (en) * | 2009-09-03 | 2011-03-03 | Rosemount Inc. | Thermowell vibration frequency diagnostic |
CN103089443A (en) * | 2011-11-04 | 2013-05-08 | 通用电气公司 | Systems And Methods For Use In Monitoring Operation Of A Rotating Component |
US20140180606A1 (en) * | 2005-12-21 | 2014-06-26 | Rolls-Royce Plc | Methods of analysing apparatus |
JP2015046116A (en) * | 2013-08-29 | 2015-03-12 | 沖電気工業株式会社 | Data analysis device and method, program, and recording medium |
CN104748953A (en) * | 2013-12-26 | 2015-07-01 | 通用电气公司 | Methods and systems to monitor health of rotor blades |
CN104748952A (en) * | 2013-12-26 | 2015-07-01 | 通用电气公司 | Methods And Systems To Monitor Health Of Rotor Blades |
US20150267538A1 (en) * | 2014-03-24 | 2015-09-24 | Alstom Technology Ltd | Steam turbine with resonance chamber |
US10352794B2 (en) * | 2012-10-05 | 2019-07-16 | Siemens Energy, Inc. | Turbine blade fatigue life analysis using non-contact measurement and dynamical response reconstruction techniques |
CN110095243A (en) * | 2019-06-05 | 2019-08-06 | 哈尔滨汽轮机厂有限责任公司 | A kind of steam turbine blade natural frequency measurement, device |
CN110687124A (en) * | 2019-10-18 | 2020-01-14 | 佛山科学技术学院 | Blade crack positioning method based on visual vibration measurement and nonlinear bicoherence spectrum |
JPWO2020157818A1 (en) * | 2019-01-29 | 2021-11-18 | Primetals Technologies Japan株式会社 | Diagnostic device and equipment equipped with it and diagnostic method |
US11352958B2 (en) * | 2020-06-03 | 2022-06-07 | Rolls-Royce Plc | Aircraft gas turbine engine with improved response to rotor unbalance |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8313279B2 (en) * | 2008-04-21 | 2012-11-20 | General Electric Company | Dual rotor vibration monitoring |
GB0811073D0 (en) * | 2008-06-18 | 2008-07-23 | Rolls Royce Plc | Timing analysis |
US7941281B2 (en) | 2008-12-22 | 2011-05-10 | General Electric Company | System and method for rotor blade health monitoring |
GB2466817B (en) | 2009-01-09 | 2010-12-08 | Rolls Royce Plc | Determination of blade vibration frequencies and/or amplitudes |
RU2613047C1 (en) * | 2015-11-25 | 2017-03-15 | Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" | Method of vibration diagnostics of bearing supports as part of gas turbine engines using technical microphone |
CN105844049A (en) * | 2016-04-11 | 2016-08-10 | 同济大学 | Method for extracting acceleration main-order vibration signals on active mount passive side in real time |
EP3296195B1 (en) * | 2016-09-16 | 2019-10-30 | Ratier-Figeac SAS | Propeller health monitoring |
US10941725B2 (en) | 2017-06-27 | 2021-03-09 | Rolls-Royce Corporation | Vibration feedback controller |
DE102020200936A1 (en) * | 2020-01-27 | 2021-07-29 | MTU Aero Engines AG | Method, device and graphical user interface for analyzing a mechanical object |
DE102021204463A1 (en) * | 2021-05-04 | 2022-11-10 | Ziehl-Abegg Se | Method for determining the vibration behavior of an electric motor and/or its installation environment, as well as the corresponding electric motor and fan |
CN115560648B (en) * | 2022-12-01 | 2023-03-14 | 成都市鸿侠科技有限责任公司 | Impeller blade radial end face runout continuous and rapid measuring tool |
CN115808236B (en) * | 2023-02-02 | 2023-05-05 | 武汉理工大学 | Marine turbocharger fault on-line monitoring and diagnosing method and device and storage medium |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5152172A (en) * | 1989-03-23 | 1992-10-06 | Electric Power Research Institute | Operating turbine resonant blade monitor |
US5412985A (en) * | 1992-09-18 | 1995-05-09 | Ametek Aerospace Products, Inc. | System and method for ratiometrically processing sensed speed and vibration signals for a non-uniformly rotating body |
US5471880A (en) * | 1994-04-28 | 1995-12-05 | Electric Power Research Institute | Method and apparatus for isolating and identifying periodic Doppler signals in a turbine |
US6208946B1 (en) * | 1997-09-30 | 2001-03-27 | Advantest Corp. | High speed fourier transform apparatus |
US20020035438A1 (en) * | 2000-01-12 | 2002-03-21 | Prince Thomas A. | Fast chirp transform |
US20070006636A1 (en) * | 2003-04-11 | 2007-01-11 | Oxford Biosignals Limited | Method and system for analysing tachometer and vibration data from an apparatus having one or more rotary components |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5631327A (en) | 1979-08-24 | 1981-03-30 | Hitachi Ltd | Method of diagnosing vibration of rotary machine |
US4408294A (en) * | 1981-03-27 | 1983-10-04 | General Electric Company | Method for on-line detection of incipient cracks in turbine-generator rotors |
US4422333A (en) * | 1982-04-29 | 1983-12-27 | The Franklin Institute | Method and apparatus for detecting and identifying excessively vibrating blades of a turbomachine |
US5258923A (en) * | 1987-07-22 | 1993-11-02 | General Electric Company | System and method for detecting the occurrence, location and depth of cracks in turbine-generator rotors |
US4918381A (en) | 1989-04-06 | 1990-04-17 | Hewlett-Packard Company | Automated method for determining total harmonic distortion |
DE4127395A1 (en) * | 1991-08-19 | 1993-02-25 | Siemens Ag | METHOD AND DEVICE FOR DETECTING AND LOCATING CHANGES ON A COMPONENT OF A TURBINE |
US5501105A (en) | 1991-10-02 | 1996-03-26 | Monitoring Technology Corp. | Digital signal processing of encoder signals to detect resonances in rotating machines |
US5365787A (en) | 1991-10-02 | 1994-11-22 | Monitoring Technology Corp. | Noninvasive method and apparatus for determining resonance information for rotating machinery components and for anticipating component failure from changes therein |
US5343404A (en) | 1992-11-12 | 1994-08-30 | Maritec Corp. | Precision digital multimeter and waveform synthesizer for multi-signals with distorted waveforms embedded in noise |
US5483833A (en) | 1994-03-22 | 1996-01-16 | Martin Marietta Energy Systems, Inc. | Method and apparatus for monitoring aircraft components |
US6289735B1 (en) * | 1998-09-29 | 2001-09-18 | Reliance Electric Technologies, Llc | Machine diagnostic system and method for vibration analysis |
US6526356B1 (en) | 2001-06-19 | 2003-02-25 | The Aerospace Corporation | Rocket engine gear defect monitoring method |
GB0202348D0 (en) * | 2002-02-01 | 2002-03-20 | Bae Systems Plc | Damping of vibrations |
PL200003B1 (en) * | 2002-08-26 | 2008-11-28 | Abb Sp Zoo | Method of detection and automatic identification of defects of technological equipment |
EP1776622B1 (en) * | 2004-07-02 | 2012-08-29 | University of Alberta | Detection and quantification of stiction |
US7546769B2 (en) | 2005-12-01 | 2009-06-16 | General Electric Compnay | Ultrasonic inspection system and method |
GB0525936D0 (en) * | 2005-12-21 | 2006-02-01 | Rolls Royce Plc | Methods of analysing apparatus |
-
2005
- 2005-12-21 GB GBGB0525936.1A patent/GB0525936D0/en not_active Ceased
-
2006
- 2006-12-06 US US12/085,943 patent/US20090082976A1/en not_active Abandoned
- 2006-12-06 WO PCT/GB2006/004546 patent/WO2007071912A2/en active Application Filing
- 2006-12-06 EP EP06820429A patent/EP1966571A2/en not_active Withdrawn
-
2013
- 2013-07-05 US US13/935,924 patent/US10352823B2/en active Active
-
2016
- 2016-02-09 US US15/018,899 patent/US20160187227A1/en not_active Abandoned
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5152172A (en) * | 1989-03-23 | 1992-10-06 | Electric Power Research Institute | Operating turbine resonant blade monitor |
US5412985A (en) * | 1992-09-18 | 1995-05-09 | Ametek Aerospace Products, Inc. | System and method for ratiometrically processing sensed speed and vibration signals for a non-uniformly rotating body |
US5471880A (en) * | 1994-04-28 | 1995-12-05 | Electric Power Research Institute | Method and apparatus for isolating and identifying periodic Doppler signals in a turbine |
US6208946B1 (en) * | 1997-09-30 | 2001-03-27 | Advantest Corp. | High speed fourier transform apparatus |
US20020035438A1 (en) * | 2000-01-12 | 2002-03-21 | Prince Thomas A. | Fast chirp transform |
US20070006636A1 (en) * | 2003-04-11 | 2007-01-11 | Oxford Biosignals Limited | Method and system for analysing tachometer and vibration data from an apparatus having one or more rotary components |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10352823B2 (en) * | 2005-12-21 | 2019-07-16 | Rolls-Royce Plc | Methods of analysing apparatus |
US20140180606A1 (en) * | 2005-12-21 | 2014-06-26 | Rolls-Royce Plc | Methods of analysing apparatus |
US20110054822A1 (en) * | 2009-09-03 | 2011-03-03 | Rosemount Inc. | Thermowell vibration frequency diagnostic |
US10156480B2 (en) * | 2009-09-03 | 2018-12-18 | Rosemount Inc. | Thermowell vibration frequency diagnostic |
CN103089443A (en) * | 2011-11-04 | 2013-05-08 | 通用电气公司 | Systems And Methods For Use In Monitoring Operation Of A Rotating Component |
US20130111982A1 (en) * | 2011-11-04 | 2013-05-09 | Thomas James Batzinger | Systems and Methods For Use In Monitoring Operation Of A Rotating Component |
US8505364B2 (en) * | 2011-11-04 | 2013-08-13 | General Electric Company | Systems and methods for use in monitoring operation of a rotating component |
US10352794B2 (en) * | 2012-10-05 | 2019-07-16 | Siemens Energy, Inc. | Turbine blade fatigue life analysis using non-contact measurement and dynamical response reconstruction techniques |
JP2015046116A (en) * | 2013-08-29 | 2015-03-12 | 沖電気工業株式会社 | Data analysis device and method, program, and recording medium |
CN104748953A (en) * | 2013-12-26 | 2015-07-01 | 通用电气公司 | Methods and systems to monitor health of rotor blades |
CN104748952A (en) * | 2013-12-26 | 2015-07-01 | 通用电气公司 | Methods And Systems To Monitor Health Of Rotor Blades |
US20150184533A1 (en) * | 2013-12-26 | 2015-07-02 | General Electric Company | Methods and systems to monitor health of rotor blades |
US9920628B2 (en) * | 2014-03-24 | 2018-03-20 | General Electric Technology Gmbh | Steam turbine with resonance chamber |
US20150267538A1 (en) * | 2014-03-24 | 2015-09-24 | Alstom Technology Ltd | Steam turbine with resonance chamber |
JPWO2020157818A1 (en) * | 2019-01-29 | 2021-11-18 | Primetals Technologies Japan株式会社 | Diagnostic device and equipment equipped with it and diagnostic method |
JP7077426B2 (en) | 2019-01-29 | 2022-05-30 | Primetals Technologies Japan株式会社 | Diagnostic device and equipment equipped with it and diagnostic method |
CN110095243A (en) * | 2019-06-05 | 2019-08-06 | 哈尔滨汽轮机厂有限责任公司 | A kind of steam turbine blade natural frequency measurement, device |
CN110687124A (en) * | 2019-10-18 | 2020-01-14 | 佛山科学技术学院 | Blade crack positioning method based on visual vibration measurement and nonlinear bicoherence spectrum |
US11352958B2 (en) * | 2020-06-03 | 2022-06-07 | Rolls-Royce Plc | Aircraft gas turbine engine with improved response to rotor unbalance |
US11359549B2 (en) * | 2020-06-03 | 2022-06-14 | Rolls-Royce Plc | Aircraft engine |
Also Published As
Publication number | Publication date |
---|---|
US20140180606A1 (en) | 2014-06-26 |
EP1966571A2 (en) | 2008-09-10 |
WO2007071912A2 (en) | 2007-06-28 |
GB0525936D0 (en) | 2006-02-01 |
US10352823B2 (en) | 2019-07-16 |
US20160187227A1 (en) | 2016-06-30 |
WO2007071912A3 (en) | 2008-06-26 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10352823B2 (en) | Methods of analysing apparatus | |
Dalpiaz et al. | Effectiveness and sensitivity of vibration processing techniques for local fault detection in gears | |
Lei et al. | Fault diagnosis of rotating machinery using an improved HHT based on EEMD and sensitive IMFs | |
Eftekharnejad et al. | The application of spectral kurtosis on acoustic emission and vibrations from a defective bearing | |
Shibata et al. | Fault diagnosis of rotating machinery through visualisation of sound signals | |
EP3049788B1 (en) | Gear fault detection | |
US8752394B2 (en) | Determining fan parameters through pressure monitoring | |
EP2237003B1 (en) | Method for analysing vibration in rotor blades | |
US4422333A (en) | Method and apparatus for detecting and identifying excessively vibrating blades of a turbomachine | |
WO2008093349B1 (en) | A method for non-intrusive on-line detection of turbine blade condition | |
JP2000506262A (en) | Multi-sensor device and method for monitoring a turbomachine | |
Dalpiaz et al. | Gear fault monitoring: comparison of vibration analysis techniques | |
Krause et al. | Asynchronous response analysis of non-contact vibration measurements on compressor rotor blades | |
Elbarghathi et al. | Two stage helical gearbox fault detection and diagnosis based on continuous wavelet transformation of time synchronous averaged vibration signals | |
Kumar et al. | Vibration signal analysis using time and timefrequency domain | |
Bhende et al. | Comprehensive bearing condition monitoring algorithm for incipient fault detection using acoustic emission | |
Hemmati et al. | Rolling element bearing condition monitoring using acoustic emission technique | |
Omar et al. | Gear tooth diagnosis using wavelet multi-resolution analysis enhanced by Kaiser’s windowing | |
Somashekar et al. | Vibration signature analysis of ic engine | |
Klinchaeam et al. | Fault detection of a spur gear using vibration signal with multivariable statistical parameters. | |
Wändell | Multistage gearboxes: Vibration based quality control | |
Sanders | A guide to vibration analysis and associated techniques in condition monitoring | |
Rathna Prasad et al. | Diagnostics of fatigue crack in the shaft using spectral kurtosis | |
Tuma et al. | Assessment of gear quality considering the time domain analysis of noise and vibration signals | |
Ullah et al. | State of the Art Vibration Analysis of Electrical Rotating Machines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ROLLS-ROYCE PLC, GREAT BRITAIN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ANUZIS, PAUL;GELMAN, LEONID MOISEEVICH;REEL/FRAME:021074/0315;SIGNING DATES FROM 20080424 TO 20080427 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |